# Download Hypersonic Flows for Reentry Problems: Volume II: Test Cases by Dr. Jean-Antoine Désidéri, Professor Dr. Roland Glowinski, PDF

By Dr. Jean-Antoine Désidéri, Professor Dr. Roland Glowinski, Dr. Jacques Périaux (auth.), Dr. Jean-Antoine Désidéri, Professor Dr. Roland Glowinski, Dr. Jacques Périaux (eds.)

Read or Download Hypersonic Flows for Reentry Problems: Volume II: Test Cases — Experiments and Computations Proceedings of a Workshop Held in Antibes, France, 22–25 January 1990 PDF

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Extra info for Hypersonic Flows for Reentry Problems: Volume II: Test Cases — Experiments and Computations Proceedings of a Workshop Held in Antibes, France, 22–25 January 1990

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1 : Vortex flow • Global values Give the values of CD and C L for all the test cases evaluated in each case by integration of the surface pressure. 1-2 give the values due to the integration of the skin friction . w is the heat flux (positive if directed from the wall to the fluid). - Cross-sectional diagrams of the quantities : Cp , M, 1 - ppo , 1 0 00 £- for Euler 0 00 Cp , Cfy , Sf for Navier Stokes where Cfy = Of . 8 normal to the longitudinal axis of the wing. The root chord of the wing Or is from its apex.

1 to 1 represented by 110 mm. 1 to 1 represented by 110 mm. 1 to 1 represented by 110 mm. 1 to 1 represented by 110 mm. 2 represented by 100 mm. , overall drag, against simulated time and indicate averaging period for the presented mean values of parameters. 5 ---- ---- Physical conditions: For this test case, the flow is a free jet expanding into a plenum chamber. 006m. The starting condition will be given at the exit of the torch. The gas considered is nitrogen. The species which are present are Nt, e, N, N+, N 2 • The pressure is equal to 250 tor into the plenum chamber.

0 represented by 120 mm. • Translational temperature: AT = 2000 K represented by 150 mm. • Internal mode temperature : ~T = 2000 K represented by 150 mm. 5. ii. 05 iii. 1 • Profiles along the plane of symmetry. i. 5 ii. 8 represented by 120 mm iii. Pressure coefficient: 0 to 2 represented by 100 mm iv. Skin friction coefficient: 0 to 2 represented by 100 mm • Skin friction lines on the surface. • Overall forces and heat transfer Tabulated data for : • Lift coefficient. • Overall drag coefficient.