Shock tunnel measurements of hypervelocity blunted cone drag
Abstract
Presented here are results obtained from an investigation into the effects of nose bluntness on slender cone drag in the hypervelocity flight regime. The results indicate that, for small cone angles, the drag of a blunt cone is reasonably well predicted by the Newtonian sine-square law modified for blunt bodies. This suggests the absence of any real gas effects on the total drag. The effect of nose bluntness at the smaller bluntness ratios is relatively small. This is encouraging for the design of a hypervelocity space plane or a centerbody for an axisymmetric scramjet where a slightly blunted nose is required to reduce stagnation point heating.
- Publication:
-
AIAA Journal
- Pub Date:
- December 1994
- DOI:
- 10.2514/3.12318
- Bibcode:
- 1994AIAAJ..32.2476P
- Keywords:
-
- Aerodynamics;
- Blunt Bodies;
- Drag;
- Enthalpy;
- Hypersonic Flight;
- Nose Cones;
- Shock Tunnels;
- Slender Cones;
- Strain Measurement;
- Aerospace Planes;
- Centerbodies;
- Heating;
- Signal To Noise Ratios;
- Stagnation Point;
- Strain Gages;
- Supersonic Combustion Ramjet Engines;
- Fluid Mechanics and Heat Transfer