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VKI Hypersonic Wind Tunnels and Associated Measurement Techniques.

N9123196

Publication Date	1990
Personal Author	Simeonides, G.
Page Count	177
Abstract	A description of the two hypersonic facilities at the Belgian Von Karman Institute (VKI), providing details of their performance capabilities and operation, as well as measurement techniques currently employed is presented. The two wind tunnels are described with emphasis being placed on the Longshot intermittent tunnel which is capable of Mach/Reynolds number simulation of lifting reentry flight. The analysis of its performance and the efforts undertaken since 1982 to modernize the facility are summarized. Measurement techniques employed in two tunnels, emphasizing the measurement of heat transfer by various intrusive or non intrusive methods, are given. The instrumentation/acquisition systems are discussed together with the accuracy of various measurements, particularly in the Longshot facility.
Keywords	Flow measurement Hypersonic wind tunnels Pressure measurement Temperature measurement Test facilities Wind tunnel tests Computerized simulation Data reduction Flow visualization Heat transfer Mach number Reynolds number Foreign technology
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	51F - Test Facilities & Equipment
Corporate Authors	von Karman Inst. for Fluid Dynamics, Rhode-Saint-Genese (Belgium).; National Aeronautics and Space Administration, Washington, DC.
Document Type	Technical Report
NTIS Issue Number	199119

VKI Hypersonic Wind Tunnels and Associated Measurement Techniques.

VKI Hypersonic Wind Tunnels and Associated Measurement Techniques.
N9123196

Publication Date	1990
Personal Author	Simeonides, G.
Page Count	177
Abstract	A description of the two hypersonic facilities at the Belgian Von Karman Institute (VKI), providing details of their performance capabilities and operation, as well as measurement techniques currently employed is presented. The two wind tunnels are described with emphasis being placed on the Longshot intermittent tunnel which is capable of Mach/Reynolds number simulation of lifting reentry flight. The analysis of its performance and the efforts undertaken since 1982 to modernize the facility are summarized. Measurement techniques employed in two tunnels, emphasizing the measurement of heat transfer by various intrusive or non intrusive methods, are given. The instrumentation/acquisition systems are discussed together with the accuracy of various measurements, particularly in the Longshot facility.
Keywords	Flow measurement Hypersonic wind tunnels Pressure measurement Temperature measurement Test facilities Wind tunnel tests Computerized simulation Data reduction Flow visualization Heat transfer Mach number Reynolds number Foreign technology
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	51F - Test Facilities & Equipment
Corporate Authors	von Karman Inst. for Fluid Dynamics, Rhode-Saint-Genese (Belgium).; National Aeronautics and Space Administration, Washington, DC.
Document Type	Technical Report
NTIS Issue Number	199119