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Configuration and Computation Cases
S. Riedelbauch [34] (see also [35]) studied the aerothermodynamic properties of hypersonic flow past the radiation-cooled surface of a generic configuration (Blunt Delta Wing (BDW) [36]). The configuration is a simple slender delta wing with a blunt nose, Fig. 3.15. Navier-Stokes solutions for perfect gas were performed for flight with the conditions given in Table 3.5.
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Table 3.5. Flight parameters of the Blunt Delta Wing [34].
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Laminar flow was assumed. A surface emissivity coefficient є = 0.85 was chosen. The computations were made with an angle of attack a = 15° for two wing lengths L = 14 m and L = 4.67 m.
