Download or read book Heat transfer Measurements in Short duration Hypersonic Facilities written by D. L. Schultz and published by . This book was released on 1973 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is the first of several AGARDographs commissioned by the Fluid Dynamics Panel to deal with instrumentation techniques used in hypersonic short-duration facilities and with related topics. Since one of the reasons for the development of such facilities was the need for experimental data on the extremely high heat-transfer rates that a body experiences in re-entry conditions, the measurement of heat transfer constitutes a particularly appropriate initial subject area; moreover, the methods to be described are also applicable to a variety of problems other than those of hypersonic flow. An important feature of this AGARDograph is the unified treatment that it accords to the theory underlying heat-transfer gauges of various types. In addition, a detailed analysis is given of the magnitude of the errors in the values of heat-transfer rate deduced from the observations. Constructional considerations are discussed fully; physical data and design charts are included.
Download or read book Heat transfer Measurements in Short duration Hypersonic Facilities written by Donald Lorimer Schultz and published by . This book was released on 1973 with total page 149 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps Mach 8 heat transfer data for flows ahead of ramps written by Louis G. Kaufman and published by . This book was released on 1964 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for [M sub infinity =] 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for [M sub infinity =] 8 for Reynolds numbers between 1.1 and 3.3 million." -- page iii, pt.4.
Download or read book Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps Mach 5 and 8 data for expansion corner flows written by Louis G. Kaufman and published by . This book was released on 1963 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for [M sub infinity =] 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for [M sub infinity =] 8 for Reynolds numbers between 1.1 and 3.3 million." -- page iii, pt.4.
Download or read book Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps Mach 8 pressure data for flows ahead of ramps written by Louis G. Kaufman and published by . This book was released on 1964 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for [M sub infinity =] 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for [M sub infinity =] 8 for Reynolds numbers between 1.1 and 3.3 million." -- page iii, pt.4.
Download or read book The Use of Thermochromic Liquid Crystals for Heat Transfer Measurement in Short Duration Hypersonic Wind Tunnel Facilities written by G. T. Roberts and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat Transfer to Surfaces in the Neighborhood of Protuberances in Hypersonic Flow written by M. H. Bloom and published by . This book was released on 1957 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps Mach 5 pressure data for flows ahead of ramps written by Louis G. Kaufman and published by . This book was released on 1963 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for [M sub infinity =] 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for [M sub infinity =] 8 for Reynolds numbers between 1.1 and 3.3 million." -- page iii, pt.4.
Download or read book Heat Transfer Measurements in Hypersonic Low Density Flows with Phase Change Coatings written by Gerald M. Gregorek and published by . This book was released on 1968 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic heat transfer rates to blunt 10 and 25 degree cones were measured using surface coatings which change phase at precisely known temperatures. Results from motion picture time-histories of the melting of the coatings on nylon and teflon models taken at Mach 10 and Re sub infinity D = 5600 are compared with earlier experiments on thin-skin models using a transient technique. The two methods agree within 5% at heating rate levels below 1 BTU/sq ft sec but show 25% deviations at levels about 2 BTU/sq ft sec. This error is attributed to the injection procedure which made determination of the exact moment of model insertion difficult. (Author).
Download or read book A New Heat Transfer Capability for Application in Hypersonic Flow Using Multiple Schmidt Boelter Gages written by and published by . This book was released on 1999 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat transfer measurements were made on a complex scaled wind tunnel model containing 400 miniature discrete sensors in Hypersonic Wind Tunnels B and C at the Arnold Engineering Development Center (AEDC). This test program was significant for a number of reasons which, when combined, have led to the development of a new test capability at the AEDC. First and foremost is the large number of simultaneous thermal measurements made on the wind tunnel test model. The large number of simultaneous measurements on a single test model was primarily driven by the customer's desire to conduct the test program in the most cost effective manner. This request was translated into a system to obtain high quality test data points in the least amount of air on time and to make heat transfer measurements on all surfaces of a very complex model. The measurements were made on relatively flat surfaces, wing leading edges, and thin tip fin leading edges; multiple measurements were made on a wide variety of unconventional control surfaces and appendages. Simultaneous measurements on the wide variety of surfaces required the selection of a sensor which was highly sensitive, small, and could be contoured to small local surface radii. The sensor chosen for these measurements was the Schmidt Boelter gage. The capability to calibrate Schmidt Boelter gages and compare a National Institute of Standards and Technology (NIST) traceable and certified standard is one reason this sensor was used for all of the measurements. Since each gage needs the measurement of two thermal parameters to obtain the required measurement parameter, the simultaneous measurement of 800 thermal parameters was required. The previous data acquisition system in these hypersonic wind tunnels at the AEDC was capable of measuring outputs for only 112 Schmidt Boelter gages simultaneously.
