Hypersonic Laminar and Turbulent Heat Transfer for Slightly Blunted Slender Cones PDF Download
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Author: W. Carson Lyons
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 284
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Book Description
Author: W. Carson Lyons
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 284
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Book Description
Author: A. Wortman
Publisher:
ISBN:
Category :
Languages : en
Pages : 23
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Book Description
A formula is developed for the calculation of heat transfer through the turbulent boundary layer on slightly blunted slender cones. The combination of the modified Reynolds analogy with approximate relations between shock layer and free stream con ditions leads to a final equation in which the heat transfer is proportional to the free stream density and velocity raised to the 0.82 and 3.10 powers, respectively. The validity of the ap proach is demonstrated by flow field studies uti lizing the teethod of characteristics which indi cate that the inviscid flow field becomes essen tially independent of axial coorannates at a dis tance of 10 to 20 nose radii downstream of the nose. Because of the simplicity of the relation it is possible to obtain analytical expressions for total heat input during re-entry into the earth's atmosphere and also relations for maximum heat transfer rate during entry. Real gas prop erties are used and the equations are shown to be sufficiently accurate for most calculations of heat transfer to the conical part of the body where the flow field assumptions of constant den sity and constant velocity at the edge of the boundary layer are applicable. (Author).
Author: Donald M. Wilson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 94
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Book Description
Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author).
Author: David E. Boylan
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 68
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The report presents heat-transfer-rate measurements on sharp and blunt 10-deg half-angle cones at angles of attack between -9 and +10 deg in a low-density, hypersonic wind tunnel. Circumferential and longitudinal distributions are presented for cold wall conditions for a range at Mach and Reynolds numbers. The effect of source-like flows was studied by utilizing both conical and contoured expansion nozzles with the same free-stream similarity parameters and model wall temperatures. Comparisons are made with previously published experimental and theoretical results. (Author).
Author: N. B. Wood
Publisher:
ISBN:
Category :
Languages : en
Pages : 41
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Author: Charles E. Wittliff
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1460
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: W. Carson Lyons (Jr.)
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 72
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Book Description
A computer program is presented for calculating the various components comprising the total drag coefficient for slightly blunted slender cones. The program is applicable for either the case of a completely laminar boundary layer or where transition occurs on the cone. Weak viscous interaction effects are taken into account. Local flow properties which exist at the outer edge of the boundary layer along the cone are also computed. (Author).
Author: Albert H. Boudreau
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 18
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Author:
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 100
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