Super-Alfvénic supersonic flow over a cone in aligned fields

1972 ◽  
Vol 52 (1) ◽  
pp. 17-31 ◽  
Author(s):  
Lee A. Bertram ◽  
Y. M. Lynn
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Flow Field ◽  
Surface Pressure ◽  
Magnetic Induction ◽  
Closed Form Solution ◽  
Form Solution ◽  
Apex Angle ◽  
Induction Vector ◽  
Pressure Coefficients

Super-Alfvénic supersonic aligned magnetogasdynamic flow over a cone of finite semi-apex angle, with an attached fast shock wave, is solved numerically. We obtain ‘almond curves’ in the plane of magnetic induction vector variation, analogous to Busemann's ‘apple curves’ for supersonic cone flows, to describe the flow field near the cone. Total surface pressure coefficients, current and vorticity distributions are presented. A closed-form solution of the flow is obtained when a switch-on shock occurs.

Simple Formulae for Supersonic Flow past a Cone

1975 ◽  
Vol 26 (1) ◽  
pp. 11-19 ◽  
Author(s):  
W H Hui
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Supersonic Flow ◽  
Surface Pressure ◽  
Simple Formula ◽  
Pressure Coefficient ◽  
Circular Cone ◽  
Number Range ◽  
Thin Shock Layer ◽  
Cone Vertex

SummaryThe problem of the supersonic flow with attached shock wave past a circular cone at zero angles of attack is treated, using the thin-shock-layer expansion. The solution is calculated to the fourth approximation. A simple formula is then derived for the surface pressure coefficient by the application of the parameter-straining technique and it is shown to be very accurate for the whole Mach number range for which the shock remains attached to the cone vertex.

scholarly journals Experimental Study on Ramp Shock Wave Control in Ma3 Supersonic Flow Using Two-Electrode SparkJet Actuator

Processes ◽  
2020 ◽  
Vol 8 (12) ◽  
pp. 1679
Author(s):  
Wei Xie ◽  
Zhenbing Luo ◽  
Yan Zhou ◽  
Lin Wang ◽  
Wenqiang Peng ◽  
...  
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Flow Field ◽  
Pressure Measurement ◽  
Separation Zone ◽  
Dynamic Pressure ◽  
Base Flow ◽  
Control Effect ◽  
Dynamic Pressure Measurement ◽  
Wave Control

The control of a shock wave produced by a ramp (ramp shock) in Ma3 supersonic flow using a two-electrode SparkJet (SPJ) actuator in a single-pulse mode is studied experimentally. Except for schlieren images of the interaction process of SPJ with the flow field, a dynamic pressure measurement method is also used in the analysis of shock wave control. In a typical experimental case, under the control of single-pulsed SPJ, the characteristic of ramp shock changes from “short-term local upstream motion” in the initial stage to “long-term whole downstream motion” in the later stage. The angle and position of the ramp shock changes significantly in the whole control process. In addition, the dynamic pressure measurement result shows that the ramp pressure is reduced by a maximum of 79% compared to that in the base flow field, which indicates that the ramp shock is significantly weakened by SPJ. The effects of some parameters on the control effect of SPJ on the ramp shock are investigated and analyzed in detail. The increase in discharge capacitance helps to improve the control effect of SPJ on the ramp shock. However, the control effect of the SPJ actuator with medium exit diameter is better than that with a too small or too large one. In addition, when the SPJ exit is located in the separation zone and outside, the change in the ramp shock shows significant differences, but the control effect in the case of medium ramp distance is better when the SPJ exit is located outside the separation zone.

