The slender elliptic cone as a model for non-linear supersonic flow theory

1956 ◽  
Vol 1 (01) ◽  
pp. 1 ◽  
Author(s):  
M. D. Van Dyke
1995 ◽  
Vol 30 (2) ◽  
pp. 149-167 ◽  
Author(s):  
Naresh K. Chandiramani ◽  
Raymond H. Plaut ◽  
Liviu I. Librescu

1969 ◽  
Vol 20 (4) ◽  
pp. 382-404 ◽  
Author(s):  
B. A. Woods

SummaryThe supersonic flow past an elliptic cone of small eccentricity is treated as a pertubation of the axially-symmetric conical flow. The perturbation is singular; a uniformly valid solution is constructed by formulating the problem in sphero-conal coordinates (in which the cone surface is always a level surface of one of the coordinates) and by using the method of matched asymptotic expansions. This formulation enables first-order results to be obtained economically. In a numerical example for the flow past a cone of quite large eccentricity at incidence, it is shown that the present first-order solution (of three terms) agrees as well with experiment as a ten-term approximation obtained by Martellucci using the method of linearised characteristics.


1967 ◽  
Vol 18 (3) ◽  
pp. 298-307 ◽  
Author(s):  
W. Stahl ◽  
H. Grauer-Carstensen

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.


1956 ◽  
Vol 7 (3) ◽  
pp. 240-246 ◽  
Author(s):  
A. D. Young

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.


1967 ◽  
Vol 28 ◽  
pp. 105-176
Author(s):  
Robert F. Christy

(Ed. note: The custom in these Symposia has been to have a summary-introductory presentation which lasts about 1 to 1.5 hours, during which discussion from the floor is minor and usually directed at technical clarification. The remainder of the session is then devoted to discussion of the whole subject, oriented around the summary-introduction. The preceding session, I-A, at Nice, followed this pattern. Christy suggested that we might experiment in his presentation with a much more informal approach, allowing considerable discussion of the points raised in the summary-introduction during its presentation, with perhaps the entire morning spent in this way, reserving the afternoon session for discussion only. At Varenna, in the Fourth Symposium, several of the summaryintroductory papers presented from the astronomical viewpoint had been so full of concepts unfamiliar to a number of the aerodynamicists-physicists present, that a major part of the following discussion session had been devoted to simply clarifying concepts and then repeating a considerable amount of what had been summarized. So, always looking for alternatives which help to increase the understanding between the different disciplines by introducing clarification of concept as expeditiously as possible, we tried Christy's suggestion. Thus you will find the pattern of the following different from that in session I-A. I am much indebted to Christy for extensive collaboration in editing the resulting combined presentation and discussion. As always, however, I have taken upon myself the responsibility for the final editing, and so all shortcomings are on my head.)


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