INSTRUMENTATION AND CALIBRATION OF UTIAS 11 IN. X 15 IN. HYPERSONIC SHOCK TUNNEL.
TORONTO UNIV (ONTARIO) INST FOR AEROSPACE STUDIES
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An outline of the problems encountered in the calibration of the UTIAS 11 in. x 15 in. Hypersonic Shock Tunnel and some of the solutions are presented. An impulsively heated tungsten-wire technique was successfully developed to obtain detonation-free, smooth, and very repeatable combustion by burning stoichiometric mixtures of oxygen and hydrogen, diluted with helium. It was found that tailored shock Mach numbers as high as M sub s 9.5 were achieved. A test section flow calibration was done by measuring wall static pressures, pitot pressures and stagnation point heat-transfer rates. Qualitative pressure-time histories of static and pitot pressures obtained from theoretical considerations were used to interpret the experimental data as well as the nozzle starting time and testing times. Schlieren pictures of the flows over a flat plate and a right circular cylinder are also presented. Methods of predicting the test-section flow quantities in the different flow regimes are indicated. Nozzle starting processes are explained by utilizing available theories. The reservoir and test section conditions were usually P sub o -- 30 atmospheres to 90 atmospheres T sub o -- 3000K to 4500K sub o 1.00 to 1.35 P sub infinity - 0.003 to 0.02 psi, P sub x - 0.1 to 0.8 psi, M sub infinity 8.0 to 13.8, Relft 1.5 x 10 to the 4th to 3.82 x 10 to the 3rd based on flow field behind the shock. Author
- Test Facilities, Equipment and Methods
- Fluid Mechanics