Direct numerical simulation of hypersonic boundary-layer transition over blunt leading edges, Part I: A new numerical method and validation

35th Aerospace Sciences Meeting and Exhibit

Volumn , Issue , 1997, Pages

  Zhong, Xiaolin ^a  

^a UNIVERSITY OF CALIFORNIA   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AEROSPACE ENGINEERING; BOUNDARY LAYERS; CIRCULAR CYLINDERS; DIRECT NUMERICAL SIMULATION; FINITE DIFFERENCE METHOD; HYPERSONIC FLOW; NUMERICAL METHODS; NUMERICAL MODELS; PLASMA SHOCK WAVES; RUNGE KUTTA METHODS;

ACOUSTIC DISTURBANCES; BLUNT LEADING EDGES; DIRECT SIMULATION; HIGH-ORDER FINITE DIFFERENCES; RUNGE-KUTTA SCHEMES; SPATIAL DISCRETIZATIONS; TEMPORAL DISCRETIZATION; UNSTEADY SHOCKS;

HYPERSONIC BOUNDARY LAYERS;

EID: 84983126633     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

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