Advanced search options

Advanced Search Options 🞨

Browse by author name (“Author name starts with…”).

Find ETDs with:

in
/  
in
/  
in
/  
in

Written in Published in Earliest date Latest date

Sorted by

Results per page:

Sorted by: relevance · author · university · dateNew search

You searched for +publisher:"University of Illinois – Urbana-Champaign" +contributor:("Bragg, Michael B."). Showing records 1 – 19 of 19 total matches.

Search Limiters

Last 2 Years | English Only

No search limiters apply to these results.

▼ Search Limiters


University of Illinois – Urbana-Champaign

1. Diebold, Jeffrey Michael. The effects of turbulence on the measurements of five-hole probes.

Degree: PhD, Aerospace Engineering, 2016, University of Illinois – Urbana-Champaign

 The primary goals of this research were to quantify the effects of turbulence on the measurements of five-hole pressure probes (5HP) and to develop a… (more)

Subjects/Keywords: Multihole probes; Five-hole probes (5HP); Turbulence; Experimental fluid dynamics

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Diebold, J. M. (2016). The effects of turbulence on the measurements of five-hole probes. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/97238

Chicago Manual of Style (16th Edition):

Diebold, Jeffrey Michael. “The effects of turbulence on the measurements of five-hole probes.” 2016. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/97238.

MLA Handbook (7th Edition):

Diebold, Jeffrey Michael. “The effects of turbulence on the measurements of five-hole probes.” 2016. Web. 25 Jan 2021.

Vancouver:

Diebold JM. The effects of turbulence on the measurements of five-hole probes. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/97238.

Council of Science Editors:

Diebold JM. The effects of turbulence on the measurements of five-hole probes. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2016. Available from: http://hdl.handle.net/2142/97238

2. Deters, Robert. Performance and slipstream characteristics of small-scale propellers at low Reynolds numbers.

Degree: PhD, 4048, 2014, University of Illinois – Urbana-Champaign

 The low Reynolds number effects of small-scale propellers were investigated. At the Reynolds numbers of interest (below 100,000), a decrease in lift and an increase… (more)

Subjects/Keywords: propeller; slipstream; propeller performance; propeller efficiency; wind tunnel testing; 3D printing; Unmanned Aerial Vehicle (UAV); Micro air vehicle (MAV); low Reynolds number; 7-hole probe; pressure probe measurements; propeller testing; static tests; advancing flow tests; propeller wake; propeller thrust; propeller power; axial velocity; swirl; propeller wing interaction

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Deters, R. (2014). Performance and slipstream characteristics of small-scale propellers at low Reynolds numbers. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/49607

Chicago Manual of Style (16th Edition):

Deters, Robert. “Performance and slipstream characteristics of small-scale propellers at low Reynolds numbers.” 2014. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/49607.

MLA Handbook (7th Edition):

Deters, Robert. “Performance and slipstream characteristics of small-scale propellers at low Reynolds numbers.” 2014. Web. 25 Jan 2021.

Vancouver:

Deters R. Performance and slipstream characteristics of small-scale propellers at low Reynolds numbers. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/49607.

Council of Science Editors:

Deters R. Performance and slipstream characteristics of small-scale propellers at low Reynolds numbers. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/49607

3. Camarinha Fujiwara, Gustavo. Design of 3D swept wing hybrid models for icing wind tunnel tests.

Degree: MS, 4048, 2015, University of Illinois – Urbana-Champaign

 The study of aircraft icing is critical to ensure the safety of any aircraft that might experience icing conditions in flight, including general, commercial, and… (more)

Subjects/Keywords: Aerodynamics; aircraft icing; wind tunnel; icing; ice shape; Accretion; hybrid; sweep; swept; wing; computational fluid dynamics (CFD); aircraft certification; wing design

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Camarinha Fujiwara, G. (2015). Design of 3D swept wing hybrid models for icing wind tunnel tests. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/72880

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Camarinha Fujiwara, Gustavo. “Design of 3D swept wing hybrid models for icing wind tunnel tests.” 2015. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/72880.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Camarinha Fujiwara, Gustavo. “Design of 3D swept wing hybrid models for icing wind tunnel tests.” 2015. Web. 25 Jan 2021.

