02084nam 2200553Ia 450 991069973620332120101202100951.0(CKB)5470000002405586(OCoLC)688609638(EXLCZ)99547000000240558620101202d1984 ua 0engurbn|||||||||txtrdacontentcrdamediacrrdacarrierInvestigation of the effects of pressure gradient, temperature, and wall temperature ratio on the stagnation point heat transfer for circular cylinders and gas turbine vanes[electronic resource] /by H.T. Nagamatsu and R. E. DuffyTroy, N.Y. :Rensselaer Polytechnic Institute,[1984]1 online resource (iii, 39 pages) digital, PDF fileNASA contractor report ;174667"April 1984.""Prepared for National Aeronautics and Space Administration, Lewis Research Center under grant no. NAS3-292."Includes bibliographical references (pages 36-39).Circular cylindersnasatGas turbinesnasatHeat fluxnasatHeat transfernasatHigh pressurenasatPressure gradientsnasatShock tubesnasatVanesnasatCircular cylinders.Gas turbines.Heat flux.Heat transfer.High pressure.Pressure gradients.Shock tubes.Vanes.Nagamatsu Henry T.-2006.1413158Duffy R. E1413159Rensselaer Polytechnic Institute.Lewis Research Center.GPOGPOBOOK9910699736203321Investigation of the effects of pressure gradient, temperature, and wall temperature ratio on the stagnation point heat transfer for circular cylinders and gas turbine vanes3508856UNINA