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Aerothermal Tests Of A 1250 Cone At Mach 67 For Various Reynolds Numbers Angles Of Attack And Nose Shapes
Download Aerothermal Tests Of A 1250 Cone At Mach 67 For Various Reynolds Numbers Angles Of Attack And Nose Shapes full books in PDF, epub, and Kindle. Read online Aerothermal Tests Of A 1250 Cone At Mach 67 For Various Reynolds Numbers Angles Of Attack And Nose Shapes ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Aerothermal Tests of a 12.50 Cone at Mach 6.7 for Various Reynolds Numbers, Angles of Attack, and Nose Shapes by : Robert J. Nowak
Download or read book Aerothermal Tests of a 12.50 Cone at Mach 6.7 for Various Reynolds Numbers, Angles of Attack, and Nose Shapes written by Robert J. Nowak and published by . This book was released on 1985 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerothermal Tests of a 12.5 Percent Cone at Mach 6.7 for Various Reynolds Numbers, Angles of Attack and Nose Shapes by :
Download or read book Aerothermal Tests of a 12.5 Percent Cone at Mach 6.7 for Various Reynolds Numbers, Angles of Attack and Nose Shapes written by and published by . This book was released on 1985 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerothermal Tests of a 12.5° Cone at Mach 6.7 for Various Reynolds Numbers, Angles of Attack, and Nose Shapes by : Robert J. Nowak
Download or read book Aerothermal Tests of a 12.5° Cone at Mach 6.7 for Various Reynolds Numbers, Angles of Attack, and Nose Shapes written by Robert J. Nowak and published by . This book was released on 1985 with total page 87 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8 by : P. Calvin Stainback
Download or read book Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8 written by P. Calvin Stainback and published by . This book was released on 1969 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Heating and Boundary-layer Transition on a 1/10-power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-stream Reynolds Numbers Up to 16 X 10(6) by : Benjamine J. Garland
Download or read book Aerodynamic Heating and Boundary-layer Transition on a 1/10-power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-stream Reynolds Numbers Up to 16 X 10(6) written by Benjamine J. Garland and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Aerodynamic Characteristics of Short Blunt Cones with Various Nose and Base Cone Angles at Mach Numbers from 0.6 to 5.5 and Angles of Attack to 180 Degrees by : Stuart L. Treon
Download or read book Static Aerodynamic Characteristics of Short Blunt Cones with Various Nose and Base Cone Angles at Mach Numbers from 0.6 to 5.5 and Angles of Attack to 180 Degrees written by Stuart L. Treon and published by . This book was released on 1961 with total page 40 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 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 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 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 Transonic Investigation of the Effects of Nose Bluntness, Fineness Ratio, Cone Angle, and Base Shape on the Static Aerodynamic Characteristics of Short, Blunt Cones at Angles of Attack to 1800 by : Cuyler W. Brooks
Download or read book Transonic Investigation of the Effects of Nose Bluntness, Fineness Ratio, Cone Angle, and Base Shape on the Static Aerodynamic Characteristics of Short, Blunt Cones at Angles of Attack to 1800 written by Cuyler W. Brooks and published by . This book was released on 1963 with total page 48 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 Longitudinal Aerodynamic Characteristics of Two Blunted Cone Reentry Configurations at Mach Numbers from 17.6 to 22.2 Including Some Reynolds Number Effects by : Dal V. Maddalon
Download or read book Longitudinal Aerodynamic Characteristics of Two Blunted Cone Reentry Configurations at Mach Numbers from 17.6 to 22.2 Including Some Reynolds Number Effects written by Dal V. Maddalon and published by . This book was released on 1966 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Force and Pressure Tests on Cones with Simulated Ablated Noses at Mach Numbers 8 and 16 by :
Download or read book Force and Pressure Tests on Cones with Simulated Ablated Noses at Mach Numbers 8 and 16 written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented from static-force tests and pressure distribution tests of conical bodies with various nose shapes which were chosen to simulate the estimated shapes obtained after significant ablation of the nose had taken place. The basic cone half-angle is 6.3 deg, and the nominal bluntness ratio is 0.25. Nose shapes tested consisted of symmetrical biconics with nose angles of 30, 40, and 50 deg and asymmetrical noses derived from the 50-deg biconic. Results were also obtained for a 50-deg symmetric biconic nose on 4.0- and 9.0-deg cones. The effect of changing the nose-to-cone shoulder radius was investigated on several configurations. Most of the data were obtained at Mach 8, and a limited amount of data was taken at Mach 16. The nominal Reynolds number was 3,100,000 based on the sharp cone length of the 6.3-deg pressure model. For the force tests, the angle-of-attack range was from -5 to 11 deg, and for the pressure tests, the angles of attack included the configuration trim angle and up to 4 deg on either side of the trim angle in increments of generally 1 deg. At Mach 8, data are given for the ablated nose shapes with the vehicle rolled -30, -60, and -90 deg. (Author).
Book Synopsis Effects of Angle of Attack and Bluntness on Laminar Heating-rate Distributions of a 15 ̊cone at a Mach Number of 10.6 by : Joseph W. Cleary
Download or read book Effects of Angle of Attack and Bluntness on Laminar Heating-rate Distributions of a 15 ̊cone at a Mach Number of 10.6 written by Joseph W. Cleary and published by . This book was released on 1969 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Laminar heating rate from wind tunnel tests using angle of attack and Reynolds number.
Book Synopsis Pressure Distribution and Flow Visualization Tests of a 1.5 Elliptic Cone at Mach 10 by : R. L. Palko
Download or read book Pressure Distribution and Flow Visualization Tests of a 1.5 Elliptic Cone at Mach 10 written by R. L. Palko and published by . This book was released on 1963 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
