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2011•TsAGI science journalRequires access

DRAG OF CONE NOSES IN A SUPERSONIC FLOW

В. В. Коваленко, T. Yu. Mel’nichuk, А. Н. Кравцов

Open publisher page 5 citations

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.

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What this paper is about

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.

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Available 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.

Key concepts: Drag divergence Mach number, Drag, Wave drag, Parasitic drag, Drag coefficient, Mechanics, Reynolds number, Supersonic speed

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