For the supersonic laminar flow control research program, tests are being conducted to measure the attachment-line flow characteristics and its location on a highly swept aircraft wing. Subsonic wind tunnel experiments were conducted on 2D models to develop sensors and techniques for the flight application. Representative attachment-line data are discussed and results from the wind tunnel investigation are presented.
Measurement of attachment-line location in a wind-tunnel and in supersonic flight
1992-01-01
Conference paper
No indication
English
The Ames Supersonic Free-flight Wind Tunnel
NTRS | 1952
|Instrumentation of the ames supersonic free-flight wind tunnel
TIBKAT | 1952
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