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Author : Cindy W. Albertson
Publisher : Unknown
Page : 40 pages
File Size : 46,7 Mb
Release : 1993
Category : Temperature measurements
ISBN : NASA:31769000521818
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 36 pages
File Size : 50,9 Mb
Release : 2018-07-13
Category : Electronic
ISBN : 1722908866
The design and test results of two types of total temperature probes that were used for hypersonic boundary-layer measurements are presented. The intent of each design was to minimize the total error and to maintain minimal size for measurements in boundary layers 1.0 in. thick and less. A single platinum-20-percent-rhodium shield was used in both designs to minimize radiation heat transfer losses during exposure to the high-temperature test stream. The shield of the smaller design was flattened at the flow entrance to an interior height of 0.02 in., compared with 0.03 in. for the larger design. The resulting vent-to-inlet area ratios were 60 and 50 percent. A stainless steel structural support sleeve that was used in the larger design was excluded from the smaller design, which resulted in an outer diameter of 0.059 in., to allow closer placement of the probes to each other and to the wall. These small design changes to improve resolution did not affect probe performance. Tests were conducted at boundary-layer-edge Mach numbers of 5.0 and 6.2. The nominal free-stream total temperatures were 2600 degrees and 3200 degrees R. The probes demonstrated extremely good reliability. The best performance in terms of recovery factor occurred when the wire-based Nusselt number was at least 0.04. Recommendations for future probe designs are included. Albertson, Cindy W. and Bauserman, Willard A., Jr. Langley Research Center RTOP 506-43-21-01...
Author : R. L. P. Voisinet,Roland E. Lee,Hans Ulrich Meier
Publisher : Unknown
Page : 88 pages
File Size : 48,8 Mb
Release : 1974
Category : Fluid mechanics
ISBN : UOM:39015095246792
The predominant probes used for measuring total temperature in a compressible boundary-layer flow are described. The results of a direct comparison between two of these probes, the conical equilibrium temperature probe (Danberg probe) and the combined temperature-pressure probe of the DFVLR-AVA, are presented. The comparison was made by testing the probes simultaneously in the nozzle-wall turbulent boundary-layer flow of the NOL Boundary Layer Channel at zero and moderate heat-transfer conditions...
Author : William Joseph Yanta
Publisher : Unknown
Page : 66 pages
File Size : 54,7 Mb
Release : 1968
Category : Aerodynamics, Hypersonic
ISBN : UOM:39015095150283
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).
Author : S.P. Venkateshan
Publisher : Springer Nature
Page : 560 pages
File Size : 42,9 Mb
Release : 2021-07-01
Category : Technology & Engineering
ISBN : 9783030736200
p="" This book focuses both on the basics and more complex topics in mechanical measurements such as measurement errors & statistical analysis of data, regression analysis, heat flux, measurement of pressure, and radiation properties of surfaces. End of chapter problems, solved illustrations, and exercise problems are presented throughout the book to augment learning. It is a useful reference for students in both undergraduate and postgraduate programs. ^
Author : Jack Nugent,Glenn M. Sakamoto,Lannie D. Webb
Publisher : Unknown
Page : 60 pages
File Size : 52,6 Mb
Release : 1972
Category : Fluidic devices
ISBN : UIUC:30112106884379
An experimental temperature probe package containing a fluidic oscillator temperature probe and a shielded thermocouple temperature probe was tested during several X-15 flights. The X-15 flights provided greatly varying test conditions, including a wide range of rapidly changing total temperatures and Mach numbers which extended from subsonic to hypersonic speeds. Within restricted ranges of free-stream Mach number, free-stream unit weight flow, and local stagnation pressure, both probes yielded ramp outputs of temperature parallel to ramp inputs of free-stream total temperature. Within these ranges both probes were used to determine total temperature in the Mach 6 temperature environment. Because ambient temperature was known, both probes were used to estimate velocity and Mach number.
Author : Anonim
Publisher : Unknown
Page : 372 pages
File Size : 44,8 Mb
Release : 1994
Category : Aeronautics
ISBN : MINN:31951P00544954D
Author : Robert L. P. Voisinet,Roland E. Lee
Publisher : Unknown
Page : 144 pages
File Size : 43,5 Mb
Release : 1973
Category : Fluid mechanics
ISBN : UOM:39015095246784
The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
Author : Anonim
Publisher : Unknown
Page : 128 pages
File Size : 44,5 Mb
Release : 1994
Category : Government publications
ISBN : WISC:89117117382
Author : Anonim
Publisher : Unknown
Page : 1064 pages
File Size : 50,8 Mb
Release : 1994
Category : Government publications
ISBN : UIUC:30112005602013
Author : Marvin I. Kussoy
Publisher : Unknown
Page : 32 pages
File Size : 51,6 Mb
Release : 1989
Category : Aerodynamics, Hypersonic
ISBN : NASA:31769000583800
Author : Anonim
Publisher : Unknown
Page : 542 pages
File Size : 55,7 Mb
Release : 1972
Category : Mechanics, Applied
ISBN : UCAL:C2682437
Author : Anonim
Publisher : Unknown
Page : 24 pages
File Size : 50,5 Mb
Release : 1967
Category : Aeronautics
ISBN : UVA:X004018880
Author : United States. National Bureau of Standards
Publisher : Unknown
Page : 144 pages
File Size : 49,5 Mb
Release : 1972
Category : Temperature measurements
ISBN : IOWA:31858045231796
Author : Paul D. Freeze,Leslie D. Parker
Publisher : Unknown
Page : 144 pages
File Size : 51,7 Mb
Release : 1972
Category : Temperature
ISBN : UOM:39015086413930