Transonic flow past on enlarged missile nose parts


Autoria(s): Semyonov, Denis
Data(s)

18/12/2007

18/12/2007

2007

Resumo

Numerical computation of a viscid heat-conducting transonic flow over a generic commercial rocket profile with symmetric oversized nose part was carried out. It has been shown that at zero angle of attack for some free-streamvelocity value flow pattern loses its symmetry. This results in non-uniform pressure distribution on rocket surface in angle direction which may yield in additional oscillating stress on the rocket. Also it has been found that obtained non-symmetric flow patterns are stable for small velocity perturbations.

Identificador

TMP.objres.643.pdf

http://www.doria.fi/handle/10024/29945

URN:NBN:fi-fe20071479

Idioma(s)

en

Palavras-Chave #Transonic flow #CFD #flow instability
Tipo

Diplomityö

Master's thesis