Large carbon cluster thin film gauges for measuring aerodynamic heat transfer rates in hypersonic shock tunnels

2015 ◽  
Vol 26 (2) ◽  
pp. 025901 ◽  
Author(s):  
S Srinath ◽  
K P J Reddy
1967 ◽  
Vol 27 (3) ◽  
pp. 503-512 ◽  
Author(s):  
B. E. Edney

The theory of Fay & Riddell (1958) is used to calculate stagnation temperatures from stagnation-point heat-transfer rates measured in the working section of a hypersonic gun tunnel at a Mach number of 9·8. Measurements using both thin-film gauges and calorimeters are described. The temperatures measured using this technique are found to be lower than predicted by Lemcke (1962) from measurements of shock strengths and final pressures in the gun barrel. This discrepancy is attributed to heat losses in the barrel during the initial shock compression cycle. A simple theory is developed to take into account these losses. There is good agreement between this theory and the experimental results.


Author(s):  
Hoki Lee ◽  
T. A. Quy ◽  
C. D. Richards ◽  
D. F. Bahr ◽  
R. F. Richards

Experimental and numerical results are presented for evaporative heat transfer from ten-micron square open-top channels. The radial channels are fabricated in epoxy photoresist on a two micron thick silicon membrane. The working fluid is pumped by capillary forces from a reservoir at the edge of the silicon membrane into the channels where it evaporates. The electrical power dissipated in a thin-film heater in the center of the membrane, the conduction heat transfer rate radially out of the membrane, and the rate of evaporation of the working fluid are measured. A three-dimensional finite difference, time-domain integration is used to predict sensible and latent heat transfer rates. Only 5-10% of the energy dissipated as heat in the thin film heater is carried away as latent heat by the evaporating working fluid. Computed temperatures and heat transfer rates are shown to match the experimental results.


2013 ◽  
Vol 135 (12) ◽  
Author(s):  
C. S. Kumar ◽  
K. P. J. Reddy

Heat transfer rates measured in front and to the side of a protrusion on an aluminum flat plate subjected to hypersonic flow at zero angle of attack are presented for two flow enthalpies of approximately 2 MJ/kg and 4.5 MJ/kg. Experiments were conducted in the hypersonic shock tunnel (HST2) and free piston driven HST3 at a freestream Mach number of 8. Heat transfer data was obtained for different geometries of the protrusion of a height of 4 mm, which is approximately the local boundary layer thickness. Comparatively high rates of heat transfer were obtained at regions of flow circulation in the separated region, with the hottest spot generally appearing in front of the protuberance. Experimental values showed moderate agreement with existing empirical correlations at higher enthalpy but not at all for the lower enthalpy condition, although the correlations were coined at enthalpy values nearer to the lower value. Schlieren visualization was also done to investigate the flow structures qualitatively.


Author(s):  
Xuelei Nie ◽  
Xuegong Hu ◽  
Suresh V. Garimella ◽  
Dawei Tang

Evaporation of the thin film formed in microgrooves is associated with high heat transfer rates. One of the factors that limits this heat transfer is the capacity of the microgroove to drive fluid into the thin film. The mass flow rate and mass flux in the corner flow region of a microgroove is experimentally and theoretically investigated in this work. The experiments yield the speed at which wetting occurs in vertical microgrooves. The wetting speed reflects the balance between the gravitational, viscous and capillary forces acting on the film. A force balance is also conducted on the liquid in the corner flow region of the microgrooves. This analysis allows a calculation of the maximum amount of liquid that the microgrooves can drive to the evaporating surface in the corner flow region, which in turn determines the maximum evaporation rate in this localized area.


1970 ◽  
Author(s):  
N.V. Antonishin ◽  
S. S. Zabrodsky ◽  
L.E. Simchenko ◽  
V.V. Lushchikov

1974 ◽  
Author(s):  
S. Koncar-Djurdjevic ◽  
M. Mitrovic ◽  
S. Cvijovic ◽  
G. Popovic ◽  
Dimitrije Voronjec

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