Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 /

Aerodynamic-heating data were obtained on the conical nose of model 2 between Mach numbers 1.1 to 4.0. The local Mach numbers varied from 1.0 to 3.8; these values corresponded to local Reynolds numbers from 14,000,000 to 28,000,000. The ratio of skin temperature to local static temperature varied from 1.0 to 2.3. Over most of the test range, the data were in fair agreement with Van Driest's theory for turbulent flow on a cone.Two rocket-propelled models have been flown to Mach numbers of 5.0 and 5.6. Aerodynamic-heating data were obtained from temperature measurements made at a single station on each model. In the case of model 1, data were obtained on the parabolic nose between free-stream Mach numbers of 2.3 and 5.0. The local Mach number, which is the Mach number of the airstream just outside the boundary layer at the measuring station, varied from 2.1 to 4.5; these values corresponded to local Reynolds numbers of 11,000,000 to 19,1000,000. The ratio of skin temperature to local static temperature varied 1.1 to 2.6. The experimental data when reduced to Stanton numbers were in fair agreement with values predicted by Van Driest's theory for heat transfer on the cone with turbulent flow from the nose tip.NACA Research Memorandum L55A14A."March 11, 1955."Title from cover.Includes bibliographical references (p. 11).Aerodynamic-heating data were obtained on the conical nose of model 2 between Mach numbers 1.1 to 4.0. The local Mach numbers varied from 1.0 to 3.8; these values corresponded to local Reynolds numbers from 14,000,000 to 28,000,000. The ratio of skin temperature to local static temperature varied from 1.0 to 2.3. Over most of the test range, the data were in fair agreement with Van Driest's theory for turbulent flow on a cone.Two rocket-propelled models have been flown to Mach numbers of 5.0 and 5.6. Aerodynamic-heating data were obtained from temperature measurements made at a single station on each model. In the case of model 1, data were obtained on the parabolic nose between free-stream Mach numbers of 2.3 and 5.0. The local Mach number, which is the Mach number of the airstream just outside the boundary layer at the measuring station, varied from 2.1 to 4.5; these values corresponded to local Reynolds numbers of 11,000,000 to 19,1000,000. The ratio of skin temperature to local static temperature varied 1.1 to 2.6. The experimental data when reduced to Stanton numbers were in fair agreement with values predicted by Van Driest's theory for heat transfer on the cone with turbulent flow from the nose tip.Mode of access: Internet