Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 PDF Download
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Author: Davis H. Crawford Publisher: ISBN: Category : Aeronautics Languages : en Pages : 680
Book Description
At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Author: Davis H. Crawford Publisher: ISBN: Category : Aeronautics Languages : en Pages : 680
Book Description
At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Author: Leon H. Schindel Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 114
Book Description
This AGARDograph is a systematic collection of experimental results for use of engineers and designers, limited to externally carried, unpowered, unguided stores. In the sections dealing with store trajectories, the physical situation is described, the method of solution is indicated, and the final results are presented. Emphasis is on store motion in traversing the parent aircraft flowfield, with criteria for safe separation and methods of calculating flight path. Windtunnel test techniques are described, and some information on flight testing given. Analytical treatment is compared with flight and tunnel results. There are brief mentions of ejection systems and the effect of stores on aircraft performance.
Author: W. L. Bade Publisher: ISBN: Category : Languages : en Pages : 236
Book Description
A computer program for calculating quasi-one-dimensional gas flow in axisymmetric and two-dimensional nozzles and rectangular channels is presented. Flow is assumed to start from a state of thermochemical equilibrium at a high temperature in an upstream reservoir. The program provides solutions based on frozen chemistry, chemical equilibrium, and nonequilibrium flow with finite reaction rates. Electronic nonequilibrium effects can be included using a two-temperature model. An approximate laminar boundary layer calculation is given for the shear and heat flux on the nozzle wall. Boundary layer displacement effects on the inviscid flow are considered also. Chemical equilibrium and transport property calculations are provided by subroutines. The code contains precoded thermochemical, chemical kinetic, and transport cross section data for high-temperature air, CO2-N2-Ar mixtures, helium, and argon. It provides calculations of the stagnation conditions on axisymmetric or two-dimensional models, and of the conditions on the flat surface of a blunt wedge. The primary purpose of the code is to describe the flow conditions and test conditions in electric arc heated wind tunnels.
Author: Davis H. Crawford
Author: Davis H. Crawford
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Aeronautics and Space Administration
Author: Leon H. Schindel
Author: W. L. Bade
Author: Library of Congress
Author: Library of Congress
Author: Daniel W. Lester