Abstract
Considering the shape character of some hypervelocity space debris, the pressure coefficient was calculated using linearity theory by simplifying the hypervelocity space debris to be the sweepback wing, and integraling along the subarea. The calculating formulas of the thickness wave drag coefficient for the leading edge sweepback, trailing edge sweepback and flat trailing edge of the supersonic leading edge or subsonic leading edge were given, and the relationship between the thickness wave drag coefficient and coming flux Mach number was demonstrated.
| Original language | English |
|---|---|
| Pages (from-to) | 76-80 |
| Number of pages | 5 |
| Journal | Harbin Gongye Daxue Xuebao/Journal of Harbin Institute of Technology |
| Volume | 38 |
| Issue number | 1 |
| State | Published - Jan 2006 |
Keywords
- Mach number
- Sweepback space debris
- Thickness wave drag coefficient
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