A comparison of the chordwise pressure distribution and spanwise distribution of loading at subsonic speeds on two triangular wings of aspect ratio 2 having NACA 0005 and 0008 sections

Donald W. Smith, Verlin D. Reed
May 1952

Measurements of the distribution of surface pressures were made on two wing-body combinations employing a triangular wing having an aspect ratio ratio of 2. The first of these combinations had a wing with the NACA 0008-63 section parallel to the air stream while the wing of the second had the NACA 0005-63 section in the stream direction. The measurements were made for Mach numbers from 0.11 to 0.95 at a constant Reynolds number of 3.0 million. Data were also obtained for Reynolds numbers up to 15.0 million at the lower Mach number. A summary of data obtained from previously published force tests of these same models is also included for completeness of the presentation of the effect of wing thickness.

An Adobe Acrobat (PDF) file of the entire report: