Calculation of the aerodynamic characteristics of a wing moving with subsonic velocity under a slight effect of a shock wave

1978 ◽  
Vol 12 (4) ◽  
pp. 607-611
Author(s):  
N. A. Gritsenko ◽  
M. I. Nisht
Keyword(s):  
Shock Wave ◽  
Aerodynamic Characteristics ◽  
Slight Effect ◽  
Subsonic Velocity

Effect of Shock Wave Behavior on Unsteady Aerodynamic Characteristics of Oscillating Transonic Compressor Cascade

2021 ◽  
Author(s):  
Jiuliang Gan ◽  
Toshinori Watanabe ◽  
Takehiro Himeno
Keyword(s):  
Shock Wave ◽  
Aerodynamic Force ◽  
Aerodynamic Characteristics ◽  
Fast Response ◽  
Influence Coefficient ◽  
Compressor Cascade ◽  
Blade Vibration ◽  
Unsteady Pressure ◽  
Transonic Compressor ◽  
Unsteady Aerodynamic

Abstract The unsteady behavior of the shock wave was studied in an oscillating transonic compressor cascade. The experimental measurement and corresponding numerical simulation were conducted on the cascade with different shock patterns based on influence coefficient method. The unsteady pressure distribution on blade surface was measured with fast-response pressure-sensitive paint (PSP) to capture the unsteady aerodynamic force as well as the shock wave movement. It was found that the movement of shock waves in the neighboring flow passages of the oscillating blade was almost anti-phase between the two shock patterns, namely, the double shocks pattern and the merged shock pattern. It was also found that the amplitude of the unsteady pressure caused by the passage shock wave was very large under the merged shock pattern compared with the double shocks pattern. The stability of blade vibration was also analyzed for both shock patterns including 3-D flow effect. These findings were thought to shed light on the fundamental understanding of the unsteady aerodynamic characteristics of oscillating cascade caused by the shock wave behavior.

Flight Development of the Avro CF-100 Mark 5 Aircraft

1958 ◽  
Vol 62 (566) ◽  
pp. 118-122 ◽  
Author(s):  
D. C. Whittley
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Aspect Ratio ◽  
Aerodynamic Characteristics ◽  
Vortex Generators ◽  
High Altitudes ◽  
Trailing Edge ◽  
Flap Deflection ◽  
Performance Gains

SummaryImprovements made to the aerodynamic characteristics of the wing of the Avro CF-100 Mark 5 aircraft are discussed. Modifications to the wing included increase in aspect ratio, addition of vortex generators, and deflection of trailing edge plain flaps. The effect of flap deflection and addition of vortex generators on the aerodynamic characteristics of the wing are shown to be closely associated with interaction of the upper surface shock wave with the boundary layer. Performance gains were demonstrated at high subsonic speeds at high altitudes. Vortex generators improved the buffet boundary, whereas flap deflection both increased aircraft ceiling and improved buffet boundary.

Reynolds Number Effect Investigation of Shock Wave on Supercritical Airfoil

2014 ◽  
Vol 548-549 ◽  
pp. 520-524
Author(s):  
Xin Xu ◽  
Da Wei Liu ◽  
De Hua Chen ◽  
Yuan Jing Wang
Keyword(s):  
Shock Wave ◽  
Reynolds Number ◽  
Stokes Equations ◽  
Boundary Layer Separation ◽  
Aerodynamic Characteristics ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Supercritical Airfoil ◽  
Reynolds Number Effects ◽  
Shock Location

The supercritical airfoil has been widely applied to large airplanes for sake of high aerodynamic efficiency. But at transonic speeds, the shock wave on upper surface of supercritical airfoil may induce boundary layer separation, which would change the aerodynamic characteristics. The shock characteristics such as location and intensity are sensitive to Reynolds number. In order to predict aerodynamic characteristics of supercritical airfoil exactly, the Reynolds number effects of shock wave must be investigated.The transonic flows over a typical supercritical airfoil CH were numerically simulated with two-dimensional Navier-Stokes equations, and the numerical method was validated with test results in ETW(European Transonic Windtunnel). The computation attack angles of CH airfoil varied from 0oto 8o, Mach numbers varied from 0.74 to 0.82 while Reynolds numbers varied from 3×106 to 50×106 per airfoil chord. It is obvious that shock location moves afterward and shock intensity strengthens as Reynolds number increasing. The similar curves of shock location and intensity is linear with logarithm of Reynolds number, so that the shock location and intensity at flight condition could be extrapolated from low Reynolds number.

