Pressure distributions on a two-dimensional blurs-nosed body at angles of attack have been determined at a Mach number of 6.0 mm the hypersonic facility of the Polytechnic Institute of Brooklyn Aerodynamics Laboratory.nThe pressure distribution results and the velocity gradient at the stagnation point are compared with the theoretical predictions.nIt is shown that the Newtonian theory does not apply for bodies where the sonic point does not fall on the same radius of curvature as the staquation point. A large reduction in stagnation point heat transfer was obtained as a result of increasing the radius of curvature of the body at the comic point over that which exists at the stagnation point of constant radius of curvature models.
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