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3 edition of The measurement of heat transfer and skin friction at supersonic speeds found in the catalog.

The measurement of heat transfer and skin friction at supersonic speeds

J. E. Johnson (undifferentiated)

The measurement of heat transfer and skin friction at supersonic speeds

preliminary results of measurements on a flat plate at a Mach number of 2.5

by J. E. Johnson (undifferentiated)

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  • 11 Currently reading

Published by Ministry of Supply, Aeronautical Research Council in London .
Written in English


Edition Notes

StatementJ. E. Johnson and R. J. Monaghan.
SeriesAeronautical Research Council. Current paper -- no. 59
ContributionsMonaghan, R. J., Aeronautical Research Council (Great Britain), Royal Aircraft Establishment (Great Britain)
The Physical Object
Pagination18 p.
Number of Pages18
ID Numbers
Open LibraryOL20269892M

  21 Picken, J. Free-flight measurements of aerodynamic heat flux to slender cones with various surface finishes at high supersonic speeds. RAE Author: J. Taylor. More recently, direct measurements of the skin friction were made at low speeds by Liepmann and Dhawan, by Dhawan, and by Smith and Walker (refs. 2through 4). At supersonic speeds, skin-friction balances have been used in numerous investigations reported in references 5 through In gen­ eral, skin-friction balances have been used.

Measurement of Heat Transfer From a Supersonic Impinging Jet Onto an Inclined Flat Plate at 45 deg C., Chung, M. K., Lim, K. B., and Kang, Y. S. (August 1, ). "Measurement of Heat Transfer From a Supersonic Impinging Jet Onto an Inclined Flat Plate at 45 deg." ASME. Heat Transfer Measurements in Incompressible Turbulent Flat Plate Cited by: 6. affect the values of heat transfer and skin-friction as well as introducing an overshoot in velocity profile. This overshoot, due to heating near the wall, is mentioned briefly in the section on general fluids under pressure gradient. It is an illustration of a qualitative effect due to,u - Author: Julian D. Cole.

SUPERSONIC SPEELS AND ITS RELATION TO HEAT TRANSFER By Willard D. Coles and Robert S. Ruggeri SUMMARY An experimental investigation was conducted in a by inch tunnel to determine the mass transfer by sublimation, heat transfer, and skin friction for an iced surface on a flat plate for Mach numbers. heat-transfer and skin-friction coefficients with surface gas injection in the form of Reynolds analogy factor, 2CH/C~, and to measure the result with respect to theoretical predictions. An optimum comparison requires that both skin-friction and heat-transfer measurements be Cited by: 7.


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The measurement of heat transfer and skin friction at supersonic speeds by J. E. Johnson (undifferentiated) Download PDF EPUB FB2

The overall heat transfer measurements were made lmth a mczn plats temperature of appronmatcly 'K and for tunnel stagnation temperatures the range ~ to ~, o~rrt3~pon~w to free strsm tiPids numbers between and 4 mdl~on, bawd on plate Size: 1MB.

COUNCIL ’ CURRENT PAPERS s. The ‘Measurement of Heat Transfer and Skin Friction at Supersonic Speeds f. Part II. Boundary Layer Measurements on a Flat Plate at M = ‘and Zero Heat Transfer.

Mbnagharr, M.A. and I J. Johnson, (Tech.), E. The Measurement of Heat Transfer and Skin Friction at Supersonic Speeds Part Ill. Measurements of Overall Heat Transfer and of the Associated Boundary Layers on a Flat Plate at MI = R. Monaghan and J. Cooke LONDON: HER MAJE_STY’S.

Skin-friction measurement at supersonic speeds. Correlation of measured and theoretical heat transfer and skin friction at hypersonic speeds, including Reynolds analogy.

PERRY WOODEN and Cited by: 4. The ‘Measurement of Heat Transfer and Skin Friction at Supersonic Speeds f Part II. Boundary Layer Measurements on a Flat Plate at M = ‘and Zero Heat Transfer (). The measurement of heat transfer and skin friction at supersonic speeds part Boundary ls,yer measurements on a flat plate at M = and eero heat transfer i- Year: OAI identifier: oai:   Skin Friction end Heat Transfer Measurements in Mach 6 High Reynolds Number Flows Fiber optic pressure/skin friction gage for supersonic flow applications RecommendedCited by: arc&.

