@article{barbante2012,
	title = {Flight {Extrapolation} of {Plasma} {Wind} {Tunnel} {Stagnation} {Region} {Flowfield}},
	volume = {20},
	url = {https://arc.aiaa.org/doi/10.2514/1.17185},
	doi = {10.2514/1.17185},
	abstract = {Development of reusable space vehicles requires a precise qualification of their thermal protection system materials. The catalytic properties are usually determined in plasma wind tunnels for test conditions relevant to the flight mission program. Therefore, for such a situation, it is important to have a methodology that allows the correct extrapolation of the ground test conditions to the real flight ones and vice-versa. The local heat transfer simulation concept presented in this paper is a possible strategy for accomplishing this task. Computational results show that the ground test conditions are indeed correctly extrapolated to the flight ones and a simple method of accounting for possible discrepancies between the two configurations is presented.},
	number = {3},
	journal = {Journal of Thermophysics and Heat Transfer},
	author = {Barbante, P. F. and Chazot, O.},
	month = may,
	year = {2012},
	note = {Publisher: American Institute of Aeronautics and Astronautics Inc.},
	keywords = {Accurate Computational Fluid Dynamics, Binary Diffusion Coefficient, Boundary Layer Equations, Damköhler Numbers, Freestream Conditions, Heat Transfer, Hypersonic Flows, Shock Layers, Thermal Protection System, Wind Tunnels},
	pages = {493--499},
}

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