Heat-transfer measurements on two bodies of revolution at a Mach number of 3.12 Page: 3 of 37

NACA TN 3776

Rubesin (ref. 5). Eber (ref. 2) obtained heat-transfer rates for a cone
cylinder at local Mach numbers ranging fran 0.88 to 4.65. Again, the
experimental data are well represented by the isothermal theory of
Crocco. The data presented in references 1 and 2 were obtained at tem-
peratures near the equilibrium temperature. Heat-transfer measurements
made by Decoursin, Bradfield, and Sheppard (ref. 3) on various cones and
parabolic-arc configurations at ratios of wall-to-local-free-stream tem-
perature ranging fran 2.0 to 4.8 are the only current wind-tunnel meas-
urements available for a range of surface-temperature levels. The lami-
nar data obtained on all models agree closely with the theory df Chapman
and Rubesin (ref. 5). However, the turbulent data obtained from the a
canes did not agree closely with the theory of Van Driest (ref. 6).
Previously, the effects of surface temperature on transition have
been evaluated only at relatively low Mach numbers. Reference 7 reports
the effects of surface temperature and pressure gradient on transition
under the condition of large heat transfer. The models considered were
a 9.50-apex-angle cone cylinder and a parabolic-nosed cylinder. each
with a nose fineness ratio of 6.
In this investigation, heat-transfer coefficients for the same two
models at zero angle of attack are reported for wall-to-free-stream
static-temperature ratios ranging from 1.0 to 4.4.
The investigation was conducted in the Lewis 1- by 1-foot super-
sonic wind tunnel, which operates at a Mach number of 3.12. Tests were
made at various Reynolds numbers ranging fran 2x106 to 12xl06 based on
model length. The tunnel stagnation dew point was about -350 F at all
times. Further details concerning this facility may be found in
reference 7.
The dimensions and thermocouple locations of the models used to
obtain the heat-transfer data are shown in figure 1. Both models were
constructed from a nickel alloy with a wall thickness of approximately
1/16 inch. The cone cylinder was made of monel, whereas the parabolic-
nosed cylinder was fabricated froman "K" monel. The maxnimum surface rough-
ness on each was less than 16 microinches. Each model was instrumented
with calibrated copper-constantan thermocouples of 30-gage wire. A typ-
ical tunnel installation is shown in figure 2. The theoretical wall-
pressure distributions for the two models are presented in figure 5.
These distributions were calculated using the second-order theory pre-
sented in reference 8.
Heat-transfer data were obtained by utilizing the transient tech-
nique described in detail in reference 7. Transient temperature

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Jack, John R. & Diaconis, N. S. Heat-transfer measurements on two bodies of revolution at a Mach number of 3.12, report, October 1956; (https://digital.library.unt.edu/ark:/67531/metadc56003/m1/3/ocr/: accessed April 26, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.

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