Author: I. A. CampbellPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
An Experimental and Numerical Study of Hypersonic Flow Over a Spherically Blunted 18 Degrees Semi-angle Cone
Author: I. A. CampbellScientific and Technical Aerospace Reports
Author: Applied Mechanics Reviews
Author: An Experimental and Theoretical Investigation of the Pressure Distribution and Flow Fields of Blunted Cones at Hypersonic Mach Number
Author: Joseph W. ClearyPublisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 82
Book Description
An Experimental and Numerical Study of Hypersonic Flow Over Power-law Bodies
Author: H. G. HornungTechnical Abstract Bulletin
Author: A Theoretical and Experimental Study of Hypersonic Flow Over Flared Bodies at Incidence
Author: John V. RakichPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
Book Description
Effects of Angle of Attack and Bluntness on the Hypersonic Flow Over a 15 ̊semiapex Cone in Helium
Author: Joseph W. ClearyPublisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 52
Book Description
Government Reports Announcements
Author: Investigation of Hypersonic Flow Over Blunted Plates and Cone
Author: J. P. RHUDYPublisher:
ISBN:
Category :
Languages : en
Pages : 48
Book Description
Heat transfer rates and pressure distributions on three basic shapes were investigated at a nominal Mach number of 8 and free-stream Reynolds numbers from 0.43 to 3.4 million per foot. The models were a 0.4-in. nose radius, spherically blunted, 15-deg half-angle cone; two flat plate models with 0. 10-in. and 0. 50-in. cylindrical blunting; and a modified leading-edge plate with auxiliary planes to produce changing body shape within the elliptic flow region. The tests produced data showing the effect on heat transfer rates of the interaction of the essentially inviscid, rotational flow behind the bow shock with the viscous boundary layer on the body. The results of pressure distribution tests show good agreement with theory. Heat transfer rates over the entire body were accurately predicted through the use of outer-edge boundary-layer conditions obtained from isentropic expansion from normal-shock stagnation conditions.