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Eq. (20) is a convenient way to couple the solution of the mixing length to the flowfield. In the wake-law region of the boundary layer, locally defined eddy diffusivity is commonly used. For example, Purchased from American Institute of Aeronautics and Astronautics 34 W. E. NICOLET AND A. BALAKRISHNAN Kendall et al. 018 u e 6^ (21 where oo r I \ " uMdy (22 2 is the incompressible displacement thickness. Moss also employs locally defined eddy viscosities in his calculations of hypervelocity entry flows.

June 4-6, 1979. , 1979. All rights reserved. *Member, Technical Council, Aerospace Systems Division. Presently, president of Thermal Sciences, Inc. tStaff Engineer, Aerospace Systems Division. 26 Purchased from American Institute of Aeronautics and Astronautics PREDICTING OFF-STAGNATION-POINT FLOWFIELDS 5T = normalized turbulent mixing length, £a*/y Le = Lewis Number p = parameter used in evaluating nonsimilar integrals P = pressure P = parameter defined by Eq. (34) Pr = Prandtl Number Prv = turbulent Prandtl Number q^a = diffusive heat flux qf = radiative heat flux r = local body radius in a meridian plane R Re = radius of curvature = Reynolds Number A s = surface parallel coordinate Sc = Schmidt Number, p/yD Sc.

The important physical events encountered during planetary entry are significantly different from those met during Earth reentry. In particular, the shock-layer radiation causes massive ablation from the w a l l , which affects the entire flowfield; the viscous/mixing region assumes the character of a free shear/mixing region instead of a boundary layer. This requires a significantly different modeling approach. Transition and turbulence also are important since they change the character of the mixing layer and, consequently, the radiation flux reaching the wall.

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