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Laminar Transitional And Turbulent Heat Transfer To A Cone Cylinder Flare Body At Mach 80
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Book Synopsis Laminar, Transitional, and Turbulent Heat Transfer to a Cone-cylinder-flare Body at Mach 8.0 by : Victor Zakkay
Download or read book Laminar, Transitional, and Turbulent Heat Transfer to a Cone-cylinder-flare Body at Mach 8.0 written by Victor Zakkay and published by . This book was released on 1962 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: A modified equation for the heat transfer coefficient in the transitional and fully turbulent region based on the F.P.R.E. method is then presented. This method gives good agreement with the experimental results presented here.
Book Synopsis Laminar, Transitional and Turbulent Flow with Adverse Pressure Gradient on a Cone-flare at Mach 10 by : V. Zakkay
Download or read book Laminar, Transitional and Turbulent Flow with Adverse Pressure Gradient on a Cone-flare at Mach 10 written by V. Zakkay and published by . This book was released on 1965 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the boundary layer on a cone-flare body at Mach 10 is presented. Measurements of pressure, heat transfer and boundary layer thickness are made in regions of zero and adverse pressure gradient. Several noses are fitted to the cone to produce blunted cone-flares, which are used to study separation. The experimental results are compared to some recent analytical investigations. The results showed a small amount of blunting can lower the Reynolds number sufficiently to produce separation. The experiment results also showed that a small amount of crossflow (produced by placing the model at small angles of attack) was capable of eliminating separation.
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 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 Recovery Temperature Transition and Heat-transfer Measurements at Mach 5 by : Paul F. Brinich
Download or read book Recovery Temperature Transition and Heat-transfer Measurements at Mach 5 written by Paul F. Brinich and published by . This book was released on 1961 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Variation of Boundary-layer Transition with Heat Transfer on Two Bodies of Revolution at a Mach Number of 3.12 by : John R. Jack
Download or read book Variation of Boundary-layer Transition with Heat Transfer on Two Bodies of Revolution at a Mach Number of 3.12 written by John R. Jack and published by . This book was released on 1955 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made at a Mach number of 3.12 to determine the effects of heat transfer on boundary-layer transition. Data were obtained for a cone cylinder and a parabolic-nosed cylinder at Reynolds numbers up to 12,000,000 based on body length. The results show that cooling the cone-cylinder model to a wall-to-free-stream static-temperature ratio of approximately 1.4 increased the transition Reynolds number from a value of about 2,000,000 at equilibrium to 10,600,000. For temperature ratios less than 1.4, the boundary-layer flow was laminar over the entire model. The rapid increase of transition Reynolds number with small reductions in temeprature ratio near 1.4 indicated that temperature ratios slight lower may result in a laminar boundary layer for very high Reynolds numbers. For the parabolic-nosed body, the transition Reynolds number was about twice that of the cone-cylinder model over the temperature range investigated.
Book Synopsis Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers by : Ivan E. Beckwith
Download or read book Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers written by Ivan E. Beckwith and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Design studies of hypersonic lifting vehicles have generally indicated that aerodynamic heating may be reduced by using highly swept configurations with blunted leading edges. For laminar boundary layers the effect of sweep angle A on the heat transfer at the leading edge is usually taken as cos A as shown by the data of Feller (ref. 1) who measured the average heat transfer on the front half of a swept cylinder. More recent data (refs. 2 and 3) have indicated that the effect of sweep may be more nearly cos3/2 Lambda which, at a sweep angle of 75 deg, would result in a 50-percent reduction of the heat transfer predicted by the cos A variation. The data and theory of reference 4 also indicate a cos3/2 lambda variation but the theories of references 5 and 6 indicate a variation somewhere between cos A and cos3/2 lambda for large stream Mach numbers. The data of reference 7, in contrast to the investigations just cited, showed large increases in average heat transfer to a circular leading edge with increasing A up to a lambda of about 40 deg. These increases in heat transfer were probably caused by transition to turbulent flow which apparently resulted primarily from the inherent instability of the three-dimensional boundary layer flow on a yawed cylinder. The leading-edge Reynolds numbers of reference 7 were considerably larger than the values in references 1 to 4 and were also larger than typical values for full-scale leading edges of hypersonic vehicles; hence, the main application of the high Reynolds number tests will probably be to bodies at angle of attack.