Aerodynamics of Airfoils with Porous Trailing Edges

1979 ◽  
Vol 30 (2) ◽  
pp. 387-399 ◽  
Author(s):  
C. Samuel Ventres ◽  
Richard Barakat
Keyword(s):  
Supersonic Flow ◽  
Complex Variable ◽  
Closed Form Solution ◽  
Form Solution ◽  
Pressure Loading ◽  
Trailing Edge ◽  
Variable Theory ◽  
Complex Variable Theory ◽  
Trailing Edges ◽  
Special Case

SummaryThe aerodynamics of a thin airfoil of arbitrary camber having a porous trailing edge in steady, subsonic, compressible potential flow is investigated. In the special case of a flat plate airfoil with a porous trailing edge, an exact, closed form solution is obtained using complex variable theory. The pressure loading on the airfoil, the lift and pitching moments are exhibited explicitly along with typical numerical results. The corresponding situation in supersonic flow is also considered.

Seismic passive earth pressure coefficients using the method of characteristics

2002 ◽  
Vol 39 (2) ◽  
pp. 463-471 ◽  
Author(s):  
Jyant Kumar ◽  
Sridhar Chitikela
Keyword(s):  
Method Of Characteristics ◽  
Closed Form Solution ◽  
Earth Pressure ◽  
Retaining Walls ◽  
Form Solution ◽  
Unit Weight ◽  
Passive Earth Pressure ◽  
Pressure Coefficients ◽  
The Method Of Characteristics ◽  
Earth Pressures

The method of characteristics was used to generate passive earth pressure coefficients for an inclined wall retaining cohesionless backfill material in the presence of pseudostatic horizontal earthquake body forces. The variation of the passive earth pressure coefficients Kpq and Kpγ with changes in horizontal earthquake acceleration coefficient due to the components of soil unit weight and surcharge pressure, respectively, has been obtained; a closed-form solution for Kpq is also provided. The passive earth resistance has been found to decrease sharply with an increase in the magnitude of horizontal earthquake acceleration. The computed passive earth pressure coefficients were found to be the lowest when compared to all of the previous solutions available in the literature.Key words: earth pressures, earthquakes, method of characteristics, retaining walls, sands.

Manipulating Flow to Reduce Drag of a Square Cylinder by Using a Self-Sustained Vibrating Rod

2011 ◽  
Vol 133 (5) ◽  
Author(s):  
Rong Fung Huang ◽  
Jeng Cha Cheng ◽  
Jia-Kun Chen ◽  
Ching Min Hsu
Keyword(s):  
Flow Field ◽  
Surface Pressure ◽  
Vortex Shedding ◽  
Incidence Angle ◽  
Leading Edge ◽  
Lateral Face ◽  
Natural State ◽  
Cylinder Surface ◽  
Square Cylinder ◽  
Pressure Coefficients

The flow, vortex shedding, and surface pressure of a square cylinder at incidence were manipulated by means of a self-sustained vibrating rod placed around the leading edge of the upwind-facing lateral face of the square cylinder. The flow patterns on the cylinder surface were studied by using the surface-oil flow method for a Reynolds number between 4.5 × 104 and 1.1 × 105 as the incidence angle varied from 0° to 45°. Vortex-shedding characteristics were measured by means of a single-component hot-wire anemometer, and surface-pressure distributions were detected by using a linear-pressure scanner. The results show that owing to the influence of the rod vibration, the flow pattern on the agitated face changed from its natural state of a dual-ring bubble to the mode of boundary-layer separation. The critical incidence angle separating the dual-ring bubble and single-ring bubble modes was advanced to 11° from its natural state of 15°. The locations of the characteristic points on the cylinder surface were altered by the rod vibration, implying that the whole flow field surrounding the square cylinder was modified by the vibrating rod installed around the leading edge of the upwind-facing lateral face. The Strouhal numbers of wake instability of the controlled and uncontrolled cylinders did not present significant difference. The variations of the pressure coefficients induced by the rod vibration were closely related with the modification of the flow field on the cylinder surface. The decreases in the pressure coefficients on the upwind-facing faces and on the leeward-facing faces lead to drag reduction of the controlled cylinder by ∼25% when compared with the uncontrolled cylinder.

Sign in / Sign up

Export Citation Format

Share Document