TY - GEN
T1 - Reduction of aerodynamic heating and drag with opposing jet through extended nozzle in high enthalpy flow
AU - Morimoto, Naoki
AU - Aso, Shigeru
AU - Tani, Yasuhiro
PY - 2014/1/1
Y1 - 2014/1/1
N2 - The experimental and numerical investigations of an opposing jet through an extended nozzle are described. The opposing jet through the extended nozzle is a new type of thermal protection de- vices combining an opposing jet and a forward facing spike. The experimental measurements of the heat flux distribution on a hemispheric- cylindrical blunt test model were conducted in a free piston shock tunnel in Kyushu University. The present test flow condition is 5,600 m/s and Mach number at 6.6. The shock tunnel testing demonstrates capabilities of this device reduc- ing the heat flux up to 92% in hypersonic and high enthalpy flow. In addition, axisymmetric Navier-Stokes numerical simulations were car- ried out. The numerical simulations show reduc- Tion of both aerodynamic heating and drag with precise explanations of the flow field structure.
AB - The experimental and numerical investigations of an opposing jet through an extended nozzle are described. The opposing jet through the extended nozzle is a new type of thermal protection de- vices combining an opposing jet and a forward facing spike. The experimental measurements of the heat flux distribution on a hemispheric- cylindrical blunt test model were conducted in a free piston shock tunnel in Kyushu University. The present test flow condition is 5,600 m/s and Mach number at 6.6. The shock tunnel testing demonstrates capabilities of this device reduc- ing the heat flux up to 92% in hypersonic and high enthalpy flow. In addition, axisymmetric Navier-Stokes numerical simulations were car- ried out. The numerical simulations show reduc- Tion of both aerodynamic heating and drag with precise explanations of the flow field structure.
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M3 - Conference contribution
AN - SCOPUS:84910675880
T3 - 29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014
BT - 29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014
PB - International Council of the Aeronautical Sciences
T2 - 29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014
Y2 - 7 September 2014 through 12 September 2014
ER -