Flight Test Results for an Advanced Technology Light Airplane

A single-engine light airplane was modified by the installation of a wing with reduced area, Fowler flaps, Kruger flaps, and spoilers. Flight test results show that zero-lift drag was reduced 13.8 % and a trimmed maximum lift coefficient of 2.73 was achieved. Gust response was significantly reduced and excellent roll control was achieved with spoilers. Several design features employed in the new wings have excellent potential for in-corporation in future light airplanes. Nomenclature A = aspect ratio b = wing span c = mean aerodynamic chord CD = airplane drag coefficient CD() = zero lift drag coefficient GI = rolling moment coefficient C/g = roll power dCf/dds CfS = roll damping coefficient C [ = airplane lift coefficient e = induced drag efficiency factor p = roll rate Sw = wing area THP = thrust horsepower THPe = equivalent thrust horsepower Ve = equivalent velocity VT — true airspeed W — gross weight 0 = sideslip angle df = Fowler flap deflection 5k = Kruger flap deflection ds = spoiler deflection 0 = roll angle Po = standard sea-level density a = density ratio, p/p()