Add to ORKGAn approximate theory is developed for predicting the rate of heat transfer to the stagnation region of blunt bodies in hypersonic flight. Attention is focused on the case where wall temperature is small compared to stagnation temperature. The theoretical heat-transfer rate at the stagnation point of a hemispherical body is found to agree with available experimental data. The effect of yaw on heat transfer to a cylindrical stagnation region is treated at some length, and it is predicted that large yaw should cause sizable reductions in heat-transfer rate
Effect of coolant gas injection in the stagnation region on the surface heat transfer rates and aero...
A general method has been developed, using the methods of kinetic theory, whereby the surface temper...
Hypersonic transitional flow has been studied using the Direct Simulation Monte Carlo method. The cy...
An approximate theory is developed for predicting the rate of heat transfer to the stagnation region...
Stagnation point convective heat transfer for blunt body moving at hypersonic spee
An experimental investigation was conducted to evaluate the heat-transfer characteristics of a hyper...
An experimental investigation was made in the GALCIT hypersonic wind tunnel, leg number 1, at a nomi...
An experimental investigation was made in the GALCIT hypersonic wind tunnel, leg number 1, at a nomi...
Comparison of heat transfer rates to blunt bodies of revolution & evaluation of effects of body-nose...
Local heat-transfer coefficients, temperature recovery factors, and pressure distributions were meas...
Solution for shock layer energy equation with mass and convective heat transfer at hypersonic spee
Results are presented from recent investigations of the aeroaynamic heating rates of blunt nose shap...
Effect of coolant gas injection in the stagnation region on the surface heat transfer rates and aero...
Effect of radiative heat transfer in low Reynolds number hypersonic flow about blunt bod
Convection coefficients and heat fluxes due to aerodynamic heating on critical surfaces of hypersoni...
Effect of coolant gas injection in the stagnation region on the surface heat transfer rates and aero...
A general method has been developed, using the methods of kinetic theory, whereby the surface temper...
Hypersonic transitional flow has been studied using the Direct Simulation Monte Carlo method. The cy...
An approximate theory is developed for predicting the rate of heat transfer to the stagnation region...
Stagnation point convective heat transfer for blunt body moving at hypersonic spee
An experimental investigation was conducted to evaluate the heat-transfer characteristics of a hyper...
An experimental investigation was made in the GALCIT hypersonic wind tunnel, leg number 1, at a nomi...
An experimental investigation was made in the GALCIT hypersonic wind tunnel, leg number 1, at a nomi...
Comparison of heat transfer rates to blunt bodies of revolution & evaluation of effects of body-nose...
Local heat-transfer coefficients, temperature recovery factors, and pressure distributions were meas...
Solution for shock layer energy equation with mass and convective heat transfer at hypersonic spee
Results are presented from recent investigations of the aeroaynamic heating rates of blunt nose shap...
Effect of coolant gas injection in the stagnation region on the surface heat transfer rates and aero...
Effect of radiative heat transfer in low Reynolds number hypersonic flow about blunt bod
Convection coefficients and heat fluxes due to aerodynamic heating on critical surfaces of hypersoni...
Effect of coolant gas injection in the stagnation region on the surface heat transfer rates and aero...
A general method has been developed, using the methods of kinetic theory, whereby the surface temper...
Hypersonic transitional flow has been studied using the Direct Simulation Monte Carlo method. The cy...