Add to ORKGAn experimental investigation was conducted to determine the coolant-side, heat transfer coefficients for a liquid cooled, hydrogen-oxygen rocket thrust chamber. Heat transfer rates were determined from measurements of local hot gas wall temperature, local coolant temperature, and local coolant pressure. A correlation incorporating an integration technique for the transport properties needed near the pseudocritical temperature of liquid hydrogen gives a satisfactory prediction of hot gas wall temperatures
Correlation equations for predicting gas-side heat transfer of axisymmetric rocket engine nozzle
Wall temperature and heat transfer patterns in liquid-propellant rocket thrust chamber coolant chann...
The analysis, design, fabrication, and testing of a liquid rocket engine thrust chamber which is gas...
Hot-gas side heat-transfer rates for liquid oxygen and hydrogen propellant rocket nozzl
Heat-transfer rates and coefficients and coolant pressure loss characteristics in regeneratively coo...
Heat-transfer coefficients were obtained on a thrust chamber which simulated the geometry of the NER...
The potential benefits of simultaneously using hydrogen and oxygen as rocket engine coolants are des...
Cryogenic para hydrogen heat transfer data at near critical pressures and temperatures for advanced ...
Hydrogen and Methane are two fluids that are either used or in discussion as propellants for upper a...
Single correlating equation for single phase forced convection heat transfer coefficients for turbul...
An experimental program using hydrogen and oxygen as the propellants and supercritical liquid oxygen...
Hydrogen and Methane are two fluids that are either used or in discussion as propellants for upper a...
Hydrogen and Methane are two fluids that are either used or in discussion as propellants for upper a...
A priori prediction of rocket engine combustor flowfields is extremely difficult due to a number of ...
An experimental investigation was conducted to determine the hot-gas-side heat transfer characterist...
Correlation equations for predicting gas-side heat transfer of axisymmetric rocket engine nozzle
Wall temperature and heat transfer patterns in liquid-propellant rocket thrust chamber coolant chann...
The analysis, design, fabrication, and testing of a liquid rocket engine thrust chamber which is gas...
Hot-gas side heat-transfer rates for liquid oxygen and hydrogen propellant rocket nozzl
Heat-transfer rates and coefficients and coolant pressure loss characteristics in regeneratively coo...
Heat-transfer coefficients were obtained on a thrust chamber which simulated the geometry of the NER...
The potential benefits of simultaneously using hydrogen and oxygen as rocket engine coolants are des...
Cryogenic para hydrogen heat transfer data at near critical pressures and temperatures for advanced ...
Hydrogen and Methane are two fluids that are either used or in discussion as propellants for upper a...
Single correlating equation for single phase forced convection heat transfer coefficients for turbul...
An experimental program using hydrogen and oxygen as the propellants and supercritical liquid oxygen...
Hydrogen and Methane are two fluids that are either used or in discussion as propellants for upper a...
Hydrogen and Methane are two fluids that are either used or in discussion as propellants for upper a...
A priori prediction of rocket engine combustor flowfields is extremely difficult due to a number of ...
An experimental investigation was conducted to determine the hot-gas-side heat transfer characterist...
Correlation equations for predicting gas-side heat transfer of axisymmetric rocket engine nozzle
Wall temperature and heat transfer patterns in liquid-propellant rocket thrust chamber coolant chann...
The analysis, design, fabrication, and testing of a liquid rocket engine thrust chamber which is gas...