Computational and experimental analysis of Mach 2 air flow over a blunt body with plasma aerodynamic actuation

Sun, Qibin; Cheng, Baolei; Li, Yinghong; Kong, WeiSong; Li, Jun; Zhu, Yifei; Jin, Di

doi:10.1007/s11431-013-5177-6

Cited by 15 publications

(7 citation statements)

References 8 publications

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“…There are many methods for producing plasma, such as dielectric barrier discharge [1,[5][6][7][8][9][10][11], spark discharge [1,7,12] and arc discharge [13][14][15]. The plasmaenhanced aerodynamics has been demonstrated in separation control, lift improvement, drag reduction and flight control without moving surfaces.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

Liu

Niu

Wang

et al. 2015

Sci. China Technol. Sci.

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Spark discharge plasma synthetic jets (SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting balance at a 20 m/s wind speed. The aim was to explore the SPJ's effect on airfoil aerodynamic by examining SPJ generators' position along the chordwise and the jet flow direction about the chord. Near the wing leading edge, two SPJ generators raised the stall angle by 2° and increased the maximum lift coefficient by 9%. The drag coefficient was decreased by 33.1%, and the lift-drag ratio was increased by 104.2% at an angle of attack above 16°. The rolling-moment coefficient was modified by 0.002, and the yawing-moment coefficient was changed by 0.0007 at angles of attack in the range of 0°-16°. The results showed that SPJs can control wing aerodynamic forces at a high angle of attack and moments at a low angle of attack. plasma synthetic jet, spark discharge, NACA 0021 airfoil, aerodynamic performance, aerodynamic control Citation: Liu R B, Niu Z G, Wang M M, et al. Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

Liu

Niu

Wang

et al. 2015

Sci. China Technol. Sci.

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“…Plasma actuators have also shown potential in jet mixing [40], lift augmentation of air vehicle wings [32,34], suppressing vortex shedding over blunt bodies [29,37], suppressing endwall secondary flows in compressor cascades [38], reducing noise [11], and heat transfer augmentation [70]. Benard et al [32] presented a parameterisation of the plasma actuator controller, but this discussion is beyond the topic of this review.…”

Section: Refmentioning

confidence: 99%

Flow Control Methods and Their Applicability in Low-Reynolds-Number Centrifugal Compressors—A Review

Tiainen

Grönman

Jaatinen-Värri

et al. 2017

IJTPP

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Abstract:The decrease in the performance of centrifugal compressors operating at low Reynolds numbers (e.g., unmanned aerial vehicles at high altitudes or small turbomachines) can reach 10% due to increased friction. The purposes of this review are to represent the state-of-the-art of the active and passive flow control methods used to improve performance and/or widen the operating range in numerous engineering applications, and to investigate their applicability in low-Reynolds-number centrifugal compressors. The applicable method should increase performance by reducing drag, increasing blade loading, or reducing tip leakage. Based on the aerodynamic and structural demands, passive methods like riblets, squealers, winglets and grooves could be beneficial; however, the drawbacks of these approaches are that their performance depends on the operating conditions and the effect might be negative at higher Reynolds numbers. The flow control method, which would reduce the boundary layer thickness and reduce wake, could have a beneficial impact on the performance of a low-Reynolds-number compressor in the entire operating range, but none of the methods represented in this review fully fulfil this objective.

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“…The results showed that the shock front increased dispersion in its structure and/or the standoff distance from the model when the plasma was generated either off-board or on-board ahead of a model. Computational and experimental studies [18] indicate that an added magnetic field can strengthen the arc plasma to further weaken the shock wave. However, microwave plasma projected on-board was shown still too weak to introduce any visible effect on the shock wave in a hypersonic flow [19].…”

Section: Introductionmentioning

confidence: 99%

Shock Wave Mitigation by Air Plasma Deflector

Kuo¹

2018

AAST

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When the spacecraft flies much faster than the sound speed (~1200 km/h), the airflow disturbances deflected forward from the spacecraft cannot get away from the spacecraft and form a shock wave in front of it. Shock waves have been a detriment for the development of supersonic aircrafts, which have to overcome high wave drag and surface heating from additional friction. Shock wave also produces sonic booms. The noise issue raises environmental concerns, which have precluded routine supersonic flight over land. Therefore, mitigation of shock wave is essential to advance the development of supersonic aircrafts. A plasma mitigation technique is studied. A theory is presented to show that shock wave structure can be modified via flow deflection. Symmetrical deflection evades the need of exchanging the transverse momentum between the flow and the deflector. The analysis shows that the plasma generated in front of the model can effectively deflect the incoming flow. A non-thermal air plasma, generated by on-board 60 Hz periodic electric arc discharge in front of a wind tunnel model, was applied as a plasma deflector for shock wave mitigation technique. The experiment was conducted in a Mach 2.5 wind tunnel. The results show that the air plasma was generated symmetrically in front of the wind tunnel model. With increasing discharge intensity, the plasma deflector transforms the shock from a welldefined attached shock into a highly curved shock structure with increasing standoff distance from the model; this curved shock has increased shock angle and also appears in increasingly diffused form. In the decay of the discharge intensity, the shock front is first transformed back to a well-defined curve shock, which moves downstream to become a perturbed oblique shock; the baseline shock front then reappears as the discharge is reduced to low level again. The experimental observations confirm the theory. The steady of the incoming flow during the discharge cycle is manifested by the repeat of the baseline shock front.

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Computational and experimental analysis of Mach 2 air flow over a blunt body with plasma aerodynamic actuation

Cited by 15 publications

References 8 publications

Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

Flow Control Methods and Their Applicability in Low-Reynolds-Number Centrifugal Compressors—A Review

Shock Wave Mitigation by Air Plasma Deflector

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