Transonic flow past on enlarged missile nose parts
Data(s) |
18/12/2007
18/12/2007
2007
|
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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 |