The fixed-base flight simulator at the University of Kansas Flight Research Laboratory was used to evaluate wing spoilers for longitudinal flight path control on a modified Cessna 177B aircraft. More than 100 simulated ILS approaches were flown by evaluation pilots using both conventional methods and spoiler controls. Three different spoiler control methods were evaluated. Spoilers provided precise glide path control with constant airspeed and attitude. Control is most effective when the steady-state trimmed airplane CL remains independent of spoiler position.Nomenclature ASEL = airplane, single engine, land CL = airplane lift coefficient C m = pitching moment coefficient Ah = altitude perturbation ILS = instrument landing system M § s = pitch acceleration due to spoiler deflection on one side n = load factor rms = root mean square AV = airspeed perturbation a -angle of attack Aa = angle of attack perturbation d s = symmetrical spoiler deflection A6 = pitch angle perturbation
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