Free-flight measurements at Mach numbers from 0.7 to 1.6 of some effects of airfoil-thickness distribution and trailing-edge angle on aileron rolling effectiveness and drag for wings with 0 and 45 degrees sweepback

Fields, E. M., Strass, H. Kurt.
naca-rm-l51g27
1951


(abstract not available)

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1951/naca-rm-l51g27.pdf