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By H. Schuh, R. L. Bisplinghoff and W. S. Hemp (Auth.)

ISBN-10: 0080101976

ISBN-13: 9780080101972

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Extra resources for Heat Transfer in Structures

Example text

If the level of disturbances is low, the HEAT TRANSFER IN HIGH SPEED FLIGHT 37 distance is large between the instability and the transition point; the latter is, however, important for the heatflowto the wall. In most cases transition does not occur at a fixed point, but spreads over a region which may be considerable in extent. Observations seem to indicate that the instantaneous flow at any point and at any time is either fully laminar or fully turbulent. In the transition region the flow fluctuates between the laminar and turbulent states, turbulent spots originating at random and flowing downstream with the fluid while spreading in size.

It is, however, desirable for aeronautical applications to know at least roughly the position of the transition point or its most forward and most aft point. Space permits only the presentation of a few results: otherwise the reader is referred to the few survey articles, Refs. 3, from which most of the extensive literature may be gathered. In the following figures results are presented for the influence on transition of a number of parameters, taken one at a time. In these experiments particular efforts were made to keep external disturbances at as u x low a level as possible.

COHEN, N . , Boundary-layer similar solutions and correlation equations for laminar heat-transfer distribution in equilibrium air at velocities up to 41,100 feet per second, NASA T R R-118 (1961). BRINICH, P. F . and SANDS, N . , Effect of bluntness on transition for a cone and a hollow cylinder at Mach 3-1, NACA T N 3979 (1957). MOECKEL, W. , Some effects of bluntness on boundary-layer transition and heat transfer at supersonic speeds, NACA Rep. 1312 (1958). BURBANK, P. B. and HODGE, B. , Distribution of heat transfer on a 10° cone at angles of attack from 0° to 15° for Mach numbers of 2-49 to 4-65 and solution of the heat transfer equation that permits complete machine calculations, NASA M E M O 6-4-59L (1959).

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Heat Transfer in Structures by H. Schuh, R. L. Bisplinghoff and W. S. Hemp (Auth.)


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