Abstract The modification of high-speed flight vehicles by adding a spike attached to the stagnation point yields a complex flow-field full of interesting details. The purpose of this work is to contribute to the following two aspects. First, to analyze the interaction between oblique shock, separation shock and reattachment shock to explain the mechanism of drag reduction caused by the spike. Second, to assess the impact of varying the spike length (L/D = 0.5, 1.0 and 1.5), angle-of-attack (up to 10°) and Mach number (up to 3) on the level of drag reduction. The results reveal that, by comparing with the un-spiked blunt nose, the maximum drag reduction is 42% for L/D = 1.0 at α = 0°. For higher angles-of-attack, the spike is found to have little benefits in reducing the drag. Moreover, the efficiency of the spike in reducing drag and increasing lift depends largely on spike length. However, the spike length does not influence the aerodynamic coefficients when it exceeds the value of the blunt-body diameter ratio (L/D = 1.0).
Highlights Effect of spike lengths, Mach numbers and AoA on drag and flow of a spiked blunt body. The maximum drag reduction at α = 0° is about 60%. Drag decreases with spike length but when length exceeds a value the changes in drag is little. No attachment at non-zero AoA the separated shear layer so a disappearance of reattachment shock.
Evaluation of aerospike for drag reduction on a blunt nose using experimental and numerical modeling
Acta Astronautica ; 160 ; 656-671
2019-03-02
16 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Thermal and structural response of aerospike mounted on blunt-nose body
SAGE Publications | 2021
|Aerospike for Drag Reduction in Hypersonic Flow
AIAA | 2008
|ENGINEERING NOTE - Effectiveness of Aerospike for Drag Reduction on a Blunt Cone in Hypersonic Flow
Online Contents | 2010
|Breathing blunt-nose concept for drag reduction in supersonic flow
Tema Archiv | 2009
|Breathing blunt-nose concept for drag reduction in supersonic flow
SAGE Publications | 2009
|