Flight Determination of the Longitudinal Stability and Control Characteristics of a 0.125-Scale Rocket-Boosted Model of the Mcdonnell F-101 Airplane at Mach Numbers from 0.82 to 1.84

A flight test has been conducted to determine the longitudinal stability and control characteristics of a 0.125-scale model of the McDonnell F-1OlA airplane for the Mach number range between 0.82 and 1.84. The variation of lift-curve slope with Mach number was gradual with a maximum value of 0.107 occurring at a Mach number of 0.95. The minimum drag coefficient (including base and internal drag) has a value of 0.020 at a Mach number of 0.87. The drag rise begins at a Mach number of 0.90, and at Mach number of 1.10 the minimum drag is 0.070. Above this Mach number there is a gradual increase in minimum drag coefficient to a value of 0.074 when the Mach number is 1.83. The aerodynamic-center location moved from a value of 62 percent mean aerodynamic chord at a Mach number of 0.88 to its most rearward position of 85 percent at a Mach number of 1.40. The all-movable horizontal tail remained an effective control for producing lift and pitching moment with the variation in effectiveness being gradual throughout the Mach number range covered by the test. There were no large or abrupt losses in pitch damping over the Mach number range covered.