The use of splitter plates for two dimensional transonic testing in wind tunnels was investigated on a 12% biconvex airfoil section over the Mach number range 0.6 to 1.0. Measured pressure distributions were compared to transonic theory and to other experiments, including an investigation in the same facility without splitter plates. The results of the experiment show the best agreement with theory over the entire transonic Mach number range.
Two-dimensional transonic testing with splitter plates
1978-02-01
Report
No indication
English
Two-dimensional transonic testing with splitter plates
TIBKAT | 1978
|Two-Dimensional Transonic Testing with Splitter Plates
NTIS | 1978
|Freestream Velocity Corrections for Two-Dimensional Testing with Splitter Plates
Online Contents | 1997
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