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In a series of wind tunnel tests, measurements were made of the aerodynamic loads acting on eight different store configurations mounted in the external captive position on a one-twentieth-scale model of the F-4C aircraft. Store models included blunt and contoured afterbody shapes, stable and unstable designs, and large (one per pylon) and small (rack-mounted) configurations. The tests were conducted in an effort to evaluate sting effects on captive store loads. Sting effects were considered to consist of two contributions: the effect of altering the afterbody of a store to allow insertion of a sting, and the effect of the presence of the sting. Altering the afterbody of an unstable store influenced captive loads less than altering a stable configuration. It was also determined that the presence of a sting affected most the pitching and yawing moments.
Wind tunnel tests were conducted to provide support interference information for planning and directing wind tunnel tests at supersonic and hypersonic Mach numbers. Sting-length and sting-diameter effects on base and surface pressures of a blunt 6-deg cone with a sliced base were investigated at Mach numbers 2, 3, 5, and 8. Dynamic stability tests on a blunt 7-deg cone were also conducted at Mach numbers 2, 5, and 8. The objectives of the 7-deg cone tests were to define critical sting lengths as determined by the measurement of dynamic stability derivatives, static pitching moment, and base pressure. Two frequencies of oscillation were investigated, and data were obtained for laminar, transitional, and turbulent boundary-layer conditions at the model base. The data from the 6- and 7-deg cone tests showed that the critical sting length depended on the interference indicator, Mach number, angle of attack, state of the model boundary layer, and frequency of oscillation. The critical sting length was generally less for models with turbulent boundary layers than for those with laminar boundary layers. A critical sting length of 2.5 model diameters was determined to be suitable for all test conditions that produced a turbulent boundary layer at or ahead of the model base.
In a series of wind tunnel tests, measurements were made of the aerodynamic loads acting on eight different store configurations supported in and near the external captive position on a 1/20-scale model of the F-4C aircraft. Store models included blunt and contoured afterbody shapes, stable and unstable configurations, and large (pylon-mounted) and small (rack-mounted) configurations. Six components of forces and moments were measured using two methods of supporting the store models: an internal bracket support technique (IBS), and a dual sting support technique. Some characteristics of the interference flow field of the aircraft were also inferred.
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).