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Arizona State University
1.
Kirkman, Jeffrey Jordan.
Transonic Flow Around Swept Wings: Revisiting Von Kármán’s
Similarity Rule.
Degree: Aerospace Engineering, 2016, Arizona State University
URL: http://repository.asu.edu/items/38688 
► Modern aircraft are expected to fly faster and more efficiently than their predecessors. To improve aerodynamic efficiency, designers must carefully consider and handle shock wave…
(more)
▼ Modern aircraft are expected to fly faster and more
efficiently than their predecessors. To improve aerodynamic
efficiency, designers must carefully consider and handle shock wave
formation. Presently, many designers utilize computationally heavy
optimization methods to design wings. While these methods may work,
they do not provide insight. This thesis aims to better understand
fundamental methods that govern wing design. In order to further
understand the flow in the transonic regime, this work revisits the
Transonic Similarity Rule. This rule postulates an equivalent
incompressible geometry to any high speed geometry in flight and
postulates a “stretching” analogy. This thesis utilizes panel
methods and Computational Fluid Dynamics (CFD) to show that the
“stretching” analogy is incorrect, but instead the flow is
transformed by a nonlinear “scaling” of the flow velocity. This
work also presents data to show the discrepancies between many
famous authors in deriving the accurate Critical Pressure
Coefficient (Cp*) equation for both swept and unswept wing
sections. The final work of the thesis aims to identify the correct
predictive methods for the Critical Pressure
Coefficient.
Subjects/Keywords: Aerospace engineering; Aircraft Wing Sweep; Critical Pressure Coefficient; Shock Formation; Transonic Similarity Rule
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APA (6th Edition):
Kirkman, J. J. (2016). Transonic Flow Around Swept Wings: Revisiting Von Kármán’s
Similarity Rule. (Masters Thesis). Arizona State University. Retrieved from http://repository.asu.edu/items/38688
Chicago Manual of Style (16th Edition):
Kirkman, Jeffrey Jordan. “Transonic Flow Around Swept Wings: Revisiting Von Kármán’s
Similarity Rule.” 2016. Masters Thesis, Arizona State University. Accessed January 24, 2021.
http://repository.asu.edu/items/38688.
MLA Handbook (7th Edition):
Kirkman, Jeffrey Jordan. “Transonic Flow Around Swept Wings: Revisiting Von Kármán’s
Similarity Rule.” 2016. Web. 24 Jan 2021.
Vancouver:
Kirkman JJ. Transonic Flow Around Swept Wings: Revisiting Von Kármán’s
Similarity Rule. [Internet] [Masters thesis]. Arizona State University; 2016. [cited 2021 Jan 24].
Available from: http://repository.asu.edu/items/38688.
Council of Science Editors:
Kirkman JJ. Transonic Flow Around Swept Wings: Revisiting Von Kármán’s
Similarity Rule. [Masters Thesis]. Arizona State University; 2016. Available from: http://repository.asu.edu/items/38688
2.
Camarinha Fujiwara, Gustavo.
Design of 3D swept wing hybrid models for icing wind tunnel tests.
Degree: MS, 4048, 2015, University of Illinois – Urbana-Champaign
URL: http://hdl.handle.net/2142/72880
► 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)
▼ 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 military aviation. The certification of modern commercial transports requires manufacturers to demonstrate that these
aircraft can safely operate during icing conditions through a set of flight tests, consistent with the standards set forth by the Federal Aviation Administration.
This is often expensive and challenging to find the appropriate icing test conditions. Thus, both computational methods and icing wind tunnel experiments are utilized during the design and certification of
aircraft ice-protection systems to provide a controlled and repeatable environment to mitigate risks, reduce costs, and validate the existing computational icing tools.
However, the existing icing wind tunnel facilities cannot accommodate large wings such as those found on modern commercial
aircraft without being dramatically scaled. Two methods of scaling exist. The first geometrically scales the entire geometry to fit inside the tunnel test section and then scales the icing conditions to obtain icing similitude. The second maintains the full-scale leading edge of the reference geometry and replaces the aft section with a truncated trailing edge that produces a similar flowfield around the leading edge with a significantly shorter chord, reducing model size and tunnel blockage. This type of model is referred to as a hybrid and its biggest advantage lies in the fact that it is designed to produce full-scale ice shapes, while reducing or even eliminating the need for icing scaling. While a design method for a straight, untapered hybrid
wing is well documented and there is a broad set of experimental data available, the design of a swept, hybrid
wing lacks both a design method and experimental data.
This thesis established a design method for large hybrid swept wings that reproduce full-scale ice accretions through icing wind tunnel tests. The design method was broken down in two steps: 1) A 2D hybrid airfoil design, and 2) A 3D hybrid swept
wing design. Multiple existing computational tools were employed and several parametric studies performed.
