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:
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 B. Rumsey and published by . This book was released on 1958 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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).
Download or read book Measurements of Aerodynamic Heat Transfer on a 15 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 61 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book NASA Technical Note written by and published by . This book was released on 1964 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
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.
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 Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-10 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Download or read book Free flight Skin temperature and Surface pressure Measurements on a Highly Polished Nose Having a 1000 Total angle Cone and a 100 Half angle Conical Flare Section Up to a Mach Number of 4 08 written by Bernard Rashis and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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).
Download or read book Measurements of Aerodynamic Heat Transfer in Turbulent Separated Regions at a Mach Number of 1 8 written by Benjamine J. Garland and published by . This book was released on 1958 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Inverse Heat Conduction and Heat Exchangers written by Suvanjan Bhattacharyya and published by BoD – Books on Demand. This book was released on 2020-12-02 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt: A direct solution of the heat conduction equation with prescribed initial and boundary conditions yields temperature distribution inside a specimen. The direct solution is mathematically considered as a well-posed one because the solution exists, is unique, and continuously depends on input data. The estimation of unknown parameters from the measured temperature data is known as the inverse problem of heat conduction. An error in temperature measurement, thermal time lagging, thermocouple-cavity, or signal noise data makes stability a problem in the estimation of unknown parameters. The solution of the inverse problem can be obtained by employing the gradient or non-gradient based inverse algorithm. The aim of this book is to analyze the inverse problem and heat exchanger applications in the fields of aerospace, mechanical, applied mechanics, environment sciences, and engineering.
Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1961-07 with total page 1766 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1961 with total page 1878 pages. Available in PDF, EPUB and Kindle. Book excerpt:
