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Unformatted text preview: M 2 = 0 . 7815 . 992 CHAPTER 8. ONEDIMENSIONAL COMPRESSIBLE FLOW Using the isentropicflow tables again to compute the area ratio behind the shock, we find M 2 A 2 /A ∗ 0.7800 1.0471 0.7815 1.0464 0.8000 1.0382 Therefore, the area ratio is A 2 A ∗ = 1 . 0464 Station 3: Finally, from the geometry, the area ratio at Station 3 is A 3 A ∗ = A 3 A 2 A 2 A ∗ = 5 4 (1 . 0464) = 1 . 3080 Using the isentropicflow tables we have A 3 /A ∗ M 3 1.3398 0.500 1.3080 0.517 1.3034 0.520 where we again use linear interpolation to arrive at the results in the central row. Therefore, the Mach number at Station 3 is M 3 . = 0 . 52...
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 Spring '06
 Phares
 Fluid Dynamics, Aerodynamics, area ratio

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