scholarly journals Wind-tunnel investigations of blunt-body drag reduction using forebody surface roughness

2001 ◽  
Author(s):  
Stephen Whitmore ◽  
Stephanie Sprague ◽  
Jonathan Naughton
Keyword(s):  
Surface Roughness ◽  
Wind Tunnel ◽  
Drag Reduction ◽  
Blunt Body ◽  
Body Drag

Plasma injection for hypersonic blunt-body drag reduction

AIAA Journal ◽  
2002 ◽  
Vol 40 ◽  
pp. 1178-1186 ◽  
Author(s):  
J. S. Shang
Keyword(s):  
Drag Reduction ◽  
Blunt Body ◽  
Body Drag ◽  
Plasma Injection

Drag reduction on a spiked body at hypersonic speed

2010 ◽  
Vol 114 (1152) ◽  
pp. 113-119 ◽  
Author(s):  
G. d’Humières ◽  
J. L. Stollery
Keyword(s):  
Drag Reduction ◽  
Blunt Body ◽  
Force Measurements ◽  
Solid Cone ◽  
Spherical Cap ◽  
Pressure Drag ◽  
Body Drag ◽  
Hypersonic Wind Tunnel ◽  
Hypersonic Speeds ◽  
Good Agreement

AbstractFitting a spike on a blunt body provides a drag reduction at supersonic and hypersonic speeds. In this study, the laminar flow over a spiked, conical body terminated by a spherical cap, inspired by the Apollo re-entry capsule design, was investigated using a hypersonic wind tunnel. Schlieren pictures revealed the absence of flow unsteadiness for the range of spike lengths tested, and force measurements showed a maximum reduction of 77% of the unspiked body drag.A simple theoretical model based on the pressure drag generated by a solid cone showed good agreement with the experimental data. The measured shock stand-off distance agreed well with predictions.

Plasma Injection for Hypersonic Blunt-Body Drag Reduction

AIAA Journal ◽  
2002 ◽  
Vol 40 (6) ◽  
pp. 1178-1186 ◽  
Author(s):  
J. S. Shang
Keyword(s):  
Drag Reduction ◽  
Blunt Body ◽  
Body Drag ◽  
Plasma Injection

scholarly journals Fore-Body Drag Reduction of a Blunt Body in Compressible Thrbulent Boundary Layer.

2002 ◽  
Vol 50 (586) ◽  
pp. 474-476
Author(s):  
Takafumi Yamawaki ◽  
Hideaki Ogawa ◽  
Takeo Okunuki ◽  
Hisao Koyama ◽  
Hiroshi Itoh ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Drag Reduction ◽  
Blunt Body ◽  
Body Drag

Blunt-body wave drag reduction using focused energy deposition

AIAA Journal ◽  
1999 ◽  
Vol 37 ◽  
pp. 460-467 ◽  
Author(s):  
David Riggins ◽  
H. F. Nelson ◽  
Eric Johnson
Keyword(s):  
Drag Reduction ◽  
Energy Deposition ◽  
Blunt Body ◽  
Body Wave ◽  
Wave Drag ◽  
Wave Drag Reduction

Drag reduction of a blunt body through reconfiguration of rear flexible plates

2021 ◽  
Vol 33 (4) ◽  
pp. 045102
Author(s):  
C. García-Baena ◽  
J. I. Jiménez-González ◽  
C. Martínez-Bazán
Keyword(s):  
Drag Reduction ◽  
Blunt Body ◽  
Flexible Plates

A numerical study on the single pulsed energy addition based unsteady wave drag reduction at varied hypersonic flow regimes

2020 ◽  
pp. 095441002097313
Author(s):  
Dathi SNV Rajasekhar Rao ◽  
Bibin John
Keyword(s):  
Steady State ◽  
Mach Number ◽  
Drag Reduction ◽  
Shock Layer ◽  
Blunt Body ◽  
Wave Drag ◽  
Flow Features ◽  
Energy Pulse ◽  
Energy Addition ◽  
Wave Drag Reduction

In this study, unsteady wave drag reduction in hypersonic flowfield using pulsed energy addition is numerically investigated. A single energy pulse is considered to analyze the time-averaged drag reduction/pulse. The blast wave creation, translation and its interaction with shock layer are studied. As the wave drag depends only on the inviscid aspects of the flowfield, Euler part of a well-established compressible flow Navier-Stokes solver USHAS (Unstructured Solver for Hypersonic Aerothermodynamics) is employed for the present study. To explore the feasibility of pulsed energy addition in reducing the wave drag at different flight conditions, flight Mach numbers of 5.75, 6.9 and 8.0 are chosen for the study. An [Formula: see text] apex angle blunt cone model is considered to be placed in such hypersonic streams, and steady-state drag and unsteady drag reductions are computed. The simulation results indicate that drag of the blunt-body can be reduced below the steady-state drag for a significant period of energy bubble-shock layer interaction, and the corresponding propulsive energy savings can be up to 9%. For energy pulse of magnitude 100mJ deposited to a spherical region of 2 mm radius, located 50 mm upstream of the blunt-body offered a maximum percentage of wave drag reduction in the case of Mach 8.0 flowfield. Two different flow features are found to be responsible for the drag reduction, one is the low-density core of the blast wave and the second one is the baroclinic vortex created due to the plasma energy bubble-shock layer interaction. For the same freestream stagnation conditions, these two flow features are noted to be very predominant in the case of high Mach number flow in comparison to Mach 5.75 and 6.9 cases. However, the ratio of energy saved to the energy consumed is noted as a maximum for the lower Mach number case.

Sign in / Sign up

Export Citation Format

Share Document