Drag Reduction by Laser-Plasma Energy Addition in Hypersonic Flow

2008 ◽  
Author(s):  
A. C. Oliveira ◽  
M. A. S. Minucci ◽  
P. G. P. Toro ◽  
J. B. Chanes ◽  
L. N. Myrabo ◽  
...  
Keyword(s):  
Drag Reduction ◽  
Hypersonic Flow ◽  
Laser Plasma ◽  
Plasma Energy ◽  
Energy Addition

Bow Shock Wave Mitigation by Laser-Plasma Energy Addition in Hypersonic Flow

2008 ◽  
Vol 45 (5) ◽  
pp. 921-927 ◽  
Author(s):  
A. C. Oliveira ◽  
M. A. S. Minucci ◽  
P. G. P. Toro ◽  
J. B. Chanes ◽  
L. N. Myrabo ◽  
...  
Keyword(s):  
Shock Wave ◽  
Hypersonic Flow ◽  
Laser Plasma ◽  
Bow Shock ◽  
Plasma Energy ◽  
Bow Shock Wave ◽  
Energy Addition ◽  
Shock Wave Mitigation

Numerical Study on Process of Drag Reduction by Laser Plasma in Supersonic Vehicle

2013 ◽  
Vol 631-632 ◽  
pp. 1011-1016
Author(s):  
Qian Li ◽  
Zhun Liu ◽  
Yan Ji Hong ◽  
Dian Kai Wang
Keyword(s):  
Shock Wave ◽  
Drag Reduction ◽  
Laser Plasma ◽  
Mechanical Model ◽  
Numerical Study ◽  
Bow Shock ◽  
Plasma Energy ◽  
Bow Shock Wave ◽  
Fluid Field ◽  
Computational Code

Interaction between laser plasma and bow shock wave in front of supersonic vehicle is analysized. Physical and mechanical model of laser plasma energy being deposited in supersonic fluid field is established and computational code is programmed. Process of drag reduction by laser plasma in supersonic vehicle is simulated numerically, and the mechanism of laser plasma reducing drag is disclosed. Simulated results are compared with relative references’, which agree well with each other. It is illuminated that drag reduction by laser plasma can be studied by the established model and code.

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.

Effectiveness of Aerospike for Drag Reduction on a Blunt Cone in Hypersonic Flow

2010 ◽  
Vol 47 (3) ◽  
pp. 542-544 ◽  
Author(s):  
Vinayak Kulkarni ◽  
Viren Menezes ◽  
K. P. J. Reddy
Keyword(s):  
Drag Reduction ◽  
Hypersonic Flow ◽  
Blunt Cone

Numerical Simulation on Air Mass Capture Control of Hypersonic Inlet by Laser Energy

2014 ◽  
Vol 644-650 ◽  
pp. 1470-1473 ◽  
Author(s):  
Qian Li ◽  
Yan Ji Hong ◽  
Wei Zhao ◽  
Dian Kai Wang
Keyword(s):  
Hypersonic Flow ◽  
Laser Power ◽  
Laser Energy ◽  
Air Mass ◽  
Capture Ratio ◽  
Princeton University ◽  
Hypersonic Inlet ◽  
Mass Capture ◽  
Energy Addition ◽  
Numerical Program

Mechanism of hypersonic inlet performance promoting by “virtual cowl” induced by laser energy is introduced, and the physical model of interaction between laser energy and shocks in hypersonic flow field is established. Through comparing results in this paper with the work performed by Macheret et al.(Princeton University) and analyzing effects of laser energy deposited in hypersonic flow, numerical program and the feasibility of model are validated. At Mach 6, with no laser energy addition, air mass capture ratioKmis 71.87% in this paper, whileKmis 73.17% in the reference. Energy addition module can simulate the formation of shocks induced by laser energy, and the interaction process between laser energy and compression ramp shocks properly. Curves of mass capture ratioKmagrees well with that of the reference.Kmis a little higher than data in the reference, but the variable trend is consistent with each other when laser power is 1kW. When laser power is 0.5kW,Kmvaries a little, and the peak value is 77.36%, which only increases 7.64%, while the value is 7.28% in the reference.

Mechanism study on drag reduction and thermal protection for the porous opposing jet in hypersonic flow

2020 ◽  
Vol 103 ◽  
pp. 105933
Author(s):  
Shi-bin Li ◽  
Tao-tao Zhang ◽  
Chao Ou ◽  
Wei Huang ◽  
Jian Chen
Keyword(s):  
Drag Reduction ◽  
Hypersonic Flow ◽  
Thermal Protection ◽  
Mechanism Study
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