Longitudinal stability and control characteristics at transonic speeds of a semispan airplane model having a 45 degree sweptback wing and tail as obtained by the transonic-bump method

Leroy Spearmen
naca-rm-l8c11
Jun 1948


An investigation has been made in the Langley high-speed 7- by 10-foot tunnel using the transonic-bump method to determine the longitudinal stability and control characteristics at transonic speed of a semispan airplane model having a 45 degree sweptback wing and tail. The tail was placed directly behind the wing for these tests.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1948/naca-rm-l8c11.pdf