Flight determination of wing and tail loads on a fighter-type airplane by means of strain-gage measurements

William S. Aiken, Jr
naca-tn-1729
Oct 1948


A flight investigation was conducted to determine the contributions of wing, tail, and fuselage to the total airplane lift of a propeller-driven fighter-type airplane. The tests covered a Mach number range from 0.2 to 0.8.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1948/naca-tn-1729.pdf