Mach weighted area ruling for supersonic vehicles

Details Mach weighted area ruling for supersonic vehicles Mach weighted area ruling for supersonic vehicles

2005-09-13

2005-09-13

Poon, Peter M. (Department: 3643)

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

C244S119000

Reexamination Certificate

active

06942178

ABSTRACT:
A method and design system for a low drag vehicle includes determining a plurality of configurations for at least two different Mach numbers that minimize the rate of change of cross-sectional area of the vehicle in accordance with the Sears-Haack minimum drag body. A user can specify design objectives and constraints to meet in determining optimum configurations for the vehicle, and the configurations are averaged to determine a final configuration. The at least two configurations can be weighted to emphasize optimum performance at particular operating conditions before averaging the configurations. The second order derivative of cross-sectional area for the final configuration can be smoothed, and then integrated twice to determine the cross-sectional area.

REFERENCES:
Area Rule and Transonic Flight, http://www.aerospaceweb.org/question/aerodynamics/q0104.shtml.
Sriram K. Rallabhandi and Dimitri N. Mavris, An Unstructured Wave Drag Code For Preliminary Design of Future Supersonic Aircraft, American Institue of Aeronautics and Astronautics Paper, pp. 1-8, Aerospace Systems Design Lab, Georgia Tech, Atlanta.
Minoru Yoshimoto, Naoki Uchiyama, Optimization of Canard Surface Positioning of Supersonic Business Jet for Low Boom and Low Drag Design, American Institue of Aeronautics and Astronautics, 2003, pp. 1-10, AIAA 2003-3576, 33rd AIAA Fluid Dyanics Conference and Exhibit, Orlando, Florida, Jun. 23-27, 2003.
Yoshikazu Makino, Ken'ichiro Suzuki, Masayoshi Noguchi and Kenji Yoshida, Non-Axisymmetrical Fuselage Shape Modification for Drag Reduction of a Low Sonic-Boom Airplane, American Institue of Aeronautics and Astronautics, 2003, pp. 1-11, AIAA 2003-557, 41st Aerospace Sciences Meeting and Exhibit Jan. 6-9, 2003, Reno, Nevada.
Donald C. Howe, Sonic Boom Reduction Through the Use of Non-Axsymmetric Configuration Shaping, American Institue of Aeronautics and Astronautics, 2003, pp. 1-9, AIAA 2003-929, 41st Aerospace Sciences Meeting and Exhibit, Jan. 6-9, 2003, Reno, Nevada.
Charbel Farhat, Brian Argrow, Melike Nikbay and Kurt Maute, A Shape Optimization Methodology with F-Function Lobe Balancing for Mitigating the Sonic Boom, American Institute of Aeronautics and Astronautics, 2002, pp. 1-9, AIAA 2002-5551, 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization. Sep. 4-6, 2002. Atlanta Georgia.
Frank Marconi, Rodney D.W. Bowersox and Joseph A. Schetz, Sonic Boom Alleviation Using Keel Configurations, Journal of Aircraft, vol. 40, No. 2, Mar.-Apr. 2003, pp. 363-369.
Christine M. Darden, Sonic Boom Minimization with Nose-Bluntness Relaxation, NASA, 1979, pp. 1-50, NASA Technical Paper 1348, USA.
Richard L. Campbell, “Efficient Viscous Design of Realistic Aircraft Configurations”, American Institute of Aeronautics and Astronautics Publication No. AIAA-98-2539.

Affiliated with

Also associated with

Rating

Mach weighted area ruling for supersonic vehicles does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Mach weighted area ruling for supersonic vehicles, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Mach weighted area ruling for supersonic vehicles will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-3448655