Abstract: Results of numerical investigation of a supersonic flow around sharp circular cones at zero angle of attack are presented. An analysis of total drag constituents of a cone, namely, a wave drag and friction drag depending on the cone semiapex angle is carried out. This analysis proves the presence of the minimum of total drag. Dependences of the cone semiapex angle with minimum drag on the Reynolds number Re are obtained within the range of the Mach numbers of the incident flow M∞ = 3−8.
Publication Year: 2011
Publication Date: 2011-01-01
Language: en
Type: article
Indexed In: ['crossref']
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Cited By Count: 5
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