Temperature recovery factors on a slender 12° cone-cylinder at Mach numbers from 3.0 to 6.3 and angles of attack up to 45°
Publisher: NACA
Published: 1955
Place of publication: Washington, D.C.
Language: eng
Number of pages: 62
Subjects: Heat--Transmission; Laminar boundary layer--Research; Aerodynamics--Research.
Description: <a href="http://uf.catalog.fcla.edu/uf.jsp?st=UF003854733&ix=nu&I=0&V=D&pm=1" rel="nofollow">http://uf.catalog.fcla.edu/uf.jsp?st=UF003854733&ix=nu&I=0&V=D&pm=1</a>