The skin-friction com>oneilt is always difficult to estimate with precision since it depends on such parameters as the local heat-transfer conditions, pressure Lrar'rents and Isminar-to-turbulent trans*tion polnt.3 which may be ill-dcfinod.

Ikn.+hermore the correction of total drag measure. Skin-friction coefficients on biconvex cone (referred to free-stream kinetic pressure), M =Re = x /ft. Skin-friction coefficients on biconvex cone (referred to local kinetic pressure), M =Re = x /ft. Relationship between reattachment and peak-suction locations from Ref.

File Size: 1MB. The final report consists of an AIAA and an ASME paper. An experimental investigation was conducted to measure skin friction along the chamber walls of supersonic combustors.

Skin-friction drag at supersonic-hypersonic speeds with transition. MEI-KAO LIU ; MEI-KAO LIU. ARA Inc., West Covina, Calif. Conventional skin friction measurement techniques for strongly perturbed supersonic turbulent boundary layers Correlation of measured and theoretical heat transfer and skin friction at hypersonic speeds Author: Mei-Kao Liu.

A description of the calibration methods necessary to insure accurate measurements is included. Examples of recent unsteady heat transfer and skin friction measurements with interpretations of the meaning and importance of the results are by:   Silvester, T.B., Morgan, R.G.: Skin friction measurements and flow establishment within a Long Duct at superorbital speeds.

AIAA J. 46 (2), – () CrossRef Google Scholar : Lv Zhiguo, Lv Zhiguo, Li Guojun, Zhao Rongjuan, Jiang Hua, Liu Jichun, Huang Jun, Liu Shiran. Influence of the Wake Component on Turbulent Skin Friction at Subsonic and Supersonic Speeds 7 June | Aeronautical Quarterly, Vol.

30, No. 4 Generalized Velocities in the Outer Region of Hypersonic Turbulent Boundary LayersCited by: The Measurement of Heat Transfer and Skin Friction at Supersonic Speeds - Part IV; Tests on a Flat Plate at M= Notes Abstract: Abstract: Free-flight tests at supersonic speeds have been made to determine the local convective heat-transfer coefficients, evaluated from measured skin temperatures along the body of a rocket-propelled fin-stabilized parabolic body of revolution.

The Measurement of Heat Transfer and Skin Friction at Supersonic Speeds - Part III; Measurements of Overall Heat Transfer. On the use of hot and cold-film sensors for skin friction and heat transfer measurements in impingement flows.

Letters in Heat and Mass Transfer, Vol. 3, Issue. 6, p. Letters in Heat and Mass Transfer, Vol. 3, Issue. 6, p. supersonic measuiemente that have been made were at relatively low Reynolde umbers.

Flat-plate skin-friction measurements at zero heat transfer fromvarious sources were compared with the various theories for flat-plate turbulent flow in reference 3. In order some needed akin-friction data on a body ofCited by: 3. Corpus ID: Measurement by wake momentum surveys at Mach and of turbulent boundary-layer skin friction on five swept wings @inproceedings{CzarneckiMeasurementBW, title={Measurement by wake momentum surveys at Mach and of turbulent boundary-layer skin friction on five swept wings}, author={K.

Czarnecki and Mary L. Jackson and Russell B. Laminar-turbulent transition and the subsequent development of the turbulent boundary layer at hypersonic speeds affect heat-transfer, skin friction, and boundary-layer separation.S.

C. Sommer and B. J. Chort, Free-Flight Measurements of Skin Friction of Turbulent Boundary Layers with High Rates of Heat Transfer at High Supersonic Speeds, J. Cited by: 3.Summary: Skin and structural temperatures have been obtained on the X-1B and X-1E research airplanes under transient aerodynamic heating conditions at speeds up to Mach numbers near Extensive temperature measurements were obtained throughout the X-1B airplane, and temperature distributions are shown on the nose cone, the wing, and the.