Vancouver:

Camarinha Fujiwara G. Design of 3D swept wing hybrid models for icing wind tunnel tests. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2015. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/72880.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Camarinha Fujiwara G. Design of 3D swept wing hybrid models for icing wind tunnel tests. [Thesis]. University of Illinois – Urbana-Champaign; 2015. Available from: http://hdl.handle.net/2142/72880

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

4. Mortonson, Andrew. Use of hybrid airfoil design in icing wind tunnel tests of large scale swept wings.

Degree: MS, 4048, 2012, University of Illinois – Urbana-Champaign

 In-flight ice accretion is an important safety consideration for modern aircraft. The certification of commercial airliners for flight into known icing is difficult due to… (more)

Subjects/Keywords: truncated airfoil; airframe icing; hybrid airfoil; Icing Research Tunnel; Common Research Model (CRM)

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Mortonson, A. (2012). Use of hybrid airfoil design in icing wind tunnel tests of large scale swept wings. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/42351

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Mortonson, Andrew. “Use of hybrid airfoil design in icing wind tunnel tests of large scale swept wings.” 2012. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/42351.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Mortonson, Andrew. “Use of hybrid airfoil design in icing wind tunnel tests of large scale swept wings.” 2012. Web. 25 Jan 2021.

Vancouver:

Mortonson A. Use of hybrid airfoil design in icing wind tunnel tests of large scale swept wings. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2012. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/42351.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Mortonson A. Use of hybrid airfoil design in icing wind tunnel tests of large scale swept wings. [Thesis]. University of Illinois – Urbana-Champaign; 2012. Available from: http://hdl.handle.net/2142/42351

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

5. Wiberg, Brock. Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D.

Degree: MS, 4048, 2014, University of Illinois – Urbana-Champaign

 The study of aircraft icing is necessary to ensure the safety of commercial, military, and general aviation aircraft. The certification of modern commercial transports requires… (more)

Subjects/Keywords: aircraft icing; icing; ice shape; Accretion; sweep; swept; wing; computational fluid dynamics (CFD); aircraft certification; hybrid; similitude

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Wiberg, B. (2014). Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/46609

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Wiberg, Brock. “Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D.” 2014. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/46609.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Wiberg, Brock. “Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D.” 2014. Web. 25 Jan 2021.

Vancouver:

Wiberg B. Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/46609.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Wiberg B. Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D. [Thesis]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/46609

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

6. Monastero, Marianne. Validation of 3-D ice accretion documentation and replication method including pressure-sensitive paint.

Degree: MS, 4048, 2014, University of Illinois – Urbana-Champaign

 Accurate representation of ice accretions is important to the study and understanding of aircraft icing. For research and certification purposes, replicas of ice accretions generated… (more)

Subjects/Keywords: icing; Pressure-sensitive Paint; Aerodynamics; Wind Tunnel

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Monastero, M. (2014). Validation of 3-D ice accretion documentation and replication method including pressure-sensitive paint. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/46651

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Monastero, Marianne. “Validation of 3-D ice accretion documentation and replication method including pressure-sensitive paint.” 2014. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/46651.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Monastero, Marianne. “Validation of 3-D ice accretion documentation and replication method including pressure-sensitive paint.” 2014. Web. 25 Jan 2021.

Vancouver:

Monastero M. Validation of 3-D ice accretion documentation and replication method including pressure-sensitive paint. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/46651.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Monastero M. Validation of 3-D ice accretion documentation and replication method including pressure-sensitive paint. [Thesis]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/46651

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

7. Bottalla, Joseph R. Performance of an airfoil with a power-saving, tab-assisted flap system.

Degree: MS, 4048, 2011, University of Illinois – Urbana-Champaign

 This study investigated the feasibility of reducing control surface input power with the use of a tab-assisted flap. Wind tunnel tests were conducted at the… (more)

Subjects/Keywords: Wind tunnel; Aerodynamics; Airfoil; Flap; Tab; Performance

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Bottalla, J. R. (2011). Performance of an airfoil with a power-saving, tab-assisted flap system. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/26028

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Bottalla, Joseph R. “Performance of an airfoil with a power-saving, tab-assisted flap system.” 2011. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/26028.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Bottalla, Joseph R. “Performance of an airfoil with a power-saving, tab-assisted flap system.” 2011. Web. 25 Jan 2021.

Vancouver:

Bottalla JR. Performance of an airfoil with a power-saving, tab-assisted flap system. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2011. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/26028.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Bottalla JR. Performance of an airfoil with a power-saving, tab-assisted flap system. [Thesis]. University of Illinois – Urbana-Champaign; 2011. Available from: http://hdl.handle.net/2142/26028

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

8. Diebold, Jeffrey. Aerodynamics of a swept wing with leading-edge ice at low Reynolds number.

Degree: MS, 4048, 2012, University of Illinois – Urbana-Champaign

 An experimental study of the aerodynamics of a swept wing with ice at low Reynolds number has been performed. The goal of this work was… (more)

Subjects/Keywords: aircraft icing; swept wing icing; swept wing aerodynamics

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Diebold, J. (2012). Aerodynamics of a swept wing with leading-edge ice at low Reynolds number. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/34279

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Diebold, Jeffrey. “Aerodynamics of a swept wing with leading-edge ice at low Reynolds number.” 2012. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/34279.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Diebold, Jeffrey. “Aerodynamics of a swept wing with leading-edge ice at low Reynolds number.” 2012. Web. 25 Jan 2021.