Download or read book Heat Transfer Measurements in Hypersonic Low density Flows by Thin Skin Techniques and Phase change Coatings written by G. M. Gregorek and published by . This book was released on 1968 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Heat transfer Distributions in Deep Cavities in Hypersonic Separated Flow written by Allan R. Wieting and published by . This book was released on 1970 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypervelocity wind tunnel tests to determine local cold wall convective heating rates to small rectangular cavities,
Download or read book Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps Part Iv Mach 8 Heat Transfer Data for Flows Ahead of Ramps Part of an Investigation of Hypersonic Flow Separation and Control Characteristics written by Louis G Kaufman (II.) and published by . This book was released on 1964 with total page 141 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for M = 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for M = 8 for Reynolds numbers between 1.1 and 3.3 million. (Author).
Download or read book Experimental Surface Heat Flux Measurement in Hypervelocity Flows written by William P. Flaherty and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Prediction of heat transfer is integral to development of hypersonic vehicles. Underprediction of heat transfer rates can result in catastrophic failures during flight testing. An example which illustrates the importance of heat transfer during hypersonic flight is the destruction of the space shuttle Columbia during the re-entry portion of STS-107. The shuttle experienced damage to its heat shielding, which in turn was not able to protect the craft from the extremely high levels of heat transfer experience during re-entry, resulting in the destruction of the craft. Due to both the high costs and dangers associated with flight testing, ground based experimental heat transfer data is essential the the design of safe and efficient hypersonic craft. Experimental data in facilities which have the ability to create mid to high enthalpy flowfields without large amounts of freestream dissociation is highly desirable in order to both validate CFD codes and to determine the effects of variations in geometry on heat transfer. The Hypervelocity Expansion Tube (HET) is one of a few facilities in the US that are able to create these flows, and thus it is an optimal test bed for these types of studies. Two gage types used in order to measure surface heat transfer, thermocouples and thin film gages. This thesis details the development and application of thermocouples and thin film surface heat transfer gages in the HET. These gages have been extensively used in other hypersonic facilities, but their application and comparison in intermediate enthalpy conditions (like those created in the HET) has not been well established in previous reports. This study sought to compare the performance of the gages and to apply them to canonical model geometries to investigate heat transfer in the HET.
Download or read book A Review of High speed Convective Heat transfer Computation Methods written by Michael E. Tauber and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Heat Transfer Measurements on Reentry Vehicle Surfaces at High Reynolds Number written by Bryan E. Richards and published by . This book was released on 1973 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat transfer rates using calorimeter sensors, and pressures using variable reluctance diaphragm transducers, have been measured on five model shapes at Mach numbers of 15 and 20 and over a unit Reynolds number range of 2 million to 7 million per foot. Two basic shapes, a hemisphere and a half-angle biconic configuration with and without nose bluntness, were tested with different surface roughness. The results are reported and discussed. (Modified author abstract).
Download or read book Method for Prediction of Streamlines and Heat Transfer to Bodies in Hypersonic Flow written by ERNEST A. SANLORENZO and published by . This book was released on 1960 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: The requirement of this contract is the investigation of methods for the prediction of heat transfer to typical hypersonic configurations. In support of this work extensive pressure and heat transfer measurements have been made in the hypersonic facilities at Arnold Engineering Development Center, Tullahoma, Tennessee. The experimental effort was divided into two phases. During the first phase, very basic geometries were investigated which included a spherically blunted cone. In the second phase, various delta wing configurations were tested. These configurations considered the effect of leading edge sweep, dihedral, and cathedral. The work reported herein is the result of a general heat transfer analysis as applied to the first phase experimental results, and in particular, to the spherically blunted cone.
