Wing Planform Geometry Effects on Large Subsonic Military Transport Airplanes.

Kulfan, R. M.; Vachal, J. D.

doi:10.21236/ada056124

Cited by 25 publications

(7 citation statements)

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“…Several transonic and aeroelastic SBW design studies have been performed in the past [1][2][3][4][5][6] , although not with a full MDO approach. Recently, as proposed by Pfenninger, NASA became interested in revisiting the possibility of a strut-braced transonic transport.…”

Section: Figure 1 Conventional Cantilever Configurationmentioning

confidence: 99%

Multidisciplinary design optimization of a strut-braced wing transonic transport

Gundlac

Tetrault

Gern

et al. 2000

38th Aerospace Sciences Meeting and Exhibit

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Recent transonic airliner designs have generally converged upon a common cantilever low-wing configuration. It is unlikely that further large strides in performance are possible without a significant departure from the present design paradigm. One such alternative configuration is the strut-braced wing, which uses a strut for wing bending load alleviation, allowing increased aspect ratio and reduced wing thickness to increase the lift to drag ratio. The thinner wing has less transonic wave drag, permitting the wing to unsweep for increased areas of natural laminar flow and further structural weight savings. High aerodynamic efficiency translates into smaller, quieter, less expensive engines with lower noise pollution. A Multidisciplinary Design Optimization (MDO) approach is essential to understand the full potential of this synergistic configuration due to the strong interdependency of structures, aerodynamics and propulsion. NASA defined a need for a 325-passenger transport capable of flying 7500 nautical miles at Mach 0.85 for a 2010 service entry date. Lockheed Martin Aeronautical Systems (LMAS), as Virginia Tech's industry partner, placed great emphasis on realistic constraints, projected technology levels, manufacturing and certification issues. Numerous design challenges specific to the strut-braced wing became apparent through the interactions with LMAS.

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Section: Figure 1 Conventional Cantilever Configurationmentioning

confidence: 99%

Multidisciplinary design optimization of a strut-braced wing transonic transport

Gundlac

Tetrault

Gern

et al. 2000

38th Aerospace Sciences Meeting and Exhibit

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“…An artistic representation of Pfenninger's concept is shown in Figure 20. Later, at the end of the '70s, Boeing and Air Force compared TBW with a baseline model [196]. The analysis showed potentials for lower gross weight, lower empty weight, and reduced fuel consumption.…”

Section: First Work In the Second Half Of The Past Centurymentioning

confidence: 99%

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Cavallaro

Demasi

2016

Progress in Aerospace Sciences

120

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“…The full report shows that the approximating functions were quadratic polynomials. 21 This approach also was used by Jensen, et al 22 to study the effects of using different objective functions on the configuration of a military transport. No further results of studies using this methodology by Boeing have appeared in the literature.…”

Section: Key Early Workmentioning

confidence: 99%

Getting the full benefits of CFD in conceptual design

Mason

Knill

Giunta

et al. 1998

16th AIAA Applied Aerodynamics Conference

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The applied aerodynamics community is struggling to develop a means of incorporating computational fluid dynamics (CFD) into the early stages of aircraft systems design, where it can have the greatest impact on vehicle design. This paper describes developments in computational design methodology arising from research into multidisciplinary design optimization (MDO) done recently by the authors that addresses this problem. The premise is that advanced CFD should be used to precompute a database of solutions which is then interpolated during the design process. Design of experiments theory is used to select the "conditions" or "design points" used to populate the database, and statistical methods are then used to develop a mathematical model of the CFD solutions which is used to "interpolate" the database. The specific models we use, called "response surface models" are quadratic least squares fits to functions of the CFD results. Populating the database is made possible through the use of coarse grained parallel computing. We demonstrate the method using a recent example from our MDO work.

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Wing Planform Geometry Effects on Large Subsonic Military Transport Airplanes.

Cited by 25 publications

References 0 publications

Multidisciplinary design optimization of a strut-braced wing transonic transport

Multidisciplinary design optimization of a strut-braced wing transonic transport

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Getting the full benefits of CFD in conceptual design

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