Vancouver:

Diebold J. Aerodynamics of a swept wing with leading-edge ice at low Reynolds number. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2012. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/34279.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Diebold J. Aerodynamics of a swept wing with leading-edge ice at low Reynolds number. [Thesis]. University of Illinois – Urbana-Champaign; 2012. Available from: http://hdl.handle.net/2142/34279

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

9. Hortensius, Ruben. An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight.

Degree: MS, 4048, 2012, University of Illinois – Urbana-Champaign

 Due to the large disturbance created by the sonic boom, supersonic flight is strictly controlled by the FAA. One way in which to minimize the… (more)

Subjects/Keywords: Gulfstream; Rolls-Royce; supersonic engine; bypass; high-flow bypass nacelle; Guide Vanes; oil flow visualization; schlieren; supersonic business jet; quiet supersonic business jet; flow through vanes; choked flow; sonic boom; annular flow; wind tunnel testing; experimental testing

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Hortensius, R. (2012). An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/29820

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Hortensius, Ruben. “An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight.” 2012. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/29820.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Hortensius, Ruben. “An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight.” 2012. Web. 25 Jan 2021.

Vancouver:

Hortensius R. An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2012. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/29820.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Hortensius R. An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight. [Thesis]. University of Illinois – Urbana-Champaign; 2012. Available from: http://hdl.handle.net/2142/29820

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

10. Herrera, Arthur A. An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight.

Degree: MS, 4048, 2011, University of Illinois – Urbana-Champaign

 Current FAA regulations limit the speed of civilian passenger jets to subsonic or transonic speeds due to the effects of the sonic boom produced by… (more)

Subjects/Keywords: Supersonic Business Jet (SSBJ); Sonic Boom; Engine Nacelle; Annular Flow; Annular Blockage; Guide Vanes; Wind Tunnel Testing; Experimental Testing

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Herrera, A. A. (2011). An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/26159

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Herrera, Arthur A. “An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight.” 2011. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/26159.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Herrera, Arthur A. “An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight.” 2011. Web. 25 Jan 2021.

Vancouver:

Herrera AA. An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2011. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/26159.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Herrera AA. An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight. [Thesis]. University of Illinois – Urbana-Champaign; 2011. Available from: http://hdl.handle.net/2142/26159

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

11. Ansell, Phillip J. Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape.

Degree: PhD, 4048, 2014, University of Illinois – Urbana-Champaign

 An analysis of unsteady modes present in the flowfield of an airfoil with a leading-edge horn-ice shape was performed in the current study. An NACA… (more)

Subjects/Keywords: airfoil; icing; ice accretion; flowfield unsteadiness; shear-layer flapping; vortex shedding; aircraft; separation bubble; separated flow; airfoil circulation; Strouhal number; shear-layer reattachment; stall; unsteady flow

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Ansell, P. J. (2014). Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/46620

Chicago Manual of Style (16th Edition):

Ansell, Phillip J. “Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape.” 2014. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/46620.

MLA Handbook (7th Edition):

Ansell, Phillip J. “Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape.” 2014. Web. 25 Jan 2021.

Vancouver:

Ansell PJ. Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/46620.

Council of Science Editors:

Ansell PJ. Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/46620


University of Illinois – Urbana-Champaign

12. Ansell, Phillip J. Flight envelope protection using flap hinge moment measurement.

Degree: MS, 4048, 2010, University of Illinois – Urbana-Champaign

 An experimental investigation of the sensitivity of flap hinge moment to airfoil surface contamination was conducted at the University of Illinois at Urbana-Champaign Aerodynamics Research… (more)

Subjects/Keywords: hinge moment; envelope protection; icing; simulated icing; roughness; simulated damage; contamination; Aerodynamics; aeronautics; stall; NACA 3415; NACA 23012; glaze ice; rime ice; trim tab; Flap; control surface

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Ansell, P. J. (2010). Flight envelope protection using flap hinge moment measurement. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/16147

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Ansell, Phillip J. “Flight envelope protection using flap hinge moment measurement.” 2010. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/16147.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Ansell, Phillip J. “Flight envelope protection using flap hinge moment measurement.” 2010. Web. 25 Jan 2021.

