The Flow over a Flat Plate with a Small Angle of Attack at Mach Number 1

1954 ◽  
Vol 21 (4) ◽  
pp. 261-274 ◽  
Author(s):  
GOTTFRIED GUDERLEY
Keyword(s):  
Mach Number ◽  
Flat Plate ◽  
Small Angle ◽  
Angle Of Attack

scholarly journals An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2

2018 ◽  
Author(s):  
N. V. Semionov ◽  
Yu. G. Yermolaev ◽  
V. L. Kocharin ◽  
A. D. Kosinov ◽  
A. N. Semenov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Small Angle ◽  
Angle Of Attack ◽  
Swept Wing

scholarly journals The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2

2017 ◽  
Author(s):  
N. V. Semionov ◽  
Yu. G. Yermolaev ◽  
A. D. Kosinov ◽  
A. N. Semenov ◽  
B. V. Smorodsky ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Small Angle ◽  
Angle Of Attack ◽  
Swept Wing ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

Unsteady Lift for Impulsively Started Transonic/Supersonic Flow

2015 ◽  
Author(s):  
Chen-Yuan Bai ◽  
Juan Li ◽  
Zi-Niu Wu
Keyword(s):  
Mach Number ◽  
Small Angle ◽  
Angle Of Attack ◽  
Phase Variation ◽  
Leading Edge ◽  
High Angle ◽  
Leading Edge Vortex ◽  
Three Phase ◽  
Edge Vortex ◽  
Starting Flow

The unsteady lift for incompressible starting flow of a flat plate at high angle of attack involves a repeatable three-phase variation: (a) initial lift drop, (b) a Wagner type lift increase enhanced by leading edge vortex and (c) a lift drop due to a lift-decreasing trailing edge vortex spiral induced by the leading edge vortex convected to the trailing edge. For compressible starting flow at small angle of attack, it is well known that the lift experiences an initial drop due to piston effect and then a Wagner type lift increase enhanced by compressibility. The third phase has not been reported in the past. In this paper we consider subsonic, transonic and supersonic starting flow at high angle of attack. Numerical computation using computational fluid dynamics is used to compute the flow and lift behavior is explained using existing theories. It is found that, when the angle of attack is 20 degrees, we still observe the three-phase lift variation for Mach number below 0.8. The second conclusion is that the lift during the Wagner type increase phase is a decreasing function of the Mach number, in contrast to what we know from piston and indicial function method for small angle of attack. Another important conclusion is, when the Mach number is high enough, say above 0.9, only two-phase variation is observed: (a) initial lift drop and (b) Wagner type lift increase. For supersonic starting flow the Wagner type lift increase is replaced by a linear increase.

Relations of Lift and Drag Coefficients of Flow around Flat Plate

2014 ◽  
Vol 518 ◽  
pp. 161-164 ◽  
Author(s):  
Hai Bo Jiang ◽  
Yan Ru Li ◽  
Zhong Qing Cheng
Keyword(s):  
Flat Plate ◽  
Small Angle ◽  
Total Pressure ◽  
Angle Of Attack ◽  
Vertical Component ◽  
Horizontal Component ◽  
High Angle ◽  
High Angle Of Attack ◽  
Drag Coefficients ◽  
Lift And Drag

In this paper, when Reynolds number is within the range of 10000 to 1000000, the horizontal component of the total pressure of flow around flat plate at high angle of attack was regarded as lift of high angle of attack, and the vertical component was regarded as drag of high angle of attack. The horizontal component of total pressure at small angle of attack was regarded as shape drag, and the total drag coefficient at small angle of attack was considered to the sum of the shape drag and frictional drag at zero angle of attack. For the two states of large and small angle of attack, the application scopes of the formulas of lift and drag coefficients were given. Final, the relations of lift and drag coefficients were obtained by eliminating all angles of attack. Research results show that lift - drag curve of small angles of attack is parabola, and the lift - drag curve of high angles of attack is circle.

Rarefied gas flow past a flat plate at zero angle of attack

2020 ◽  
Vol 32 (8) ◽  
pp. 087108
Author(s):  
A. A. Abramov ◽  
A. V. Butkovskii ◽  
O. G. Buzykin
Keyword(s):  
Flat Plate ◽  
Gas Flow ◽  
Rarefied Gas ◽  
Angle Of Attack ◽  
Rarefied Gas Flow ◽  
Flow Past
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