Abstract
We present a shape optimization methodology for reducing the initial shock pressure rise (ISPR) on the ground of a supersonic aircraft. This methodology combines elements from the linearized aerodynamic theory such as Whitham's F-function with elements from the nonlinear aerodynamic theory such as the prediction of lift distribution by an Euler or a Navier-Stokes flow solver. We report on the application of this shaping technology to a Point of Departure aircraft developed by Lockheed-Martin for DARPA's Quiet Supersonic Platform program. We demonstrate a ten-fold reduction of the ISPR on the ground, from 1.623 psf at M∞ = 1.5 to 0.152 psf, while maintaining constant lift and wave drag.
Original language | English |
---|---|
DOIs | |
Publication status | Published - 2002 |
Externally published | Yes |
Event | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: 14 Jan 2002 → 17 Jan 2002 |
Conference
Conference | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 |
---|---|
Country/Territory | United States |
City | Reno, NV |
Period | 14/01/02 → 17/01/02 |