Measurements of forces and wing pressures at Mach numbers 0.70, 0.79 and 0.85, and at Reynolds numbers in the range 1.7 million to 13.6 million, on a half model of a transport-aircraft-type wing-body combination, were analyzed to show the effects of changes of Reynolds number and transition position on the transonic flows over the upper surface of the wing at high incidence. Each of the three Mach numbers provides a different example of flow development and form of scale effect.
An Investigation of Scale Effects on the Transonic Flow over Swept Wings. Part 1: Measurements on a Model of a Transport-Aircraft Configuration
1976
126 pages
Report
Keine Angabe
Englisch
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