The problem of supersonic flow over the lower surface of a triangular wing

1970 ◽  
Vol 1 (6) ◽  
pp. 95-98
Author(s):  
S. M. Ter-Minasyants
Keyword(s):  
Supersonic Flow ◽  
Lower Surface ◽  
Triangular Wing

Supersonic flow over a triangular wing

1985 ◽  
Vol 26 (3) ◽  
pp. 391-396 ◽  
Author(s):  
G. N. Dudin ◽  
I. I. Lipatov
Keyword(s):  
Supersonic Flow ◽  
Triangular Wing

Numerical Investigation of Viscous Laminar Supersonic Flow Past an Asymmetric Biconvex Circular-Arc Aerofoil

2013 ◽  
Vol 390 ◽  
pp. 147-151
Author(s):  
Saif Akram ◽  
Nadeem Hasan ◽  
Aqib Khan
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Supersonic Flow ◽  
Numerical Investigation ◽  
Lower Surface ◽  
Two Dimensional ◽  
Circular Arc ◽  
Flow Past ◽  
Supersonic Regime ◽  
Force Characteristics

A numerical investigation of two-dimensional unsteady, viscous and laminar compressible flow past an asymmetric biconvex circular-arc aerofoil in supersonic regime is carried out. The focus of the present work is to investigate the effects of variation of Mach number, at two different angles of attack, on the flow and force characteristics on NACA 2S-(50)(04)-(50)(20) aerofoil. The value of Reynolds number is taken as 5x105. The computations are carried out at Mach numbers of 1.25, 1.5 and 2.0 at an angle of attack of α=0° and α=10°. It is found that the aerofoil works well in the supersonic flow and, unlike the conventional symmetric biconvex aerofoil, generates finite lift at α=0° due to stronger shock waves at the lower surface. Moreover, the L/D ratio at α=10° is always found to be more than 2.5.

The Caret Wing at Certain Off-Design Conditions

1972 ◽  
Vol 23 (4) ◽  
pp. 263-275 ◽  
Author(s):  
W H Hui
Keyword(s):  
Supersonic Flow ◽  
Central Region ◽  
Cross Flow ◽  
Lower Surface ◽  
Uniform Flow ◽  
Pressure Curve ◽  
Angle Of Incidence ◽  
Internal Shock ◽  
The Cross ◽  
Leading Edges

SummaryA unified theory is given of hypersonic and supersonic flow over the lower surface of a caret wing at certain off-design conditions when the bow shock is attached to the leading edges of the wing and when there exists no internal shock. The flow field on the lower surface of a caret wing consists of uniform flow regions near the leading edges, where the cross-flow is supersonic, and a non-uniform flow in the central region, where the cross-flow is subsonic. The basic assumption is that the flow in the central region differs slightly from the two-dimensional supersonic flow over a flat plate at the same angle of incidence as that of the lower ridge of the wing. Based on this assumption, a first-order perturbation flow is first calculated and then strained and corrected so that it matches the uniform flow which is obtained exactly. Slope discontinuities of the pressure curve are found at the cross-flow sonic line. Numerical examples and comparisons with previous theories and experiments are included.

Supersonic Flow Past a Slender Delta Wing. An Experimental Investigation Covering the Incidence Range –5° ≤ α ≤ 50°

1976 ◽  
Vol 27 (2) ◽  
pp. 143-153 ◽  
Author(s):  
I C Richards
Keyword(s):  
Experimental Investigation ◽  
Supersonic Flow ◽  
Surface Pressure ◽  
Shock Layer ◽  
Delta Wing ◽  
Lower Surface ◽  
Flow Visualisation ◽  
Pressure Distributions ◽  
Thin Shock Layer ◽  
Oil Flow

SummaryA detailed survey of a delta wing of 70° sweep has been performed at M = 2.5. The measurements include upper- and lower-surface pressure distributions, schlieren photographs, vapour-screen photographs and surface oil-flow visualisation. The results have been compared with thin-shock-layer theory and various other predictions.

Normal force of a flat triangular wing in a supersonic flow

1978 ◽  
Vol 12 (3) ◽  
pp. 479-480
Author(s):  
V. I. Lapygin
Keyword(s):  
Supersonic Flow ◽  
Normal Force ◽  
Triangular Wing
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