Author: R. L. Palko Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 68
Book Description
Results are presented for tests conducted on a 1.5 elliptic cone to determine the pressure distribution, flow streamlines, and shock wave shape at high angles of attack. The tests were performed at a Mach number of 10 and a freestream unit Reynolds number of 1.6 x 10 to the 6th power per foot. The angle-of-attack range was from 0 to 60 deg. The model was oriented both with the major and the minor axis of the ellipse located in the pitch plane.
Author: Robert H. Feldhuhn Publisher: ISBN: Category : Cone Languages : en Pages : 106
Book Description
An experimental investigation of the flow field associated with a highly yawed cone was conducted at a Mach number of 5 and a free-stream Reynolds number per foot of 4,400,000. Surface static pressure measurements, flow-field surveys and schlieren photographs were obtained on a sharp five-degree semi-vertex angle cone at an angle of attack of 24 degrees. The results of the measurements indicate that the flow field on the leeward side of a highly yawed cone is very similar to that of a circular cylinder in supersonic cross flow. The essential difference between these two flow fields is the presence of a disturbance from the tip of the cone which separates the gas which has passed through the shock wave on the windward side from the flow which has passed through the weaker portion of the shock wave on the leeward side of the cone. (Author).
Author: Otto Walchner Publisher: ISBN: Category : Languages : en Pages : 46
Book Description
The pressure distribution over a 10 deg cone was measured in ARL's 20-inch hypersonic wind tunnel at Mach-14 and for various angles of attack and sideslip. The effect of different unsymmetrically blunted noses, with small bluntness ratios, on the pressure distribution is investigated. Test results relate any small unsymmetrical nose bluntness to the rotational symmetry of the flow over a body of revolution at high Mach numbers. The reported test complement, AD-711 921. (Author).
Author: R. L. Palko
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Author: Defense Documentation Center (U.S.)
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Author: Robert H. Feldhuhn
Author: George E. Kaattari
Author: National Research Council Canada
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Author: Otto Walchner