Download or read book A Fine wire Stagnation Temperature Probe written by William Joseph Yanta and published by . This book was released on 1970 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: A temperature probe using a small thermocouple wire with its axis placed normal to an airstream was designed, built and tested. The primary purpose of the probe is to measure the stagnation temperature distribution through a supersonic turbulent boundary layer. The small probe size permits measurements in the laminar sublayer region. The probe's simple geometric shape and design provides simplicity in determining the local gas temperature. Experiments were made to measure the local stagnation temperature of the flow with an accuracy of 5R over a moderate temperature range of 560R to 780R. (Author)
Download or read book A Fine Wire Stagnation Temperature Probe written by William J. Yanta and published by . This book was released on 1970 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A temperature probe using a small thermocouple wire with its axis placed normal to an airstream was designed, built and tested. The primary purpose of the probe is to measure the stagnation temperature distribution through a supersonic turbulent boundary layer. The small probe size permits measurements in the laminar sublayer region. The probe's simple geometric shape and design provides simplicity in determining the local gas temperature. Experiments were made to measure the local stagnation temperature of the flow with an accuracy of 5R over a moderate temperature range of 560R to 780R. (Author).
Download or read book A Hot wire Stagnation Temperature Probe written by William Joseph Yanta and published by . This book was released on 1968 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: A temperature probe using a platinum 'hot-wire' which can be used to measure the local stagnation temperature in a hypersonic boundary layer was designed and tested. The temperature dependence of the wire properties is taken into account which greatly extends the probe's operating range. The primary function of the probe is to measure the temperature profiles in the sublayer. The small wire size (0.0001 inches) and suitable probe design make it possible to make measurements to within 0.003 inches of the wall. (Author).
Download or read book A Fine wire Thermocouple Probe for Measurement of Stagnation Temperatures in Real Gas Hypersonic Flows of Nitrogen written by Brian Ray Hollis and published by . This book was released on 1991 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Use of a Pulse Heated Fine Wire Probe for the Measurement of Total Temperature in Shock Driven Facilities written by Eric J. Softley and published by . This book was released on 1968 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A fine wire placed in a flow stream will experience an energy transfer rate dependent on various flow properties and on the difference between a wire recovery temperature T sub R and the wire temperature T sub w. By applying an electrical pulse T sub w can be varied during the flow duration, and from measurements made on the wire the value of T sub R (or its subsequent history if it is time dependent) can be determined. The stagnation temperature approximates the quantity T sub R and can be determined directly from it in many applications. Measurements behind an incident shock in a shock tube has resulted in measurements of T sub s to within 5% of that calculated from shock velocity. Applications of the technique to hypersonic near wakes and to boundary layers undergoing transition are demonstrated. (Author).
Download or read book Total Temperature Probes for High temperature Hypersonic Boundary layer Measurements written by Cindy W. Albertson and published by . This book was released on 1993 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A HOT WIRE STAGNATION TEMPERATURE PROBE written by William J. Yanta and published by . This book was released on 1968 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: A temperature probe using a platinum 'hot-wire' which can be used to measure the local stagnation temperature in a hypersonic boundary layer was designed and tested. The temperature dependence of the wire properties is taken into account which greatly extends the probe's operating range. The primary function of the probe is to measure the temperature profiles in the sublayer. The small wire size (0.0001 inches) and suitable probe design make it possible to make measurements to within 0.003 inches of the wall. (Author).
Download or read book An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient written by David L. Brott and published by . This book was released on 1969 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: The paper describes the results of a detailed experimental investigation of a two-dimensional turbulent boundary layer in a favorable pressure gradient where the free-stream Mach number varied from 3.8 to 4.6 and the ratio of wall to adiabatic-wall temperature has a nominal value of 0.82. Detailed profile measurements were made with pressure and temperature probes; skin friction was measured directly with a shear balance. The velocity- and temperature-profile results were compared with zero pressure gradient and incompressible results. The skin-friction data were correlated with momentum-thickness Reynolds number and pressure-gradient parameter. (Author).
Download or read book NBS Special Publication written by and published by . This book was released on 1972 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Cold Flow Field Experimental Study Associated with a Two dimensional Multiple Nozzle written by Jerry L. Wagner and published by . This book was released on 1971 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: A cold flow-field study of a rapid expansion, Mach 4.73, two-dimensional multiple nozzle array has been carried out in the hypersonic wind Tunnel. The nozzles are of the type used in a gas dynamic laser where the quality of the downstream flow field is important. The report examines the uniformity of the flow field in such a multiple nozzle array. Tests were conducted at supply conditions of 45 psia and 540 deg R. Pitot pressure, static pressure, and total temperature were measured along the axial, vertical, and horizontal centerlines within the nozzle and 21 nozzle exit heights downstream. Shadowgraph pictures provided qualitative flow field observations. The shock structure consisted of sidewall shocks, nozzle trailing edge shocks, and nozzle throat shocks. Viscous phenomena consisted of the boundary layers on the sidewalls and contoured walls, as well as the turbulent wakes caused by the trailing edges of the center nozzle blades. Mach number, static temperature, static density, and velocity profiles are presented. This flowfield information is useful to the prediction of the degradation of beam quality resulting from the non-homogeneity of a gas-dynamic-laser flowfield.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1984 with total page 558 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by United States. National Aeronautics and Space Administration and published by . This book was released on 1978 with total page 814 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Measurements of a Mach 4 9 Zero pressure gradient Turbulent Boundary Layer with Heat Yransfer written by Robert L. P. Voisinet and published by . This book was released on 1972 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of the compressible turbulent boundary layer in a zero-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall for a nominal Mach number of 4.9, at momentum thickness Reynolds numbers from 7,000. to 58,000. and at wall-to-adiabatic-wall temperature ratios of 1.0, 0.8 and 0.25. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. Furthermore, the wall shear and surface heat transfer were measured directly with a skin-friction balance and a heat-transfer gage, respectively. (Author Modified Abstract).
Download or read book Bibliography of Scientific and Industrial Reports written by and published by . This book was released on 1970 with total page 922 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by and published by . This book was released on 1983 with total page 430 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers written by David F. Gates and published by . This book was released on 1973 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).
Download or read book Measurement of Unsteady Fluid Dynamic Phenomena written by Bryan E. Richards and published by . This book was released on 1977 with total page 360 pages. Available in PDF, EPUB and Kindle. Book excerpt:
