A Procedure for Calculating the Boundary-Layer Development in the Region of Transition From Laminar to Turbulent Flow

A REVIEW OF SOME RECENT DEVELOPMENTS IN HYPERSONIC FLOW**This work was supported by the United States Air Force through the Office of Scientific Research, Air Research and Development Command, under Contract AF 49 (638)-217, and through the Aeronautical Research Laboratory of Wright Air Development Center, under Contract No. 33 (616)-3265.

“…The transition Reynolds number referred to the momentum thickness Re Q is of the order of 300. 88 for the transitional and flat plate external conditions for the turbulent part, is also shown in Fig. Again the presence of large entropy gradients outside the boundary layer can affect this relation.…”

“…The curve presented corresponds to a point in the subsonic region of the body. 88. The data have been obtained at the Polytechnic Institute of Brooklyn by means of the shroud technique.…”

Laminar, Transitional and Turbulent Heat Transfer to a Cone-Cylinder-Flare Body at Mach 8.0

“…The model was constructed of 304 stainless steel having a wall thickness of 0.050". Table II (4) e dS e where U du…”