Nose Shape for Minimum Drag in Hypersonic Flow

1962 ◽  
Vol 29 (1) ◽  
pp. 98-99 ◽  
Author(s):  
E. Large
Keyword(s):  
Hypersonic Flow ◽  
Minimum Drag ◽  
Nose Shape

The construction of a nose shape of minimum drag for specified external dimensions and volume using Euler equations

2006 ◽  
Vol 70 (6) ◽  
pp. 912-923 ◽  
Author(s):  
N.L. Yefremov ◽  
A.I. Kraiko ◽  
K.S. P’yankov ◽  
S.A. Takovitskii
Keyword(s):  
Euler Equations ◽  
Minimum Drag ◽  
Nose Shape

Effect of nose shape on hypersonic flow past slender blunt bodies at an angle of attack

1972 ◽  
Vol 4 (3) ◽  
pp. 140-143 ◽  
Author(s):  
B. A. Zemlyanskii ◽  
V. V. Lunev ◽  
K. M. Magomedov
Keyword(s):  
Hypersonic Flow ◽  
Angle Of Attack ◽  
Flow Past ◽  
Blunt Bodies ◽  
Nose Shape

Hypersonic minimum drag forebodies with blunt leading edges

2013 ◽  
Vol 117 (1191) ◽  
pp. 553-557
Author(s):  
J. Pike
Keyword(s):  
Hypersonic Flow ◽  
Axisymmetric Body ◽  
The Body ◽  
Minimum Pressure ◽  
Pressure Drag ◽  
Minimum Drag ◽  
Impact Theory ◽  
Leading Edges

AbstractThe minimum pressure drag of blunt forebodies in hypersonic flow is investigated using Newton’s Impact Theory. It is shown how the minimum drag shape varies with the body slenderness and the amount of blunting. As the blunting increases the drag approaches that of the minimum drag axisymmetric body.

Hypersonic flow past nose cones of different geometries: a comparative study

SIMULATION ◽  
2017 ◽  
Vol 94 (8) ◽  
pp. 665-680 ◽  
Author(s):  
Ashish Narayan ◽  
S Narayanan ◽  
Rakesh Kumar
Keyword(s):  
Comparative Study ◽  
Hypersonic Flow ◽  
Aerodynamic Drag ◽  
Pressure Coefficient ◽  
Detailed Comparison ◽  
Maximum Pressure ◽  
Total Drag ◽  
Minimum Drag ◽  
Flow Past ◽  
Nose Cone

The present work provides a detailed comparative study of the hypersonic flow past spherically blunted and parabolic nose cones at a Mach number of 5.8, numerically. The main focus of the paper is to determine the geometry and parameters of the nose cones that provide minimum aerodynamic drag and heating. Studies on spherically blunted and parabolic nose cones are performed for different fineness ratios at zero angle of attack. It is observed that for fineness ratio <1.2, blunted cones provide minimum drag, whereas at higher values of fineness ratios >1.2, parabolic nose cones provide superior drag reduction. Detailed comparison of the flow/shock features in the vicinity of the blunted and parabolic nose cones for different fineness ratios is also shown in order to determine its influence on aerodynamic drag. An empirical correlation developed for the total drag coefficient based on regression analysis for a parabolic nose cone reveals that it is mainly a function of the maximum pressure coefficient and fineness ratio. In general, the present study reveals that parabolic nose cones at higher fineness ratios are preferred over spherically blunted ones for achieving higher drag reductions and lower heating in hypervelocity vehicles.

Numerical Simulation of the Effect of Porous Cooling of Bodies in Hypersonic Flow

2002 ◽  
Vol 33 (1-2) ◽  
pp. 8
Author(s):  
Alexander I. Leontiev ◽  
V. V. Nosatov ◽  
G. S. Sadovnikov
Keyword(s):  
Numerical Simulation ◽  
Hypersonic Flow

AXISYMMETRIC BODY AT AN ANGLE OF ATTACK IN HYPERSONIC FLOW: HEAT PROBLEM

2015 ◽  
Vol 46 (2) ◽  
pp. 107-121
Author(s):  
Vyacheslav Antonovich Bashkin ◽  
Ivan Vladimirovich Egorov ◽  
Ivan Valeryevich Ezhov
Keyword(s):  
Hypersonic Flow ◽  
Angle Of Attack ◽  
Axisymmetric Body ◽  
Heat Problem ◽  
Flow Heat
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