2-dimensional wind tunnel investigation conducted in Langley airfoil test apparatus; tests ranged in Reynolds number from 2.4 × 106 to 2.8 × 106 and in angle of attack from -- 10 to 12°; chordwise pressure distributions and schlieren flow photographs presented without analysis.
Chordwise pressure distributions over several NACA 16-series airfoils at transonic mach numbers up to 1.25
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 6-1-59L
1959
285 pages
Report
Englisch
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Chordwise Actuation Effects on NACA 0012 Morphing Airfoils (AIAA 2018-3957)
British Library Conference Proceedings | 2018
|Engineering Index Backfile | 1948
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