Measurements for range of Mach number up to 0.78; results showed that large increase in drag coefficient beyond critical Mach number indicated by wind tunnel tests was also obtained under flight conditions and that wake width was extended sharply when shock was encountered.
Wake measurements behind wing section of fighter airplane in fast dives
Nat Advisory Committee Aeronautics -- Tech Note
1947
8 pages
10 Supp plates
Report
Englisch
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Flight investigation of wing-gun fairings on fighter type airplane
Engineering Index Backfile | 1941
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