Flow modification cooling technique to reduce aerodynamic wave drag by mechanical cut shape aero-spike for the blunted body at Mach 8.0

The hypervelocity vehicle has a very high speed during flight and during this flight, the vehicle experiences very high wave drag on the body, with the highest pressure in the nose region of the vehicle. Therefore, it becomes necessary to reduce drag for safer and more economical flights. The retrac...

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Bibliographic Details
Main Authors: Kanwar, Shyam Singh, Agrawal, Gajendra Kumar, Patnaik, Avinash Ranjan, Gavel, Satish Kumar
Format: Conference Proceeding
Language:English
Subjects:
Apex angle
Diameters
Drag reduction
Flight
Hypersonic flow
Hypervelocity
Mathematical models
Numerical analysis
Stagnation point
Turbulence models
Two-equation turbulence model
Wave drag
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Summary:The hypervelocity vehicle has a very high speed during flight and during this flight, the vehicle experiences very high wave drag on the body, with the highest pressure in the nose region of the vehicle. Therefore, it becomes necessary to reduce drag for safer and more economical flights. The retractable aero-spike is a simple and effective drag mitigation device, so it becomes imperative to use a suitable spike to increase its effectiveness. In this research, Numerical results on the effect of mechanical cut aero-spike at the stagnation point of a 60° half-angle blunt cone model in a hypersonic flow stream are presented. The commercial code of ANSYS fluent is used for the present numerical investigation. The two-dimensional Reynolds-average Navier-Stokes equation (RANS) was solved numerically using ANSYS Fluent. The k-ω two-equation turbulence model was used in this study. The length of the aerospike is taken by four different lengths to base diameter (L/D) ratios: 0.2, 0.5, 0.7, and 1.0. The numerical investigation discovered a drag reduction is about 20.6% (maximum mitigation) when using cut shape aero-spike in an axisymmetric 600 apex angle blunt cone.
ISSN:0094-243X
1551-7616
DOI:10.1063/5.0177829