Vancouver:

Ansell PJ. Flight envelope protection using flap hinge moment measurement. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2010. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/16147.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Ansell PJ. Flight envelope protection using flap hinge moment measurement. [Thesis]. University of Illinois – Urbana-Champaign; 2010. Available from: http://hdl.handle.net/2142/16147

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

13. Herges, Thomas. The effects of micro-vortex generators on normal shock wave/boundary layer interactions.

Degree: PhD, 4048, 2014, University of Illinois – Urbana-Champaign

 Shock wave/boundary-layer interactions (SWBLIs) are complex flow phenomena that are important in the design and performance of internal supersonic and transonic flow fields such as… (more)

Subjects/Keywords: shock wave boundary layer interactions (SWBLI); normal shock wave; boundary layer; supersonic flow; vortex generators; SWBLI control; shock wave unsteadiness; supersonic inlet; supersonic inlet control; inlet buzz; optical diagnostic techniques; camera housing; schlieren imaging; surface oil flow visualization; pressure sensitive paint; particle image velocimetry; shear stress measurements; format figure references in Microsoft Word

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Herges, T. (2014). The effects of micro-vortex generators on normal shock wave/boundary layer interactions. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/46573

Chicago Manual of Style (16th Edition):

Herges, Thomas. “The effects of micro-vortex generators on normal shock wave/boundary layer interactions.” 2014. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/46573.

MLA Handbook (7th Edition):

Herges, Thomas. “The effects of micro-vortex generators on normal shock wave/boundary layer interactions.” 2014. Web. 25 Jan 2021.

Vancouver:

Herges T. The effects of micro-vortex generators on normal shock wave/boundary layer interactions. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/46573.

Council of Science Editors:

Herges T. The effects of micro-vortex generators on normal shock wave/boundary layer interactions. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/46573

14. Uhlig, Daniel. Micro air vehicle motion tracking and aerodynamic modeling.

Degree: PhD, 4048, 2014, University of Illinois – Urbana-Champaign

 Aerodynamic performance of small-scale fixed-wing flight is not well understood, and flight data are needed to gain a better understanding of the aerodynamics of micro… (more)

Subjects/Keywords: unsteady aerodynamics; Micro air vehicle (MAV); flight dynamics; motion tracking; Vicon; modeling; separation parameter; MAV performance

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Uhlig, D. (2014). Micro air vehicle motion tracking and aerodynamic modeling. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/49560

Chicago Manual of Style (16th Edition):

Uhlig, Daniel. “Micro air vehicle motion tracking and aerodynamic modeling.” 2014. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/49560.

MLA Handbook (7th Edition):

Uhlig, Daniel. “Micro air vehicle motion tracking and aerodynamic modeling.” 2014. Web. 25 Jan 2021.

Vancouver:

Uhlig D. Micro air vehicle motion tracking and aerodynamic modeling. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/49560.

Council of Science Editors:

Uhlig D. Micro air vehicle motion tracking and aerodynamic modeling. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/49560

15. Merrett, Craig G. Aero-servo-viscoelasticity theory: lifting surfaces, plates, velocity transients, flutter, and instability.

Degree: PhD, 4048, 2011, University of Illinois – Urbana-Champaign

 Modern flight vehicles are fabricated from composite materials resulting in flexible structures that behave differently from the more traditional elastic metal structures. Composite materials offer… (more)

Subjects/Keywords: Aeroelasticity; aero-servo-elasticity; viscoelasticity; aero-viscoelasticity; velocity transients; flutter; panel flutter; dynamic stability

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Merrett, C. G. (2011). Aero-servo-viscoelasticity theory: lifting surfaces, plates, velocity transients, flutter, and instability. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/24148

Chicago Manual of Style (16th Edition):

Merrett, Craig G. “Aero-servo-viscoelasticity theory: lifting surfaces, plates, velocity transients, flutter, and instability.” 2011. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/24148.

MLA Handbook (7th Edition):

Merrett, Craig G. “Aero-servo-viscoelasticity theory: lifting surfaces, plates, velocity transients, flutter, and instability.” 2011. Web. 25 Jan 2021.

Vancouver:

Merrett CG. Aero-servo-viscoelasticity theory: lifting surfaces, plates, velocity transients, flutter, and instability. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2011. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/24148.

