The present status of ground test facilities and 
instrumentation for simulation of hypersonic flight, 
propulsion, and atmospheric entry will be reviewed with 
respect to current and proposed international vehicle 
development programs. Particular attention will be given 
to characterization of wind tunnel test conditions and to 
methods for relating ground test conditions to the flight 
application environment, including the use of appropriate 
flight tests. The use of computational fluid dynamic tools 
to identify efficient testing strategies and to extract 
further information from test results will be addressed.