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Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Investigation at a Mach number of 1.53 to determine the effects of cambering and twisting the wing for uniform load at a lift coefficient of 0.25
Testing was performed at Mach number 1.53 with a wing-fuselage combination with a wing with 63 degrees leading-edge sweep, an aspect ratio of 3.46, and a taper ratio of 0.25. The wing had an NACA 64A005 thickness distribution parallel to the plane of symmetry and was cambered and twisted. Results regarding the comparison of lift, drag, and pitching-moment characteristics of WF-63c and WF-63, effects of sweep, and effects of Reynolds number are provided.
Date:
May 6, 1949
Creator:
Madden, Robert T.
System:
The UNT Digital Library
Events of importance for week ending May 4, 1949
This report details events of importance reported by the Hanford Operations Office for the week ending May 4, 1949.
Date:
May 6, 1949
Creator:
Schlemmer, F. C.
System:
The UNT Digital Library
Pressure-Distribution Data for the NACA 64(Sub 1)-012 and 64(Sub 1)A012 Airfoils at High Subsonic Mach Numbers
"Pressure-distribution data of the NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils have been analyzed to determine the effects of increasing the trailing-edge angle from 9 to 14 degrees. The primary effect of increasing the trailing-edge angle was to decrease the loading over the rear portion of the airfoil under lifting conditions. The differences in trailing-edge load increased with Mach number and lift coefficient" (p. 1).
Date:
May 6, 1949
Creator:
Humphreys, Milton D.
System:
The UNT Digital Library