Effects of nose angle and Mach number on transition on cones at supersonic speeds /

Effects of nose angle and Mach number on transition on cones at supersonic speeds / K.R. Czarnecki and Mary W. Jackson.

An investigation has been made to determine the transition characteristics of a group of smooth, sharp-nosed cones varying from 10 degrees to sixty degrees in included apex angle over a Mach number range from 1.61 to 2.20 and a range of Reynolds number per foot from about 1.5 million to 8 million. I...

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Bibliographic Details
Main Author: Czarnecki, K. R.
Corporate Author: United States. National Advisory Committee for Aeronautics
Other Authors: Jackson, Mary W.
Format: Government Document Book
Language:English
Published: Washington : National Advisory Committee for Aeronautics, [1958]
Series:Technical note (United States. National Advisory Committee for Aeronautics) ; 4388.
Subjects:
Noses (Aircraft)
Cone > Aerodynamics.
Aerodynamics, Supersonic.
Boundary layer.

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Call Number: Y 3.N 21/5:6/4388
Y 3.N 21/5:6/4388 Available Place a Hold

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