Abstract
Multidisciplinary design of high speed aircraft for improved sonic boom and aerodynamic performance using a multiobjective optimization procedure is addressed. The optimization procedure minimizes the primary sonic boom (characterized by the first peak in the pressure signature) at a given distance from the aircraft while minimizing the dragto-lift ratio (CD/CL) simultaneously. The secondary sonic boom (characterized by the second peak in the pressure signature) is constrained to be less than its reference value. Upper and lower bounds are also imposed on the lift coefficient. The Kreisselmeier-Steinhauser function is used for the optimization formulation. The flow equations arc solved using a three-dimensional parabolized Navier-Stokes solver. Sonic boom analysis is performed using an extrapolation procedure. A nonlinear programming technique and an approximate analysis procedure are used for optimization. The optimization procedure developed is applied to a delta wing-body configuration. Results are presented for two different cases of Optimization with different sets of design variables. Results obtained show significant improvements in the sonic boom characteristics and the aerodynamic performance in all cases. The use of the approximate analysis technique facilitates significant computational savings.
| Original language | English (US) |
|---|---|
| Title of host publication | 33rd Aerospace Sciences Meeting and Exhibit |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| ISBN (Print) | 9780000000002 |
| State | Published - 1995 |
| Event | 33rd Aerospace Sciences Meeting and Exhibit, 1995 - Reno, United States Duration: Jan 9 1995 → Jan 12 1995 |
Other
| Other | 33rd Aerospace Sciences Meeting and Exhibit, 1995 |
|---|---|
| Country/Territory | United States |
| City | Reno |
| Period | 1/9/95 → 1/12/95 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering