Effects of Mach Number up to 0.34 and Reynolds Number up to 8 X 10(exp 6) Power on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections
1950-12-01
Miscellaneous
No indication
English
FLAPS, TRAILING EDGE - COMPLETE WINGS , FLOW, VISCOUS , REYNOLDS NUMBER , CHORDWISE , PRESSURE DISTRIBUTION - WINGS , WING FLAPS, SPLIT , SURFACE CONDITIONS - COMPLETE WINGS , LIFT COEFFICIENTS - WINGS , FLOW, SUBSONIC , AIRFOIL SURFACES - ROUGHNESS , MACH NUMBER , WIND TUNNEL TESTS - NACA - PRESSURE (19 FEET) , AIRFOILS - NACA 66(215)-116(A=0 6) - 66(215)-216(A=0 6) , REYNOLDS NUMBER EFFECTS - COMPLETE WINGS
Engineering Index Backfile | 1950
|Engineering Index Backfile | 1947
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