It was shown, in 2D, that matching the stagnation point location on the leading edge of the hybrid airfoil had a first-order impact on matching the full-scale ice shape, while matching the suction peak magnitude and location had a second-order effect. The closer to the leading edge lift was generated for a given hybrid design, the less total load was required to reach the same stagnation point location. As an implication, more front-loaded airfoils required less lift than more aft-loaded ones to reach the same stagnation point location on a hybrid airfoil. More front load also increased the risk of flow separation near the leading edge, while more aft load increased the risk of separation near the trailing edge. Finally, higher hybrid scale factors were shown to increase the risk of flow separation.
In 3D,
sweep angle was…
Advisors/Committee Members: Bragg, Michael B. (advisor).
Subjects/Keywords: Aerodynamics; aircraft icing; wind tunnel; icing; ice shape; Accretion; hybrid; sweep; swept; wing; computational fluid dynamics (CFD); aircraft certification; wing design
…aircraft performance and safety. Depending on the location of the ice, the shape of
the wing, and… …swept wing icing.
Aircraft Icing Protection Program
Icing
Avoidance
Icing
Tolerant
Aircraft… …a transonic wing having a quarter-chord sweep angle of
35◦ . The supercritical wing was… …was selected to represent the
wing inside the Yehudi break and near the aircraft body. The… …designed utilizing the stations in the normal direction,
applying simple sweep wing theory, as…
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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 24, 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. 24 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 24].
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
3.
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
URL: http://hdl.handle.net/2142/46609
► 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)
▼ 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 manufacturers to demonstrate that these
aircraft can safely operate during icing conditions consistent with the standards set forth by the Federal Aviation Administration (FAA). While some of these tests are performed on actual
aircraft in flight, this is often very expensive and does not provide an adequately controlled matrix of test conditions. Computational tools are used throughout the design and certification of anti-ice systems. However, computational methods alone are not sufficient for
aircraft certification. Icing wind tunnels are used for
aircraft certification to reduce costs, provide a controlled test matrix of conditions, and validate computational icing tools.
The size of
aircraft models that can be tested in icing wind tunnels is limited by the size and capability of existing facilities. Large wings, such as those found on modern narrow and wide-body commercial transports, cannot fit in existing test sections without being dramatically scaled. Two methods of scaling exist. The first involves geometrically scaling a section of the reference
wing to fit inside the tunnel test section and then scaling the icing conditions in order to maintain icing similitude. The second method maintains the full-scale leading edge of the reference geometry but replaces the aft section of the
wing with a tail that is designed to produce similar flow around the leading edge but with a considerably shorter chord length, reducing model size and blockage. This type of model is called a hybrid and is used to generate full-scale ice shapes so that, in the simplest cases, no icing scaling is necessary. However, the methods can be combined so that the hybrid model design is used to maintain geometric similitude while icing scaling is employed to account for differences in pressure, velocity, or other conditions.
Modern commercial transport
aircraft have large, swept wings. While a broad set of experimental data exist in the literature for airfoil and straight
wing icing, there is a distinct lack of data for large, swept wings. Such data is needed in order to better understand the 3D icing physics on swept wings and to allow computational tools to be developed and validated for 3D ice features such as scallops.
In this thesis, computational tools were used to better understand the flow over a large-scale, swept-
wing, hybrid model mounted vertically in the NASA Glenn Icing Research Tunnel (IRT). Fluent, a commercial CFD code, was used to calculate flows around the flapped-hybrid model in the IRT, mounted with the root at the floor and the tip at the ceiling of the test section. Inviscid analysis reveals that the upwash ahead of the model causes the local lift coefficient to increase significantly across the swept model due to the effect of the floor and ceiling. This change in spanwise loading is shown to move the attachment line location farther…
Advisors/Committee Members: Bragg, Michael B. (advisor).
Subjects/Keywords: aircraft icing; icing; ice shape; Accretion; sweep; swept; wing; computational fluid dynamics (CFD); aircraft certification; hybrid; similitude
…2.2.2 Simple Sweep Theory . . . . . . . . . . . . . . . .
2.2.3 Wing Model Design… …aircraft
y
= Cartesian coordinate with axis pointing from center of aircraft to right wing
z… …sweep angle
λ
= wing taper ratio
µ
= dynamic viscosity
ν
= kinematic viscosity
ρ… …Champaign
WB
= Wing-Body
xv
Chapter 1
Introduction
1.1
Motivation
The study of aircraft… …with a swept-wing configuration that is representative of a modern transport aircraft
was…
Record Details
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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 24, 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. 24 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 24].
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
University of Pretoria
4.
[No author].
