High-speed wind-tunnel tests of a one-sixteenth-scale model of the D-558 research airplane : D-588-1 speed-reduction brake and symmetrical-profile wing characteristics

John B. Wright
naca-rm-l8b06
Jun 1948


The present paper contains the results of pitching-moment, lift, and drag measurements with a one-sixteenth-scale of the D-558-1 with speed-reduction brakes and with a wing of symmetrical profile. Tests were conducted through a Mach number range up to 0.96 in the Langley 8-foot high-speed tunnel.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1948/naca-rm-l8b06.pdf