• Version
• 74 Downloads
• 591.45 KB File Size
• 1 File Count
• January 29, 2017 Create Date
• January 29, 2017 Last Updated

National Advisory Committee for Aeronautics, Technical Notes - Turbulent Heat Transfer Measurements at a Mach Number of 2.06

Turbulent-heat—transfer measurements were obtained through the use
of an axially symmetric annular nozzle which consists of an inner shaped
center body and an outer cylindrical sleeve. Measurements taken along
the outer sleeve gave essentially flat—plate results that are free from
wall interference and corner effects for a Mach number of 2.06 and for a

Reynolds nmnber range of 1.7 x 106 to 8.8 x 107. The heat-transfer
coefficients are in good agreement with available data from V-2 rockets
and also check the Rubesin theory and the Van Driest theory for a Mach
number of 2.0 and for a ratio of inner—surface to free-stream temperature
of 1.8. The temperature—recovery factors are approximately 0.5 percent
lower than the factors given in NASA TN 2077 for a Mach number of 2.h.

The design of supersonic aircraft and missiles requires engineering
information about heat-transfer coefficients and temperature-recovery
factors for supersonic speeds that extend over a wide range of Reynolds
number. In reference 1, local—heat~transfer-coefficient measurements were
presented for a Mach number of 5.05. Good.agreement of these results with
theoretical and experimental work was obtained. This method of testing
and reduction of data is readily adaptable to obtaining accurate measure—
ments over an extended range of both Mach and Reynolds numbers.

The purpose of this investigation is to extend the work initiated in
reference 1 to a Mach number of 2.06. The same type of apparatus and
method of reducing the data were used in this investigation as were employed
in reference 1. The range of Reynolds number for which measurements were
obtained is from 1.7 X 106 to 8.8 X 107. The results cover a tempera—
ture difference of approximately 200 at #0 seconds after starting to
approximately 50 at l20 seconds after starting. The average value of the
ratio 3f inner—surface temperature to free-stream temperature TW/Tco
was 1.