Computations of the Shock Waves at Hypersonic Velocities Taken into Account the Chemical Reactions that Appear in the Air at High Temperatures

INCAS Bulletin

Mihai Leonida NICULESCU¹  Marius Gabriel COJOCARU²  Dumitru PEPELEA³  Mihai Victor PRICOP⁴ 

[1] INCAS − National Institute for Aerospace Research “Elie Carafoli”, Flow Physics Department, Numerical Simulation Unit, B-dul Iuliu Maniu 220, Bucharest 061126, Romania [e-mail]*;INCAS − National Institute for Aerospace Research “Elie Carafoli”, Flow Physics Department, Numerical Simulation Unit, B-dul Iuliu Maniu 220, Bucharest 061126, Romania, [e-mail];INCAS − National Institute for Aerospace Research “Elie Carafoli”, Flow Physics Department, Numerical Simulation Unit, B-dul Iuliu Maniu 220, Bucharest 061126, Romania, [e-mail];INCAS − National Institute for Aerospace Research “Elie Carafoli”, Flow Physics Department, Numerical Simulation Unit, B-dul Iuliu Maniu 220, Bucharest 061126, Romania, [e-mail];

关键词: Hypersonic flow;    shock waves;    chemical reactions;    CFD;    capsule reentry;   

DOI  :  10.13111/2066-8201.2015.7.3.12

来源: DOAJ

【 摘 要 】

The temperature in the nose region of a hypersonic vehicle can be extremely high, for example, reaching approximately 11 000 K at a Mach number of 36 (Apollo reentry). The bow shock wave is normal, or nearly normal, in the nose region of a blunt body, and the gas temperature behind this shock wave can be enormous at hypersonic speeds. In this case, the assumption of a calorically perfect nonreacting gas with the ratio of specific heats  of 1.4 gives an unrealistically high value of temperature. Therefore, the proper inclusion of chemically reacting effects is vital to the calculation of an accurate normal shock wave temperature.

【 授权许可】

Unknown