Experimental and Numerical Studies to Evaluate Real-Gas Effects on Generic Models in the Free- Piston Shock Tunnel HIEST
Abstract
This is a report of the current status of research on high-enthalpy aerodynamics using the HIEST. Free- flight force measurements have been conducted with accelerometers inside test models suspended by thin wires. Aerodynamic characteristics have been obtained for two generic models (blunted cone of nose radius 20 mm and blunted cylinder with flare) under high-enthalpy hypersonic flow conditions, and the results compared with those from the hypersonic blow-down wind tunnel in JAXA-HWT2. Numerical simulations have also been performed with an axis-symmetric and with a three- dimensional Navier-Stokes code. The blunted cylinder displayed axial force coefficients 5% higher than in the hypersonic wind tunnel. Three-component measurement has been carried out on the blunted cone, which displayed axial and normal force coefficients 9.6% and 10.9% higher than predicted by numerical simulation, while the pitching moment coefficient was 4.4% lower.
- Publication:
-
6th European Symposium on Aerothermodynamics for Space Vehicles
- Pub Date:
- January 2009
- Bibcode:
- 2009ESASP.659E.120T