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Advances in Aerodynamics

Table 3 Contributions of the terms in Eq. (10)

From: A decomposition formula for the wall heat flux of a compressible boundary layer

 

Ch,1/Ch,decom

Ch,2/Ch,decom

Ch,3/Ch,decom

Ch,4/Ch,decom

Ch,5/Ch,decom

Ch,6/Ch,decom

Ch,7/Ch,decom

Ch,0

Ch,decom

Err

P1

−0.111

−1.379

0.018

−0.084

0.478

2.437

−0.359

1.195E-4

1.183E-4

1.00%

P2

−0.213

−0.785

0.012

−0.072

0.673

1.299

0.086

1.825E-4

1.819E-4

0.33%

P3

−0.208

− 0.713

0.015

− 0.054

0.662

1.200

0.098

1.616E-4

1.620E-4

0.25%

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