Council of Science Editors:

Merrett CG. Aero-servo-viscoelasticity theory: lifting surfaces, plates, velocity transients, flutter, and instability. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2011. Available from: http://hdl.handle.net/2142/24148


University of Illinois – Urbana-Champaign

16. Yeong, Yong Han. Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft.

Degree: MS, 4048, 2010, University of Illinois – Urbana-Champaign

 Sonic boom attenuation is a considerable design challenge to enable civilian aircraft to operate at supersonic flight conditions. One technology proposed by Gulfstream Aerospace Corporation… (more)

Subjects/Keywords: Sonic Boom; Supersonic; Nacelle Bypass

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Yeong, Y. H. (2010). Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/14621

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Yeong, Yong Han. “Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft.” 2010. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/14621.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Yeong, Yong Han. “Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft.” 2010. Web. 25 Jan 2021.

Vancouver:

Yeong YH. Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2010. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/14621.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Yeong YH. Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft. [Thesis]. University of Illinois – Urbana-Champaign; 2010. Available from: http://hdl.handle.net/2142/14621

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


University of Illinois – Urbana-Champaign

17. Busch, Greg T. Experimental study of full-scale iced-airfoil aerodynamic performance using sub-scale simulations.

Degree: PhD, 4048, 2010, University of Illinois – Urbana-Champaign

 Determining the aerodynamic effects of ice accretion on aircraft surfaces is an important step in aircraft design and certification. The goal of this work was… (more)

Subjects/Keywords: ice accretion; iced airfoil; sub-scale simulation

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Busch, G. T. (2010). Experimental study of full-scale iced-airfoil aerodynamic performance using sub-scale simulations. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/14714

Chicago Manual of Style (16th Edition):

Busch, Greg T. “Experimental study of full-scale iced-airfoil aerodynamic performance using sub-scale simulations.” 2010. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/14714.

MLA Handbook (7th Edition):

Busch, Greg T. “Experimental study of full-scale iced-airfoil aerodynamic performance using sub-scale simulations.” 2010. Web. 25 Jan 2021.

Vancouver:

Busch GT. Experimental study of full-scale iced-airfoil aerodynamic performance using sub-scale simulations. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2010. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/14714.

Council of Science Editors:

Busch GT. Experimental study of full-scale iced-airfoil aerodynamic performance using sub-scale simulations. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2010. Available from: http://hdl.handle.net/2142/14714


University of Illinois – Urbana-Champaign

18. Campbell, Scot E. Multi-scale path planning for reduced environmental impact of aviation.

Degree: PhD, 4048, 2010, University of Illinois – Urbana-Champaign

 A future air traffic management system capable of rerouting aircraft trajectories in real-time in response to transient and evolving events would result in increased aircraft… (more)

Subjects/Keywords: contrail; aviation; environment; path planning; Mixed-integer linear programming (MILP); optimization; trajectory; air traffic management

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Campbell, S. E. (2010). Multi-scale path planning for reduced environmental impact of aviation. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/16034

Chicago Manual of Style (16th Edition):

Campbell, Scot E. “Multi-scale path planning for reduced environmental impact of aviation.” 2010. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/16034.

MLA Handbook (7th Edition):

Campbell, Scot E. “Multi-scale path planning for reduced environmental impact of aviation.” 2010. Web. 25 Jan 2021.

Vancouver:

Campbell SE. Multi-scale path planning for reduced environmental impact of aviation. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2010. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/16034.

Council of Science Editors:

Campbell SE. Multi-scale path planning for reduced environmental impact of aviation. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2010. Available from: http://hdl.handle.net/2142/16034


University of Illinois – Urbana-Champaign

19. Lee, Sang. Large eddy simulation of shock boundary layer interaction control using micro-vortex generators.

Degree: PhD, 4048, 2010, University of Illinois – Urbana-Champaign

 The performance of supersonic engine inlets and external aerodynamic surfaces can be critically affected by shock wave / boundary layer interactions (SBLIs), whose severe adverse… (more)

Subjects/Keywords: supersonic; vortex generator; shock boundary layer interaction; Large Eddy Simulation (LES)

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Lee, S. (2010). Large eddy simulation of shock boundary layer interaction control using micro-vortex generators. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/14579

Chicago Manual of Style (16th Edition):

Lee, Sang. “Large eddy simulation of shock boundary layer interaction control using micro-vortex generators.” 2010. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/14579.

MLA Handbook (7th Edition):

Lee, Sang. “Large eddy simulation of shock boundary layer interaction control using micro-vortex generators.” 2010. Web. 25 Jan 2021.

Vancouver:

Lee S. Large eddy simulation of shock boundary layer interaction control using micro-vortex generators. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2010. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/14579.

Council of Science Editors:

Lee S. Large eddy simulation of shock boundary layer interaction control using micro-vortex generators. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2010. Available from: http://hdl.handle.net/2142/14579

.