Book Synopsis Technical Publications Announcements with Indexes by : United States. National Aeronautics and Space Administration
Download or read book Technical Publications Announcements with Indexes written by United States. National Aeronautics and Space Administration and published by . This book was released on 1962-04 with total page 694 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer on a 15 Deg Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 by : CHARLES B. RUMSEY
Download or read book Measurements of Aerodynamic Heat Transfer on a 15 Deg Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 written by CHARLES B. RUMSEY and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of aerodynamic heat transfer were made at a number of stations along a cone-cylinder-flare model having a 15 degrees total-angle conical nose and a 10 degrees half-angle flare skirt. The maximum Mach number was 4.7, and local Reynolds numbers based on body length to a measurement station varied from 2 x 10 to the 6th power to 138 x 10 to the 6th power. Local Stanton numbers measured on the nose cone and flare showed fair agreement with laminar and turbulent theories, while the measurements on the cylinder were generally somewhat lower than theory. Experimental recovery factors, determined twice during the test, were unaccountably lower than theoretical values. Local transition Reynolds numbers, based on length from the nose tip, varied from 3 x 10 to the 6th power to 18 x 10 to the 6th power and were much lower than values previously obtained on the smoother nose of a similar model. At an angle of attack of about 9 degrees, the heat transfer on the flare increased to more than twie the theoretical turbulent value for zero angle of attack. (Author).
Book Synopsis The Effect of Centrifugal Forces on Boundary Layer Transition for a Highly Heated Body by : Eugene Sevigny
Download or read book The Effect of Centrifugal Forces on Boundary Layer Transition for a Highly Heated Body written by Eugene Sevigny and published by . This book was released on 1959 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree 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 Degree 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 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2 by : Charles B. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2 written by Charles B. Rumsey and published by . This book was released on 1961 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of aerodynamic heat transfer have been made at several stations on the 15 degree total-angle conical nose of a rocket-propelled model in free flight at Mach numbers up to 5.2. Data are presented for a range of local Mach number just outside the boundary layer from 1.40 to 4.65 and a range of local Reynolds number from 3.8 times 10 to the 6th power to 46.5 times 10 to the 6th power, based on length from the nose tip to a measurement station. Laminar, transitional, and turbulent heat-transfer coefficients were measured. The laminar data were in agreement with laminar theory for cones, and the turbulent data agreed well with turbulent theory for cones using Reynolds number based on length from the nose tip. (Author).
Book Synopsis Experimental Investigation of Boundary-layer Transition on a Cooled 7.5° Total-angle Cone at Mach 10 by : Philip E. Everhart
Download or read book Experimental Investigation of Boundary-layer Transition on a Cooled 7.5° Total-angle Cone at Mach 10 written by Philip E. Everhart and published by . This book was released on 1967 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1971 with total page 804 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Recovery Temperatures on a Sphere with Laminar, Transitional, and Turbulent Boundary Layers at Mach Numbers of 2.00 and 4.15 by : Ivan E. Beckwith
Download or read book Heat Transfer and Recovery Temperatures on a Sphere with Laminar, Transitional, and Turbulent Boundary Layers at Mach Numbers of 2.00 and 4.15 written by Ivan E. Beckwith and published by . This book was released on 1957 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made of the pressure and equilibrium-temperature distributions on sphere at Mach numbers of 2.00 and 4.15. The local aerodynamic best transfer was also measured on a sphere at a Mach number of 2.00 and on a hemisphere-cylinder at a Mach number of 4.15. The Reynolds number range for these tests was from 1.5 x 10 to the 6th power to 8.1 x 10 to the 6th power, based on free-stream conditions and the diameter of the spheres.
Book Synopsis HEAT TRANSFER MEASUREMENTS ON A CONE-CYLINDER-FLARE AT A MACH NUMBER OF 6.8 by :
Download or read book HEAT TRANSFER MEASUREMENTS ON A CONE-CYLINDER-FLARE AT A MACH NUMBER OF 6.8 written by and published by . This book was released on 1962 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat transfer measurements have been made in the hypersonic wind tunnel on a cone-cylinder-flare and high values of the heat transfer factor found where the flow reattached on the flare.
