Although computational aerodynamics simulation has been taking more responsibility during recent years, wind tunnel experimentation has continued to play the major role in flight vehicle analysis and design.This role, however, is changing because of the great strides in the capability and confidence in numerical simulations. For a small, well defined, class of supersonic and hypersonic flow problems, high quality numerical solutions are now believed to represent the physics of the problem more accurately than a wind tunnel experimental can simulate the free flight conditions. An example of this is the supersonic or hypersonic, laminar, perfect gas flow over a spherically blunted cone at low angle of attack. In this paper, aerodynamic force and moment measurements and flow visualization results are presented for a reentry vehicle configuration at Mach 8. All of the results were obtained in the Sandia Mach 8 long duration, blow-down, hypersonic wind tunnel. The basic vehicle configuration is a spherically blunted cone with a slice parallel with the axis of the vehicle. Onto the slice portion of the vehicle can be attached flaps with three different deflection angles, 10, 20 and 30 deg. Flow visualization results include surface oil flow, spark Schlieren, and liquid crystal photographs. 1 ref., 7 figs. (ERA citation 16:000952)
Joint computational/experimental aerodynamics research on a reentry vehicle. Part 1, Experimental results
1990
20 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Aerodynamics , Fluid Mechanics , Reentry Vehicles , Flow Visualization , Hypersonic Flow , Computer Calculations , Computerized Simulation , Experimental Data , Flow Models , Fluid Flow , Navier-Stokes Equations , Numerical Solution , S Codes , Supersonic Flow , Wind Tunnels , Meetings , Tables(data) , EDB/420400 , EDB/990200