A low speed wind tunnel test was conducted for the 8.9% model of the ALFLEX (Automatic Landing Flight Experiment) vehicle. The objectives of the experiment were: (1) to clarify the effect of the makeshift sting support on the main flow; (2) to measure the forces and moments acting on the model; (3) to measure the hinge moments acting around the axes of control surfaces; (4) to measure the distribution of the static pressure on both sides of the wings; and (5) to observe the situation of the flow passing by the model. The data obtained in this wind tunnel test are utilized in the design of the ALFLEX vehicle. They are essential for designing the aerodynamic model of the vehicle, for determination of the necessary ability of the actuators which operate the control surfaces, for confirmation of the size and configuration of the speed brakes, and so on. The visualization of the separated flow at the rear part of the model was, along with the surveillance of the boundary layer transition by the hot films, helpful to understand the actual flow behavior of the model.
Low Speed Wind Tunnel Test for 8.9% Model of HOPE ALFLEX Vehicle
1993
26 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Aerodynamics , Wind tunnel tests , Low speed wind tunnels , Wind tunnel models , Subsonic flow , Aerodynamic configurations , Flow visualization , Pressure distribution , Boundary layer transition , Static pressure , Foreign technology , HOPE ALFLEX vehicle
Suspending wind-tunnel test for the ALFLEX vehicle
TIBKAT | 1996
British Library Conference Proceedings | 1998
|British Library Conference Proceedings | 1998
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