A revisit to supersonic-flow theory in the early fifties

1988 ◽  
Author(s):  
H. CHENG
Keyword(s):  
Supersonic Flow ◽  
Flow Theory

Base Pressure Measurements on Elliptic Cones in Supersonic Flow

1967 ◽  
Vol 18 (3) ◽  
pp. 298-307 ◽  
Author(s):  
W. Stahl ◽  
H. Grauer-Carstensen
Keyword(s):  
Boundary Layer ◽  
Supersonic Flow ◽  
Reasonable Agreement ◽  
Flow Theory ◽  
Reynolds Numbers ◽  
Base Flow ◽  
Base Pressure ◽  
Pressure Measurements ◽  
Pressure Coefficients ◽  
Mach Numbers

SummaryAt the Aerodynamische Versuchsanstalt Gottingen (AVA), base pressure measurements were made on five elliptic cones. The ratios of the axes of the ellipses were: 1:12, 1:3, 1:1, 3:1, and 12:1. All the cones had the same volume and the same length. The investigations were carried out for Mach numbers M∞=1·50, 1·73, and 1·98 at angles of incidence between about —2 degrees and about 8 degrees. Reynolds numbers, based on a mean length, lm, varied from 2·5×106 to 3·0×106; the boundary layer approaching the base was turbulent. The base pressure coefficients are given as a function of geometry. Some of the results were compared with the base-flow theory of Korst and reasonable agreement was found.

Note on the Wave Drags of Untapered Wings with Streamwise Tips at Zero Lift

1956 ◽  
Vol 7 (3) ◽  
pp. 240-246 ◽  
Author(s):  
A. D. Young
Keyword(s):  
Supersonic Flow ◽  
Simple Proof ◽  
General Theorem ◽  
Flow Theory ◽  
Two Dimensional ◽  
Dimensional Flow ◽  
Two Dimensional Flow ◽  
Swept Wings ◽  
Constant Section

SummaryDetailed calculations based on linearised supersonic flow theory have demonstrated in a number of cases the equivalence between the wave drags of yawed or swept wings of constant section and zero lift and the corresponding values in two-dimensional flow. These results and others are shown to follow readily from a general theorem for which a simple proof is given. Some interesting deductions are illustrated in Fig. 3.

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