Abstract
The wave drag of a supersonic aircraft is closely related to its cross section area distribution, and a reasonable cross section area distribution is important to wave drag reduction. This paper presents a study of the fuselage shape parameterization based on the cross section area decomposition using the class-shape-transformation (CST), and proposes an extended far-field composite element (EFCE) wing-body wave drag optimization method, as well as a supersonic wing-body shape optimization case using the EFCE method, which yields a 39% reduction of the wave drag coefficient. It is suggested that the CST parameterization and the corresponding optimization process of the fuselage shape require fewer parameters and less computation cost than the wing; and similar to the area rule shape modification, the EFCE optimization code can automatically lead to a "coke bottle" fuselage shape.
| Original language | English |
|---|---|
| Pages (from-to) | 1036-1045 |
| Number of pages | 10 |
| Journal | Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica |
| Volume | 34 |
| Issue number | 5 |
| DOIs | |
| State | Published - May 2013 |
Keywords
- Class-shape-transformation
- Drag reduction
- Extended far-field composite element
- Parameterization
- Shape optimization
- Shock wave
- Supersonic aircraft