Chordwise Pressure Distributions on a 12-foot-span Wing of NACA 66-series Airfoil Sections up to a Mach Number of 0.60
01.10.1948
Sonstige
Keine Angabe
Englisch
Engineering Index Backfile | 1948
|Engineering Index Backfile | 1949
|Engineering Index Backfile | 1959
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