Design of supersonic aircraft and missiles requires information about heat transfer coefficients and temperature recovery factors for supersonic speeds that extend over wide range of Reynolds number; extension of investigation reported in Tech Note 3303, indexed in Engineering Index 1954 p 9, to measurement of Mach number of 2.06.
Turbulent-heat-transfer measurements at Mach number of 2.06
NACA -- Tech Note
1955
20 pages
Report
Englisch
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Turbulent-heat-transfer measurements at a Mach number of 2.06
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