Abstract
A design optimization procedure for improved sonic boom and aerodynamic performance of high speed aircraft is presented. The rnultiobjectivc optimization procedure simultaneously minimizes the primary sonic boom, characterized by the first peak in the pressure signature, at a given distance from the aircraft and the drag-to-lift ratio (CD/CL) of the aircraft. The secondary sonic boom (characterized by the second peak in the pressure signature) is constrained below its reference value. Upper and lower bounds are also imposed on the lift coefficient. The flow equations are solved using a threedimensional parabolized Navier-Stokes solver. Sonic boom analysis is performed using an extrapolation procedure. The Kreisselmeicr-Steinhauser function is used for the multiobjective optimization formulation. A discrete semi-analytical aerodynamic sensitivity analysis procedure coupled with an analytical grid sensitivity analysis technique is used for evaluating design sensitivities. The use of the semi-analytical sensitivity analysis techniques results in significant computational savings. A nonlinear programming technique and an approximate analysis procedure arc used in the optimization. The optimization procedure developed is applied to a doubly swept wing-body configuration. Results obtained show significant improvements in the sonic boom characteristics and the aerodynamic performance.
| Original language | English (US) |
|---|---|
| Title of host publication | 1995 Fluid Dynamics Conference |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| Pages | 1-12 |
| Number of pages | 12 |
| State | Published - 1995 |
| Event | Fluid Dynamics Conference, 1995 - San Diego, United States Duration: Jun 19 1995 → Jun 22 1995 |
Other
| Other | Fluid Dynamics Conference, 1995 |
|---|---|
| Country | United States |
| City | San Diego |
| Period | 6/19/95 → 6/22/95 |
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ASJC Scopus subject areas
- Aerospace Engineering
- Mechanical Engineering
- Fluid Flow and Transfer Processes
- Energy Engineering and Power Technology
Cite this
Optimization procedure for reduced sonic boom in high speed flight. / Chattopadhyay, Aditi; Narayan, J. R.; Pagaldipti, N.; Wensheng, X.; Cheun, S. H.
1995 Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 1995. p. 1-12.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Optimization procedure for reduced sonic boom in high speed flight
AU - Chattopadhyay, Aditi
AU - Narayan, J. R.
AU - Pagaldipti, N.
AU - Wensheng, X.
AU - Cheun, S. H.
PY - 1995
Y1 - 1995
N2 - A design optimization procedure for improved sonic boom and aerodynamic performance of high speed aircraft is presented. The rnultiobjectivc optimization procedure simultaneously minimizes the primary sonic boom, characterized by the first peak in the pressure signature, at a given distance from the aircraft and the drag-to-lift ratio (CD/CL) of the aircraft. The secondary sonic boom (characterized by the second peak in the pressure signature) is constrained below its reference value. Upper and lower bounds are also imposed on the lift coefficient. The flow equations are solved using a threedimensional parabolized Navier-Stokes solver. Sonic boom analysis is performed using an extrapolation procedure. The Kreisselmeicr-Steinhauser function is used for the multiobjective optimization formulation. A discrete semi-analytical aerodynamic sensitivity analysis procedure coupled with an analytical grid sensitivity analysis technique is used for evaluating design sensitivities. The use of the semi-analytical sensitivity analysis techniques results in significant computational savings. A nonlinear programming technique and an approximate analysis procedure arc used in the optimization. The optimization procedure developed is applied to a doubly swept wing-body configuration. Results obtained show significant improvements in the sonic boom characteristics and the aerodynamic performance.
AB - A design optimization procedure for improved sonic boom and aerodynamic performance of high speed aircraft is presented. The rnultiobjectivc optimization procedure simultaneously minimizes the primary sonic boom, characterized by the first peak in the pressure signature, at a given distance from the aircraft and the drag-to-lift ratio (CD/CL) of the aircraft. The secondary sonic boom (characterized by the second peak in the pressure signature) is constrained below its reference value. Upper and lower bounds are also imposed on the lift coefficient. The flow equations are solved using a threedimensional parabolized Navier-Stokes solver. Sonic boom analysis is performed using an extrapolation procedure. The Kreisselmeicr-Steinhauser function is used for the multiobjective optimization formulation. A discrete semi-analytical aerodynamic sensitivity analysis procedure coupled with an analytical grid sensitivity analysis technique is used for evaluating design sensitivities. The use of the semi-analytical sensitivity analysis techniques results in significant computational savings. A nonlinear programming technique and an approximate analysis procedure arc used in the optimization. The optimization procedure developed is applied to a doubly swept wing-body configuration. Results obtained show significant improvements in the sonic boom characteristics and the aerodynamic performance.
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UR - http://www.scopus.com/inward/citedby.url?scp=84959228124&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84959228124
SP - 1
EP - 12
BT - 1995 Fluid Dynamics Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
ER -