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Tests were conducted in the Aerodynamic Wind Tunnel (4T) to evaluate the validity of weapon aerodynamics acquired from theoretical calculations which employed mathematical models to simulate actual test hardware and to assess the problems encountered during the separation of various weapon shapes, at transonic flight conditions, from the number one TER position. The data will also be used to aid in the development of a mathematical method for predicting store separation characteristics. Data were obtained at Mach numbers from 0.5 to 1.3. Force and pressure distribution measurements were obtained to assess the influence of angle of attack and both linear and angular store displacements from the carriage position. Store models were separated from a TER mounted on the inboard pylon of a half-span wing similar in planform to the wing of the F-4 aircraft. Data were obtained on 0.10-scale models of the M-117 and maximum volume bombs. Test results showed that large nose-down pitching-moment coefficients were encountered by all store models at the number one TER carriage position. Complete separation trajectories were obtained only at a Mach number of 0.5 for all 16-in.-diam store models. Decreasing store model diameter increased the maximum Mach number at which complete trajectories were obtained. (Author).
Tests were conducted in the Aerodynamic Wind Tunnel (4T) to evaluate the validity of weapon aerodynamics acquired from theoretical calculations which employed mathematical models to simulate actual test hardware and to assess the problems encountered during the separation of various weapon shapes, at transonic flight conditions, from the number one TER position. The data will also be used to aid in the development of a mathematical method for predicting store separation characteristics. Data were obtained at Mach numbers from 0.5 to 1.3. Force and pressure distribution measurements were obtained to assess the influence of angle of attack and both linear and angular store displacements from the carriage position. Store models were separated from a TER mounted on the inboard pylon of a half-span wing similar in planform to the wing of the F-4 aircraft. Data were obtained on 0.10-scale models of the M-117 and maximum volume bombs. Test results showed that large nose-down pitching-moment coefficients were encountered by all store models at the number one TER carriage position. Complete separation trajectories were obtained only at a Mach number of 0.5 for all 16-in.-diam store models. Decreasing store model diameter increased the maximum Mach number at which complete trajectories were obtained. (Author).
An experimental program was conducted to parametrically study the interference on an afterbody model that would be produced by the aft-support blade used with a wingtip support system. Geometric variables included the blade axial location, thickness, span, chord, and leading- and trailing-edge contours. Data were obtained over the Mach number range from 0.6 to 1.2 with the model at zero angle of attack. Interference was evaluated by comparing afterbody drag from a reference configuration, which had the aft-support blade removed, to the various configurations with a blade installed. A reasonable correlation of the blade interference effects on the afterbody drag coefficient was obtained, which included the influence of support blade axial position and blockage. Decreasing blade leading-edge bluntness by a factor of two resulted in a significant reduction of interference in the Mach number range from 0.9 to 1.1. Significantly greater interference was measured without jet flow than with jet flow. It is shown that a Euler equation computer code is a useful tool for the design of minimum interference support systems. (Author).
Aerodynamic characteristics effected by parallel- staged simple aerodynamic configurations at Mach numbers of 3 and 6.