Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45°


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Abstract: Temperature recovery factors were determined for a slender, thin-walled cone-cylinder, having a 12° vertex angle and a 1.25-inch-diameter cylinder, at Mach numbers from 3.02 to 6.30. The angle-of-attack range was 0° to 45° at Mach numbers up to 3.50, and about 0° to 20° at Mach numbers from 4.23 to 6.30. A transverse cylinder of the same diameter was also tested at Mach number 3.02. Free-stream Reynolds numbers varied from 1.8 to 11.0 million per foot. Flow visualization studies of boundary-layer transition and flow separation were made and the results correlated with recovery-factor measurements.




Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers From 3.0 to 6.3 and Angles of Attack Up to 45°


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Index of NACA Technical Publications


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Experimental Study of the Equivalence of Transonic Flow about Slender Cone-cylinders of Circular and Elliptic Cross Section


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The results of the investigation suggest that at transonic speeds and at small angles of attack the calculation of all aerodynamic characteristics of slender, three-dimensional shapes can be made by use of transonic slender-body theory when the pressures on the equivalent body of revolution are Imown, either by experiment, or by an adequate nonlinear theory. From transonic slender-body theory it is deduced that the slenderness required for this application is the same as that required for the successful application of the transonic area rule.




Meddelanden


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FFA Meddelande


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