Flight data collected on a wing glove testbed are very sensitive to flight conditions (e.g., Mach number, Reynolds number, aircraft weight). Previous laminar flow control flight research has typically been narrowly focused on single point designs such as the cruise condition. The objectives for the present experiment are to collect these data across a range of flight conditions and provide stabilized flow data suitable for computational validation. To accomplish this, a flight test technique was developed to set and hold the angle of attack of a wing glove. This is accomplished via lateral-directional flight control inputs which are not susceptible to pilot-induced oscillations like pitch inputs. When applied to laminar flow control, this flight test technique is shown to be able to reasonably hold angle of attack to ±0.1°. Further, a combination of flight control inputs can compensate for asymmetric wing glove installation and position flight control surfaces for optimal data collection and comparison to computational models. Finally, a research pilot display was developed to display flow conditions at the wing glove and enable efficient flight data collection. Nomenclature α = aircraft angle of attack α test = aircraft angle of attack specified for flight data collection α tol = aircraft angle of attack tolerance β = aircraft angle of sideslip AIAA SciTech 2 = isentropic expansion factor Γ = wing geometric dihedral δ a = aileron displacement δ a, left = left aileron displacement, positive trailing edge down δ a, right = right aileron displacement, positive trailing edge up δ a, trim = aileron displacement required to null the lateral rates of the aircraft δ r = rudder displacement, positive trailing edge right δ r, trim = rudder displacement required to null the directional rates of the aircraft ΔΦ = change in bank angle ΔL = change in aircraft lift = aircraft glide angle Θ = aircraft pitch angle Λ = wing leading edge sweep referenced to aircraft longitudinal axis Λ eff = wing effective leading edge sweep referenced to freestream velocity μ = viscosity of air = density of air = aircraft bank angle limit = aircraft bank angle limit test = aircraft test bank angle a = speed of sound b = aircraft wingspan B = 10 9 c = chord length C L = wing lift coefficient C l β = rolling moment coefficient with respect to angle of sideslip C L α = wing lift coefficient with respect to angle of attack C L 0 = wing lift coefficient at zero angle of attack ft MSL = feet above mean sea level Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org | 3 h = aircraft altitude KIAS = knots indicated airspeed L = aircraft lift M = Mach number p = atmospheric pressure R = specific gas constant for air Re c = Reynolds number, chord reference length S = aircraft wing area T = temperature U ∞ = freestream velocity U n = component of X-direction freestream velocity normal to the wing leading edge U p = component of X-direction freestream velocity parallel to the wing leading edge V = component of free stream...