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Comparison of wind tunnel data obtained in the NLR subsonic transonic pressure wind tunnel and the Langley 8-foot transonic pressure tunnel

K.J. Geraedts

Abstract

This report contains a comparison of the results from tests on two configurations of a v/STOL aeroplane model at Mach numbers between 0.6 and 1.2 in +he NLR subsonic transonic pressure wind tunnel at Amsterdam and the NASA 8-foot transonio pressure tunnel at langley Field. The correlation between the results obtained in the two tunnels is quite satisfactory.

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Available abstract

Key concepts: Transonic, Subsonic and transonic wind tunnel, Wind tunnel, Hypersonic wind tunnel, Mach number, Supersonic wind tunnel, Pressure measurement, Marine engineering