WALL PRESSURE MEASUREMENTS ON A ROCKET SLED SLIPPER AT M LESS THAN 1.7.
AIR FORCE MISSILE DEVELOPMENT CENTER HOLLOMAN AFB N MEX DIRECTORATE OF TEST TRACK
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The results of an experimental study to measure aerodynamic pressures in the vicinity of and within a rocket sled slipper are presented and discussed. The main objective was to develop techniques and experimental experience in support of future work to measure wall pressures on rocket-sled slippers up to Mach 5. Four pressure orifices were installed on the rocket-sled and slipper surfaces. One of them was located two inches upstream of the slipper, another on the slipper leading edge and two inside the slipper-gap. The test conditions ranged from Mach numbers zero to 1.74. The maximum Reynolds number was 1.0 x 10 to the 7th power per foot. The measured upstream-pressure and the measured slipper leading-edge pressure behaved similar to wall pressures for flow over a surface with an upstream facing step. Maximum measured pressures upstream of the slipper and on the slipper leading edge occurred at Mach number 1.0 and were respectively 18.6 psia and 20.7 psia. The maximum measured slipper-gap pressure was 21.6 psia and occurred at the maximum Mach number of 1.74. Author
- Test Facilities, Equipment and Methods
- Fluid Mechanics