The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight PDF full book. Access full book title The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight by Richard Scherrer. Download full books in PDF and EPUB format.
Author: Richard Scherrer
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 542
Get Book Here
Book Description
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: Richard Scherrer
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 542
Get Book Here
Book Description
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: George P. Wood
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 34
Get Book Here
Book Description
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: A. J. Eggers (Jr.)
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 20
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 652
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 988
Get Book Here
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1276
Get Book Here
Book Description
Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1286
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 630
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 242
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 30
Get Book Here
Book Description
