A modeling approach for electron transpiration cooling of high-enthalpy flight is evaluated through comparison to a set of experiments performed in a plasma arc tunnel for air and argon. The comparisons include air and argon flow at high enthalpies (27.9 and , respectively), with a Mach number of 2.5 to 3. The conversion of the reported enthalpies and Mach numbers to freestream temperatures and velocities is discussed. The numerical approach is described, including implementation of a thermionic emission boundary condition and an electric field model. Also described is the implementation of a finite-rate chemistry model for argon ionization. Materials with different electron emission properties are also investigated, including graphite and tungsten. The comparisons include two different geometries with different leading-edge radii. The numerical results produce a wide range of emitted current due to the uncertainties in freestream conditions and emissive material properties, but they still agree well with the experimental measurements.
Evaluation of Computational Modeling of Electron Transpiration Cooling at High Enthalpies
Journal of Thermophysics and Heat Transfer ; 31 , 2 ; 283-293
2017-04-01
Conference paper , Article (Journal)
Electronic Resource
English
Computational Analysis of Electron Transpiration Cooling for Hypersonic Vehicles (AIAA 2017-0900)
British Library Conference Proceedings | 2017
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