Strut Support Interference on a Cylindrical Model with Boattail at Mach Numbers from 0.6 to 1.4
Final rept. 1 Jul 1974-30 Jun 1975
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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An investigation was conducted in the Aerodynamic Wind Tunnel 1T, with a sting-mounted, ogive-cylinder model and various dummy strut designs, to provide further information on sources of nozzle afterbody NAB interference and to determine how incremental changes in afterbody boattail and base pressures are affected by changes in support strut design and location. The investigation also included the effect of changing local wall porosity on the NAB interference. An analysis of pressure data obtained on the model, boattail, base, and tunnel wall surfaces at Mach numbers from 0.6 to 1.4 indicates that interference occurs above Mach 0.99 as the result of disturbances generated by the strut leading edge which are reflected from the tunnel wall to the NAB. This interference can be minimized by using a swept strut however, the optimum strut sweep angle and strut location is a function of Mach number and NAB geometry.
- Fluid Mechanics