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Experimental Investigation Of Temperature Recovery Factors On A 10 Degree Cone At Angle Of Attack At A Mach Number Of 312
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Book Synopsis Experimental Investigation of Temperature Recovery Factors on a 10 [degrees] Cone at Angle of Attack at a Mach Number of 3.12 by : John R. Jack
Download or read book Experimental Investigation of Temperature Recovery Factors on a 10 [degrees] Cone at Angle of Attack at a Mach Number of 3.12 written by John R. Jack and published by . This book was released on 1954 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of Temperature Recovery Factors on a 10 Degree Cone at Angle of Attack at a Mach Number of 3.12 by : John R. Jack
Download or read book Experimental Investigation of Temperature Recovery Factors on a 10 Degree Cone at Angle of Attack at a Mach Number of 3.12 written by John R. Jack and published by . This book was released on 1954 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: For the windward surface of the model, local recovery factors in the fully laminar and turbulent regions were not significantly affected by changes in angle of attack. At all angles of attack, increasing the free-stream Reynolds number moved the transition region upstream. For a given angle of attack, the transition region on the leeward surface is substantially upstream of that on the windward surface.
Book Synopsis 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° by : John O. Reller
Download or read book 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° written by John O. Reller and published by . This book was released on 1955 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis An Experimental Investigation of Boundary-layer Transition on a 10 ̊half-angle Cone at Mach 6.9 by : Michael C. Fischer
Download or read book An Experimental Investigation of Boundary-layer Transition on a 10 ̊half-angle Cone at Mach 6.9 written by Michael C. Fischer and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary layer transition on nose cones at hypersonic speeds.
Book Synopsis Experimental Investigation of the Turbulent-boundary-layer Temperature-recovery Factor on Bodies of Revolution at Mach Numbers from 2.0 to 3.8 by : Howard A. Stine
Download or read book Experimental Investigation of the Turbulent-boundary-layer Temperature-recovery Factor on Bodies of Revolution at Mach Numbers from 2.0 to 3.8 written by Howard A. Stine and published by . This book was released on 1952 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: A turbulent-boundary-layer temperature recovery factor f 0.885 plus or minus 0.011 was measured on both a 10 degree cone and a 40 degree cone cylinder at Mach numbers from 2 to 3.8 and Reynolds numbers based on surface kinematic viscosity from 400,000 to 4,000,000. Comparisons are made with available theories and experiments.
Book Synopsis Experimental Determination of the Recovery Factor and Analytical Solution of the Conical Flow Field for a 20 ̊included Angle Cone at Mach Numbers of 4.6 and 6.0 and Stagnation Temperatures to 2600 ̊R by : Frank A. Pfyl
Download or read book Experimental Determination of the Recovery Factor and Analytical Solution of the Conical Flow Field for a 20 ̊included Angle Cone at Mach Numbers of 4.6 and 6.0 and Stagnation Temperatures to 2600 ̊R written by Frank A. Pfyl and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95 by : Jerome D. Julius
Download or read book Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95 written by Jerome D. Julius and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Determination of the Recovery Factor and Analytical Solution of the Conical Flow Field for a 20 Deg Included Angle Cone at Mach Numbers of 4.6 and 6.0 and Stagnation Temperatures to 2600 Degree R by :
Download or read book Experimental Determination of the Recovery Factor and Analytical Solution of the Conical Flow Field for a 20 Deg Included Angle Cone at Mach Numbers of 4.6 and 6.0 and Stagnation Temperatures to 2600 Degree R written by and published by . This book was released on 1961 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the Damping in Pitch Characteristics of a Ten Degree Cone by : Alfred Merle Morrison
Download or read book An Investigation of the Damping in Pitch Characteristics of a Ten Degree Cone written by Alfred Merle Morrison and published by . This book was released on 1975 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of one-degree-of-freedom dynamic wind tunnel measurements were made for a standard Supersonic Tunnel Association ten degree cone with varying bluntnesses of .25, .1, .0167, and .07. Variations of the stability coefficients with angle-of-attack, bluntness, Reynolds number, and Mach number are obtained including Mach 18 data points for which no previous data existed. An explanation of reported difference between measured dynamic stability as obtained from ballistic range and wind tunnel techniques is offered. The equations of motion, data reduction techniques and experimental methods are also developed.
Book Synopsis Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90° by : Raul Jorge Conti
Download or read book Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90° written by Raul Jorge Conti and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis An Experimental Investigation of the Near Wake of a Slender Cone at Mach Number by : Robert J. Cresci
Download or read book An Experimental Investigation of the Near Wake of a Slender Cone at Mach Number written by Robert J. Cresci and published by . This book was released on 1965 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: Various experimental data were obtained in the near wake region of a 10 degree angle sharp cone at free stream Mach numbers of 8.0 and 11.8. The Mach 8.0 tests were conducted at free stream Reynolds numbers of 300,000 and 1,700,000 per foot; laminar and turbulent boundary layers were obtained on the cone surface at these respective Reynolds numbers. Data obtained include radial profiles of temperature, pressure, and Mach number at axial locations between one and three base diameters downstream of the model. Heat transfer and pressure distributions on the model base were also obtained. The Mach 11.8 tests were conducted at a free stream Reynolds number of 600,000 per foot and the surface boundary layer for all these tests were laminar. Data obtained include centerline distributions of Mach number, pressure, and temperature for a distance between one and four base diameters downstream of the model. Centerline temperatures were also obtained in the recirculation region for model wall to stagnation temperature ratios of 0.06 and 0.47. In addition, total temperature profiles were obtained downstream of the rear stagnation point. (Author).
Book Synopsis Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 by : Charles R. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 written by Charles R. Rumsey and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Aerodynamic Characteristics of 9 Deg Half-angle Cones with Varying Degrees of Bluntness at Mach Number 9 by : PHILCO NEWPORT BEACH CALIF AERONUTRONIC DIV.
Download or read book Experimental Investigation of the Aerodynamic Characteristics of 9 Deg Half-angle Cones with Varying Degrees of Bluntness at Mach Number 9 written by PHILCO NEWPORT BEACH CALIF AERONUTRONIC DIV. and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel test was conducted in a 21 in. hypersonic facility to obtain force and moment data on right circular cones of varying degrees of bluntness. Normal forces, axial forces, and pitching moments were measured over an angle of attack range of -10 to +15 degrees, at Mach numbers of 7.25 and 9.00, and a Reynolds number range of 0.037 to 0.150 x 10 to the 6th power/in. Three 9-degree half-angle cones with ratios of nose tip radius to base radius of 0.03, 0.187, and 0.30 were tested. The experimental data was compared with theoretical data, and the two were in good agreement. (Author).
Book Synopsis Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration by : Charles B. Rumsey
Download or read book Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration written by Charles B. Rumsey and published by . This book was released on 1955 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.
Book Synopsis Free-flight Measurements of the Static and Dynamic Stability and Drag of a 10 Degree Blunted Cone at Mach Numbers 3.5 and 8.5 by : Peter F. Intrieri
Download or read book Free-flight Measurements of the Static and Dynamic Stability and Drag of a 10 Degree Blunted Cone at Mach Numbers 3.5 and 8.5 written by Peter F. Intrieri and published by . This book was released on 1962 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 by : Charles B. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 written by Charles B. Rumsey and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.
Book Synopsis A Method for Predicting Pressures on Elliptic Cones at Supersonic Speeds by : George E. Kaattari
Download or read book A Method for Predicting Pressures on Elliptic Cones at Supersonic Speeds written by George E. Kaattari and published by . This book was released on 1970 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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