Wind tunnel force tests in wing systems through large angles of attack

Carl J. Wenzinger, Thomas A. Harris
naca-tn-294
Aug 1928


Force tests on a systematic series of wing systems over a range of angle of attack from minus forty-five degrees to plus ninety degrees are covered in this report. The investigation was made on monoplane and biplane wing models to determine the effects of variations of tip shape, aspect ratio, flap setting, stagger, gap, decalage, sweepback, and airfoil profile.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1928/naca-tn-294.pdf