supersonic configuration study, supersonic wind tunnel test, supersonic aerodynamic characteristics, reentry vehicle aerodynamics, orbital reentry vehicle, reentry body instrumentation, ionized gas temperature probe, electron number density distribution probe, sweep angle effect, communication black out region, misalignment induced rolling moment, OREX, orbital reentry experiment, lift coefficient, drag coefficient
その他のタイトル（英）
Aerodynamic characteristics of the orbital reentry vehicle experimental probe fins in a supersonic flow
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
The aerodynamic characteristics of probe fins with a sweep angle of 60 deg, which are equipped on the Orbital Reentry Experiment (OREX) vehicle to measure the surrounding ionized gas temperature and electron number density distributions in the high temperature communication black out regions, have been measured in the supersonic wind tunnel of the National Aerospace Laboratory and compared with those of the fins of 0 deg sweep angles. Since the probes are to be embeded in the boundary layer where the local Mach number is less than 2.5 over the OREX surface at a hypersonic flight speed, the aerodynamic characteristics in supersonic regions are needed to estimate the rolling moments of fins caused by the error of the installation angles. The lift coefficient slope of the probe fins decreases as the Mach number increases, being less than the values for the 0 deg sweep fins.
超音速流中における軌道再突入実験機のプローブフィンの空力特性
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