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Implicit Upwind Finite-Difference Simulation of Laminar Hypersonic Flow over Flared Cones

  • B. Müller
Part of the Notes on Numerical Fluid Mechanics (NNFM) book series (NNFM, volume 29)

Summary

Axisymmetric laminar hypersonic flow of perfect gas over flared cones is simulated by solving the thin-layer Navier-Stokes equations for the steady state using an implicit upwind scheme based on approximate factorization and the total variation diminishing (TVD) method of Harten and Yee. The algorithm is outlined, and applications are discussed for Mach 25 flow in 77 km altitude over a 30° cone with 20° flare and a 30° cone with convex rear part and a 27° flare.

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References

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    Müller, B.: “Calculation of Laminar Supersonic Flows over Ramps and Cylinder-Flares”, DFVLR-IB 221-88 A 14, 1988.Google Scholar
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Copyright information

© Springer Fachmedien Wiesbaden 1990

Authors and Affiliations

  • B. Müller
    • 1
  1. 1.Institute for Theoretical Fluid MechanicsDLRGöttingenGermany

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