Longitudinal handling characteristics of a tailless
gull-wing aircraft
.
Degree: 2008, University of Pretoria
URL: http://upetd.up.ac.za/thesis/available/etd-09182008-132941/
► A handling quality investigation was performed on the swept gull-wing configuration. The swept gull-wing configuration is tailless and has a wing with a transition in…
(more)
▼ A handling quality investigation was performed on
the swept gull-
wing configuration. The swept gull-
wing
configuration is tailless and has a
wing with a transition in the
sweep and dihedral angle. An example of this type of
aircraft is
the Exulans. This
aircraft is currently under development at the
University of Pretoria. The handling quality study was focussed on
pitch axis dynamics. The Exulans is a research testbed that will be
used to investigate the swept gull-
wing configuration and its
special controls by means of full-scale flight testing. Variable
wing sweep, twisting elevons and winglets will be investigated as
means of control. These control devices are configured in such a
way as to have minimum impact on the performance of the
aircraft.
The handling qualities of the swept gull-
wing configuration have to
be acceptable while using these different control strategies. The
study was launched to investigate whether a gull-
wing configuration
aircraft will have satisfactory handling qualities at CG positions
associated with the most favourable aerodynamic performance. There
is an aerodynamic performance gain in designing an
aircraft so that
the CG falls on the so-called `E-point'. The E-point is the centre
of pressure for an elliptical circulation distribution. An
elliptical circulation distribution is associated with the highest
Oswald efficiency for an
aircraft. Time domain simulation
techniques and frequency domain analysis techniques were used to
analyse the handling qualities of the gull-
wing configuration. The
C-star criterion was used to analyse handling qualities with time
domain simulation data as input. Comparative time domain
simulations were performed between the Exulans and other
aircraft
to compare handling qualities. Eigenvalue analysis was used
together with the thumbprint criterion to investigate inherent
gull-
wing airframe dynamics. The Shomber-Gertsen and Military
Specification 8785 criteria were also used for the same purpose.
The Neal-Smith method was used to investigate the effect of control
authority on handling qualities and the effect of a pilot. The
Monnich and Dalldorff criterion was used to evaluate gust handling
qualities. An analysis chart by Fremaux and Vairo was used to
evaluate the tumbling susceptibility of the gull-
wing
configuration. The pitch handling quality investigation shows
sufficient promise that the swept gull-
wing configuration will have
acceptable handling qualities with the CG placed at positions
associated with optimised aerodynamic performance. Analysis showed
that the swept gull-
wing configuration is potentially prone to
tumbling. With low static margins, the configuration should exhibit
improved handling qualities in gusty conditions when compared to
existing tailless
aircraft. It is recommended that a lateral
handling quality study be performed before full scale flight
testing commences on the Exulans. In addition, the possibility of
wingtip stall must be investigated for the case of the swept
gull-
wing configuration.
Advisors/Committee Members: Theron, Nicolaas J (advisor).
Subjects/Keywords: Flight simulation;
Tumbling;
Thumbprint criterion;
Neal-smith analysis;
C-star criterion;
Shomber-gertsen analysis;
Pilot induced oscillation;
Oswald efficiency;
Pilot mathematical model;
Variable sweep wing;
Exulans;
Variable static margin;
Swept gull-wing configuration;
O-point;
E-point;
Handling qualities;
Gust handling qualities;
Tailless aircraft;
Pecking;
Monnich and dalldorff criterion;
UCTD
Record Details
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Record Details
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
author], [. (2008). Longitudinal handling characteristics of a tailless
gull-wing aircraft
. (Masters Thesis). University of Pretoria. Retrieved from http://upetd.up.ac.za/thesis/available/etd-09182008-132941/
Chicago Manual of Style (16th Edition):
author], [No. “Longitudinal handling characteristics of a tailless
gull-wing aircraft
.” 2008. Masters Thesis, University of Pretoria. Accessed January 24, 2021.
http://upetd.up.ac.za/thesis/available/etd-09182008-132941/.
MLA Handbook (7th Edition):
author], [No. “Longitudinal handling characteristics of a tailless
gull-wing aircraft
.” 2008. Web. 24 Jan 2021.
Vancouver:
author] [. Longitudinal handling characteristics of a tailless
gull-wing aircraft
. [Internet] [Masters thesis]. University of Pretoria; 2008. [cited 2021 Jan 24].
Available from: http://upetd.up.ac.za/thesis/available/etd-09182008-132941/.
Council of Science Editors:
author] [. Longitudinal handling characteristics of a tailless
gull-wing aircraft
. [Masters Thesis]. University of Pretoria; 2008. Available from: http://upetd.up.ac.za/thesis/available/etd-09182008-132941/
University of Pretoria
5.
