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THE PRINCETON UNIVERSITY HIGH PRESSURE HYPERSONIC NITROGEN TUNNEL N-3. PART I. FACILITY DESCRIPTION. PART II. CALCULATION OF GAS CHARACTERISTICS AND EVALUATION OF EFFECTS OF VIBRATIONAL NON-EQUILIBRIUM. PART III. PRELIMINARY MEASUREMENTS,
I. E. Vas, G. Koppenwallner
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Abstract
A hypersonic wind tunnel using nitrogen as the test fluid was built to operate in the continuum and slip flow regimes. The free stream Mach number in the 6-8 inch diameter test section varies from 16-25 with stagnation pressures from 2000-5000 psia and stagnation temperatures to 3000K. The testing time is presently limited to 25 minutes. For the temperatures and pressures encountered, no dissociation effects are experienced but vibrational effects must be included. A freezing criterion was developed and applied to the nozzle configuration. For the operating conditions, it was found that the gas can be considered to be frozen during the entire expansion process. Measurements of wall static pressure and transverse pitot pressure traces were conducted in the test region generated by the conical nozzle. The effect of stagnation pressure on Mach number was found to be important.