Unified unsteady supersonic/hypersonic theory of flow past double wedge airfoils

1983 ◽  
Vol 34 (4) ◽  
pp. 458-488 ◽  
Author(s):  
W. H. Hui
Keyword(s):  
Double Wedge ◽  
Theory Of Flow ◽  
Flow Past

Schwarz-Christoffel Theory of Flow Past an Opening

1982 ◽  
Vol 108 (2) ◽  
pp. 399-418
Author(s):  
Cheng-lung Chen ◽  
Ming-Yang Su
Keyword(s):  
Theory Of Flow ◽  
Flow Past

Symmetrical flow past a double wedge at high subsonic Mach numbers

1978 ◽  
Vol 86 (1) ◽  
pp. 161-177 ◽  
Author(s):  
Jean-Jacques Chattot
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Analytic Solution ◽  
Physical Plane ◽  
Double Wedge ◽  
Sonic Line ◽  
Equations Of Mixed Type ◽  
Flow Past ◽  
Half Angle ◽  
Hodograph Plane

Symmetrical flow past a double wedge is studied for a high subsonic Mach number. The main features of the flow field are discussed in the physical and the hodograph plane. It is shown how a regular solution to the hodograph equation exhibits limit lines in the physical plane, which are eliminated through a ‘cut’ corresponding to the shock wave. In the case of the wedge it is assumed that the shock which is likely to be the most stable is the weakest possible.The boundary-value problem is solved in the hodograph plane using Telenin's method, which has proved to be successful when dealing with equations of mixed type. The bounded analytic solution which is thus constructed is regular in the hodograph plane but presents three folds in the physical plane.The computation is carried out for flow past a 4·5° half-angle wedge at a Mach numberM∞= 0·89. These figures are chosen so that the problem may be justifiably treated by potential theory, the entropy gradient behind the shock being negligible. In this case the mapping of the solution into the physical plane gives the pressure distribution along the double wedge, the sonic line and the shock wave. Of particular interest is the point where the sonic line meets the shock. This configuration is in agreement with the hypothesis of Nocilla, according to which the shock terminates in the supersonic domain. Experimental evidence cannot be obtained, however, because of the lack of resolution in this region.

Two-velocity theory of flow past slender profile

1972 ◽  
Vol 10 (4) ◽  
pp. 547-550 ◽  
Author(s):  
Kh. A. Rakhmatulin ◽  
N. A. Mamadaliev
Keyword(s):  
Theory Of Flow ◽  
Flow Past ◽  
Slender Profile

Experimental Investigation of Supersonic Flow Past Double-Wedge Configurations

AIAA Journal ◽  
1975 ◽  
Vol 13 (7) ◽  
pp. 897-901 ◽  
Author(s):  
John J. Bertin ◽  
John C. Hinkle
Keyword(s):  
Experimental Investigation ◽  
Supersonic Flow ◽  
Double Wedge ◽  
Flow Past
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