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- W336143911 abstract "A flight test has been conducted to determine the longitudinal stabilityand control characteristics of a 0.125-scale model of the McDonnellF-1OlA airplane for the Mach number range between 0.82 and 1.84.The variation of lift-curve slope with Mach number was gradual witha maximum value of 0.107 occurring at a Mach number of 0.95.The minimum drag coefficient (including base and internal drag) hasa value of 0.020 at a Mach number of 0.87. The drag rise begins at aMach number of 0.90, and at Mach number of 1.10 the minimum drag is0.070. Above this Mach number there is a gradual increase in minimumdrag coefficient to a value of 0.074 when the Mach number is 1.83.The aerodynamic-center location moved from a value of 62 percentmean aerodynamic chord at a Mach number of 0.88 to its most rearwardposition of 85 percent at a Mach number of 1.40.The all-movable horizontal tail remained an effective control forproducing lift and pitching moment with the variation in effectivenessbeing gradual throughout the Mach number range covered by the test. Therewere no large or abrupt losses in pitch damping over the Mach number rangecovered." @default.
- W336143911 created "2016-06-24" @default.
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- W336143911 date "1955-07-05" @default.
- W336143911 modified "2023-09-26" @default.
- W336143911 title "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" @default.
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