Results presented of drag tests of six bodies of revolution with systematically varying shapes and with fineness ratio of 5; forms were derived from source-sink distributions and formulas presented for calculation of pressure distributions of forms; tests made in NACA variable density wind tunnel.
Fuselage-drag tests in variable-density wind tunnel: streamline bodies of revolution, fineness ratio of 5
Nat Advisory Committee Aeronautics -- Tech Note
1937
11 pages
5 Supp sheets, Bibliography
Report
Englisch
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Engineering Index Backfile | 1934
|Emerald Group Publishing | 1934
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