Effect of Shock Wave Behavior On Unsteady Aerodynamic Characteristics of Oscillating Transonic Compressor Cascade

2021 ◽  
Author(s):  
Jiuliang Gan ◽  
Toshinori Watanabe ◽  
Takehiro Himeno
Keyword(s):  
Shock Wave ◽  
Aerodynamic Force ◽  
Aerodynamic Characteristics ◽  
Fast Response ◽  
Influence Coefficient ◽  
Compressor Cascade ◽  
Blade Vibration ◽  
Unsteady Pressure ◽  
Transonic Compressor ◽  
Unsteady Aerodynamic

Abstract The unsteady behavior of the shock wave was studied in an oscillating transonic compressor cascade. The experimental measurement and corresponding numerical simulation were conducted on the cascade with different shock patterns based on influence coefficient method. The unsteady pressure distribution on blade surface was measured with fast-response pressuresensitive paint (PSP) to capture the unsteady aerodynamic force as well as the shock wave movement. It was found that the movement of shock waves in the neighboring flow passages of the oscillating blade was almost anti-phase between the two shock patterns, namely, the double shocks pattern and the merged shock pattern. It was also found that the amplitude of the unsteady pressure caused by the passage shock wave was very large under the merged shock pattern compared with the double shocks pattern. The stability of blade vibration was also analyzed for both shock patterns including 3-D flow effect. These findings were thought to shed light on the fundamental understanding of the unsteady aerodynamic characteristics of oscillating cascade caused by the shock wave behavior.

Compressible Flow Simulations Over Basic Reusable Rocket Configurations

2003 ◽  
Author(s):  
Keiichiro Fujimoto ◽  
Kozo Fujii
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Compressible Flow ◽  
Simulation Method ◽  
Aerodynamic Characteristics ◽  
Pressure Level ◽  
The Body ◽  
Navier Stokes ◽  
Aerodynamic Coefficients ◽  
Flow Simulations

Compressible flow around the basic reusable rocket configurations are numerically simulated by Navier-Stokes computations. The study started with the simulations of Apollo configuration to validate the simulation method by the comparison of the aerodynamic data with NASA’s experiments, and the capability of CFD estimation are discussed. Computed aerodynamic coefficients for the Apollo agreed well with the experiments at subsonic to supersonic flow regime for whole angle of attack range. Then, the effects of the configuration parameters on the aerodynamic characteristics are numerically investigated and clarified in detail. It turns out that the aerodynamic characteristicsismainlyinfluenced by the separating position of the flow, shock wave on the surface and the pressure level behind the body. Large shoulder radius causes the strong Mach number dependency of the aerodynamic characteristics, and large fineness ratio strongly influences to the (CL)max.

Effects of Surface Waviness on the Interaction of Oblique Shock Wave With Turbulent Boundary Layer

2017 ◽  
Vol 140 (4) ◽  
Author(s):  
Md. Saddam Hossain Joy ◽  
Saeedur Rahman ◽  
A. B. M. Toufique Hasan
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Turbulent Boundary Layer ◽  
Flat Plate ◽  
Three Dimensional ◽  
Aerodynamic Characteristics ◽  
Oblique Shock ◽  
Wavy Surface ◽  
Oblique Shock Wave ◽  
Surface Waviness

Present investigation deals with the interaction of an incident oblique shock wave on a turbulent boundary layer over a wavy surface. The oblique shock wave was generated by an 8 deg wedge in a freestream Mach number of 2.0. Three-dimensional (3D) Reynolds-averaged Navier–Stokes (RANS) equations with k–ω shear stress transport (SST) turbulence model were used for numerical computation. The computed results are in good agreement with the experimental measurement and direct numerical simulation (DNS) data in case of the interaction of an oblique shock with plain flat plate. To identify the effect of surface waviness on shock wave/turbulent boundary layer interaction (SWBLI), a section of the flat plate was replaced by a wavy surface. Computations have been conducted for different magnitudes of wavy amplitude. Further, the wavelength of the wavy surface has been varied. Results showed that the presence of wavy surface induces supplementary shock and expansion waves in the flow field, which are referred as topographic waves. This supplementary system of waves interacts with the counterpart of intrinsic SWBLI in a complex manner. Flow structure, separation behavior, and aerodynamic characteristics are studied. It is revealed that the amplitude is dominant than the wavelength of waviness in case of SWBLI on a wavy surface.

A Numerical Study of the Airfoil Aerodynamic Characteristics with Porous Surface

2014 ◽  
Vol 978 ◽  
pp. 123-130
Author(s):  
Xiao Jun Xiang ◽  
Jun Li Yang
Keyword(s):  
Shock Wave ◽  
Flow Control ◽  
Flow Separation ◽  
Numerical Study ◽  
Aerodynamic Characteristics ◽  
Porous Surface ◽  
Effective Control ◽  
Passive Flow Control ◽  
Naca0012 Airfoil ◽  
Passive Flow

Numerical simulations have been done to investigate the effect of passive flow control on the flow separation and the strength of the shock wave of the NACA0012 airfoil with two types of the porous surface. It has also been discussed that which region the porous surface applied to will make better effect on the flow control. The results show that the B type of the porous surface, which has empty bottom, has effective control on the flow separation if applied to the region near behind the separation point, while the A type of the porous surface is useless. And both A and B porous surface have effect on the decreasing of the strength of the normal shock wave strength when the porosities have been applied to the region across the shock wave. And compared with A type porous surface, the effect of the control is better if B type porous surface is applied. The result has been concluded that the aerodynamic characteristics of the airfoil can be improved with B type of the porous surface. And the B type is worth to be used.

Sign in / Sign up

Export Citation Format

Share Document