Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.

Heat-transfer and pressure distributions were measured on sharp and blunt 15 degree half-angle cones. The flow was near conical on the windward side of the models up to an angle of attack of about 60 degrees. At angles of attack above 70 degrees the flow departed noticeably from conical characteristics. Heat-transfer and pressure measurements were found to agree satisfactorily with theories of simple application. At large angles of attack the effects of nose bluntness are very small in the region beyond two nose radii from the point of tangency. (Author).