Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 52
Book Description
An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient. Part 2 - The Compressibility Transformation - General Considerations
Author: An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient: The Compressibility transformation
Author: Constantino EconomosPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 52
Book Description
This report investigates the behavior of high speed turbulent boundary layer with heat transfer and streamwise pressure gradient.
Monthly Catalogue, United States Public Documents
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1730
Book Description
Scientific and Technical Aerospace Reports
Author: Calculation of Turbulent Boundary Layers with Heat Transfer and Pressure Gradient Utilizing a Compressibility Transformation. Part 1: Summary Report
Author: C. EconomosAnalysis of Variable Property Turbulent Boundary Layers by Means of a Modified Compressibility Transformation
Author: C. EconomosPublisher:
ISBN:
Category : Transformations (Mathematics)
Languages : en
Pages : 92
Book Description
A generalized form of the Coles compressibility transformation is utilized to analyze compressible turbulent boundary-layer flows. The generalization in the transformation is distinguished by specifying a stretching parameter that depends upon both space variables rather than on only the streamwise coordinate. This modification is shown to eliminate the distortion observed in the wake region of the transformed velocity profiles. For zero pressure gradient flows, predictions based upon the analysis are consistently superior with predictions due to Spalding-Chi and Baronti-Libby. A wide range of experimental data have been examined with Mach numbers ranging as high as 8, wall to free stream total temperature ratios as low as 0.25 and momentum thickness Reynolds numbers up to approximately one million.
Experimental Investigation of a 4 1/2-stage Turbine with Very High Stage Loading Factor
Author: Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 1092
Book Description
The results of the Task 1 and 2 turbine design work are reported. Preliminary design is discussed. Blading detailed design data are summarized. Predicted performance maps are presented. Steady-state stresses and vibratory behavior are discussed, and the results of the mechanical design analysis are presented. -- [V]. I The experimental test program results of a 4 1/2-stage turbine with a very high stage loading factor are presented. A four-stage turbine was tested with and without outlet turning vanes. The 4 1/2-stage turbine achieved a design point total-to-total efficiency of 0.853. The outlet turning vane design point performance was 0.4 percent of the overall 4 1/2-stage turbine efficiency. Tests were conducted at various levels of Reynolds number and indicated decreases in turbine efficiency and equivalent weight flow with decreasing Reynolds number. --[V]. II.
Meteorological and Geoastrophysical Abstracts
Author: NASA Contractor Report
Author: Evaluation of Active Cooling Systems for a Mach 6 Hypersonic Transport Airframe
Author: R. G. HelenbrookPublisher:
ISBN:
Category : Shielding (Heat)
Languages : en
Pages : 924
Book Description
Transpiration and convective cooling concepts are examined for the fuselage and tail surface of a Mach 6 hypersonic transport aircraft. Hydrogen, helium, and water are considered as coolants. Heat shields and radiation barriers are examined to reduce heat flow to the cooled structures. The weight and insulation requirements for the cryogenic fuel tanks are examined so that realistic totals can be estimated for the complete fuselage and tail. Structural temperatures are varied to allow comparison of aluminum alloy, titanium alloy, and superalloy construction materials. The results of the study are combined with results obtained on the wing structure, obtained in a previous study, to estimate weights for the complete airframe. The concepts are compared among themselves, and with the uncooled concept on the basis of structural weight, cooling system weight, and coolant weight.