Calculation Of Surface Temperatures In Steady Supersonic Flight

Author : George P. Wood
Publisher :
ISBN 13 :
Total Pages : 34 pages
Book Rating : 4.79/5 ( download)

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Download or read book Calculation of Surface Temperatures in Steady Supersonic Flight written by George P. Wood and published by . This book was released on 1946 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Surface temperatures were calculated for bodies in steady supersonic flight at Mach numbers from 2 to 10 and for altitudes from 50,000 and 200,000 feet and emissivities from 0 to 1. The importance of the effects of radiation and convection was determined. It was found, under the assumption of an isothermal atmosphere, that the gain of heat from the air by convection decreases at constant Mach number as the altitude is increased. Equilibrium between convection and radiation is established at temperatures that that consequently decrease as altitude is increased. In general, therefore, at sufficiently high altitudes the surface temperature is considerably less than the stagnation temperature. At a Mach number of 8, for example, the stagnation temperature is 4800 degrees F absolute and the equilibrium surface temperature for an emissivity of 0.5 is 3800 degress F absolute at 50,000 feet and decreases to 1350 degrees F at 200,000 feet.

Author : Richard Scherrer
Publisher :
ISBN 13 :
Total Pages : 542 pages
Book Rating : 4.57/5 ( download)

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Download or read book The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight written by Richard Scherrer and published by . This book was released on 1947 with total page 542 pages. Available in PDF, EPUB and Kindle. Book excerpt: An approximate method for determining the convective cooling requirement in the laminar-boundary-layer region of a body of revolution in high-speed flight was developed and applied to an example body. The cooling requirement for the example body was determined as a function of Mach number, altitude, size, and a surface-temperature parameter. The maximum value of Mach number considered was 3.0 and the altitudes considered were those within the lower constant-temperature region of the atmosphere (40,000 to 120,000 ft). The extent of the laminar boundary layer was determined approximately at each condition as a function of the variables considered.

Author : Robert D. Quinn
Publisher :
ISBN 13 :
Total Pages : 38 pages
Book Rating : 4.96/5 ( download)

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Download or read book A Method for Calculating Transient Surface Temperatures and Surface Heating Rates for High-speed Aircraft written by Robert D. Quinn and published by . This book was released on 2000 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a method that can calculate transient aerodynamic heating and transient surface temperatures at supersonic and hypersonic speeds. This method can rapidly calculate temperature and heating rate time-histories for complete flight trajectories. Semi-empirical theories are used to calculate laminar and turbulent heat transfer coefficients and a procedure for estimating boundary-layer transition is included. Results from this method are compared with flight data from the X-15 research vehicle, YF-12 airplane, and the Space Shuttle Orbiter. These comparisons show that the calculated values are in good agreement with the measured flight data.

Author : National Aeronautics and Space Administration (NASA)
Publisher :
ISBN 13 : 9781726152518
Total Pages : 36 pages
Book Rating : 4.10/5 ( download)

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Download or read book A Method for Calculating Transient Surface Temperatures and Surface Heating Rates for High-Speed Aircraft written by National Aeronautics and Space Administration (NASA) and published by . This book was released on 2018-08-27 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a method that can calculate transient aerodynamic heating and transient surface temperatures at supersonic and hypersonic speeds. This method can rapidly calculate temperature and heating rate time-histories for complete flight trajectories. Semi-empirical theories are used to calculate laminar and turbulent heat transfer coefficients and a procedure for estimating boundary-layer transition is included. Results from this method are compared with flight data from the X-15 research vehicle, YF-12 airplane, and the Space Shuttle Orbiter. These comparisons show that the calculated values are in good agreement with the measured flight data.Quinn, Robert D. and Gong, LeslieArmstrong Flight Research CenterSURFACE TEMPERATURE; COMPUTATION; PROCEDURES; TRANSIENT HEATING; ESTIMATING; SUPERSONIC SPEED; SPACE SHUTTLE ORBITERS; YF-12 AIRCRAFT; BOUNDARY LAYER TRANSITION; HEAT TRANSFER COEFFICIENTS; LAMINAR HEAT TRANSFER; RESEARCH VEHICLES...

Author : United States. National Advisory Committee for Aeronautics
Publisher :
ISBN 13 :
Total Pages : 944 pages
Book Rating : 4.38/5 ( download)

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Download or read book Technical Note - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1952 with total page 944 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Author : Kenneth Margolis
Publisher :
ISBN 13 :
Total Pages : 724 pages
Book Rating : 4.55/5 ( download)

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Download or read book Supersonic Wave Drag of Nonlifting Sweptback Tapered Wings with Mach Lines Behind the Line of Maximum Thickness written by Kenneth Margolis and published by . This book was released on 1948 with total page 724 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wave drag equations are derived for rhombic-profile tapered wings with maximum-thickness line swept less than the Mach line. Variations in drag with taper ratio, aspect ratio, sweepback, and Mach number are determined. Calculations are presented for representative plan forms and for a family of wings having equal root bending stress.

Author : United States. National Advisory Committee for Aeronautics
Publisher :
ISBN 13 :
Total Pages : 1370 pages
Book Rating : 4.14/5 ( download)

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Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1949 with total page 1370 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Author : Warren A. Tucker
Publisher :
ISBN 13 :
Total Pages : 738 pages
Book Rating : 4.21/5 ( download)

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Download or read book Characteristics of Thin Triangular Wings with Triangular-tip Control Surfaces at Supersonic Speeds with Mach Lines Behind the Leading Edge written by Warren A. Tucker and published by . This book was released on 1948 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical analysis, based on the linearized equation for supersonic flow, of characteristics of triangular-tip control surfaces on thin triangular wings. By restriction to case for which Mach lines from wing apex lie behind the leading edge, a simplified treatment was possible; results of previous work on lift of triangular wings could be used to derive expressions for lift effectiveness, pitching moment, rolling-moment effectiveness, hinge moment due to control deflection, and hinge moment due to angle of attack. Comparisons were made with two-dimensional case.

Author : Robert D. Quinn
Publisher :
ISBN 13 :
Total Pages : 48 pages
Book Rating : 4.89/5 ( download)

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Download or read book Real-time Aerodynamic Heating and Surface Temperature Calculations for Hypersonic Flight Simulation written by Robert D. Quinn and published by . This book was released on 1990 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Author : W. E. Moeckel
Publisher :
ISBN 13 :
Total Pages : 674 pages
Book Rating : 4.13/5 ( download)

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Download or read book Use of a Characteristic Surfaces for Unisymmetrical Supersonic Flow Problems written by W. E. Moeckel and published by . This book was released on 1949 with total page 674 pages. Available in PDF, EPUB and Kindle. Book excerpt: Application of the method of characteristics to the linearized three-dimensional equation results in a relatively simple system of difference equations that can be used to compute the supersonic flow past boundaries for which no other linearized solutions are available.