Agenbag, Daniel
Sarel.
Longitudinal
handling characteristics of a tailless gull-wing
aircraft.
Degree: Mechanical and Aeronautical
Engineering, 2008, University of Pretoria
URL: http://hdl.handle.net/2263/28011
► A handling quality investigation was performed on the swept gull-wing configuration. The swept gull-wing configuration is tailless and has a wing with a transition in…
(more)
▼ A handling quality investigation was performed on the
swept gull-
wing configuration. The swept gull-
wing configuration is
tailless and has a
wing with a transition in the
sweep and dihedral
angle. An example of this type of
aircraft is the Exulans. This
aircraft is currently under development at the University of
Pretoria. The handling quality study was focussed on pitch axis
dynamics. The Exulans is a research testbed that will be used to
investigate the swept gull-
wing configuration and its special
controls by means of full-scale flight testing. Variable
wing
sweep, twisting elevons and winglets will be investigated as means
of control. These control devices are configured in such a way as
to have minimum impact on the performance of the
aircraft. The
handling qualities of the swept gull-
wing configuration have to be
acceptable while using these different control strategies. The
study was launched to investigate whether a gull-
wing configuration
aircraft will have satisfactory handling qualities at CG positions
associated with the most favourable aerodynamic performance. There
is an aerodynamic performance gain in designing an
aircraft so that
the CG falls on the so-called `E-point'. The E-point is the centre
of pressure for an elliptical circulation distribution. An
elliptical circulation distribution is associated with the highest
Oswald efficiency for an
aircraft. Time domain simulation
techniques and frequency domain analysis techniques were used to
analyse the handling qualities of the gull-
wing configuration. The
C-star criterion was used to analyse handling qualities with time
domain simulation data as input. Comparative time domain
simulations were performed between the Exulans and other
aircraft
to compare handling qualities. Eigenvalue analysis was used
together with the thumbprint criterion to investigate inherent
gull-
wing airframe dynamics. The Shomber-Gertsen and Military
Specification 8785 criteria were also used for the same purpose.
The Neal-Smith method was used to investigate the effect of control
authority on handling qualities and the effect of a pilot. The
Monnich and Dalldorff criterion was used to evaluate gust handling
qualities. An analysis chart by Fremaux and Vairo was used to
evaluate the tumbling susceptibility of the gull-
wing
configuration. The pitch handling quality investigation shows
sufficient promise that the swept gull-
wing configuration will have
acceptable handling qualities with the CG placed at positions
associated with optimised aerodynamic performance. Analysis showed
that the swept gull-
wing configuration is potentially prone to
tumbling. With low static margins, the configuration should exhibit
improved handling qualities in gusty conditions when compared to
existing tailless
aircraft. It is recommended that a lateral
handling quality study be performed before full scale flight
testing commences on the Exulans. In addition, the possibility of
wingtip stall must be investigated for the case of the swept
gull-
wing configuration.
Advisors/Committee Members: Theron, Nicolaas J. (advisor).
Subjects/Keywords: Flight
simulation;
Tumbling; Thumbprint
criterion; Neal-smith
analysis; C-star
criterion;
Shomber-gertsen analysis; Pilot induced
oscillation; Oswald
efficiency; Pilot
mathematical model; Variable sweep
wing;
Exulans; Variable
static margin; Swept
gull-wing configuration;
O-point;
E-point; Handling
qualities; Gust handling
qualities; Tailless
aircraft;
Pecking; Monnich and
dalldorff criterion;
UCTD
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Agenbag, D. (2008). Longitudinal
handling characteristics of a tailless gull-wing
aircraft. (Masters Thesis). University of Pretoria. Retrieved from http://hdl.handle.net/2263/28011
Chicago Manual of Style (16th Edition):
Agenbag, Daniel. “Longitudinal
handling characteristics of a tailless gull-wing
aircraft.” 2008. Masters Thesis, University of Pretoria. Accessed January 24, 2021.
http://hdl.handle.net/2263/28011.
MLA Handbook (7th Edition):
Agenbag, Daniel. “Longitudinal
handling characteristics of a tailless gull-wing
aircraft.” 2008. Web. 24 Jan 2021.
Vancouver:
Agenbag D. Longitudinal
handling characteristics of a tailless gull-wing
aircraft. [Internet] [Masters thesis]. University of Pretoria; 2008. [cited 2021 Jan 24].
Available from: http://hdl.handle.net/2263/28011.
Council of Science Editors:
Agenbag D. Longitudinal
handling characteristics of a tailless gull-wing
aircraft. [Masters Thesis]. University of Pretoria; 2008. Available from: http://hdl.handle.net/2263/28011
. 
Open Access Theses and Dissertations
