High pressure hypervelocity electrothermal wind tunnel performance study and subscale testsThe feasibility of a Mach 10 to 20, high pressure electrothermal wind tunnel was assessed. A heater based on a continuous high power electric arc discharge capable of heating air to temperatures above 10,000 K and pressures of 15,000 atm is the key element of this wind tunnel. Results of analytical study indicate that the facility is capable of simulation conditions suitable for hypervelocity airbreathing propulsion testing up to Mach 16. In this case simulation was limited by pressure containment, high nozzle throat heat flux rates, and chemical freezing in the nozzle. The high total pressure capability improved the recombination chemistry in the facility nozzle as chemical equilibrium prevailed to the freezing point. Steady arc discharges were observed with liquid nitrogen flowing into the arc chamber during tests based on the two millisecond test facility. The measured steady pressure in the arc chamber was 4559 psi, which is two times greater than maximum total pressure obtainable in conventional arc heaters.
Document ID
19920043152
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rizkalla, Oussama F. (NASA Langley Research Center Hampton, VA, United States)
Chinitz, Wallace (General Applied Science Laboratories Ronkonkoma, NY, United States)
Witherspoon, F. D. (GT-Devices, Inc. Alexandria, VA, United States)
Burton, Rodney L. (Illinois, University Urbana, United States)