Publication Date:
2019-06-28
Description:
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.
Keywords:
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Type:
AIAA PAPER 92-4089
,
In: AIAA Biennial Flight Test Conference, 6th, Hilton Head Island, SC, Aug. 24-26, 1992, Technical Papers (A93-11251 01-05); p. 404-414.
Format:
text
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