Heat Transfer and Pressure Measurement on a 5-inch Hemispherical Concave Nose at a Mach Number of 2.0


Book Description

Abstract: The concave-nose stagnation-point heating is 40 percent of that of a hemisphere nose shape having the same diameter. At angles of attack of ℗±5© and ℗± 10© there is no increase in heating of the nose. Total pressures behind the shock were experienced up to 60© on the concave part for all angles of attack. The tests were made under sea-level conditions for a Reynolds number per foot of about 14 x 106.
















Experimental Convective Heat Transfer to a 4-inch and 6-inch Hemisphere at Mach Numbers from 1.62 to 3.04


Book Description

Abstract: Equilibrium temperatures and heat-transfer coefficients for a hemispherical nose have been measured for Mach numbers from 1.62 to 3.04. Heat transfer to the surface of the hemisphere was presented as Stanton number against Reynolds number for various surface heating conditions. Heat transfer at the stagnation point has been measured and correlated with theory. Transition from a laminar to a turbulent boundary layer was obtained at Reynolds numbers of approximately 1 x 106 corresponding to a region on the body located between 45© and 60© from the stagnation point.







Heat Transfer and Pressure Measurement on a 5-inch Hemispherical Concave Nose at a Mach Number of 2.0


Book Description

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