Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology
This report presents a detailed description and results of force and heat flux measurements conducted at the High-Enthalpy Shock Tunnel (HIEST) of the Japan Aerospace Exploration Agency (JAXA). The HB-2 standard hypersonic ballistic configuration was employed as a model. The force measurement tests used an aluminum alloy model and a three-component aerodynamic balance. An acceleration compensation technique was used to remove vibration components from the original data. Heat flux measurement tests used a chromel model with a total of 28 co-axial thermocouples press-fitted onto the surface. Time histories of temperature data were numerically integrated to determine the surface heat flux by applying one-dimensional heat conduction theory. Both force and heat tests used a conical nozzle, and a total of three enthalpy levels of 4, 8, and 11 MJ/kg and two levels of 4 and 8 MJ/kg were set for the force and heat tests, respectively. Although much higher stagnation enthalpy can be attained, relatively lower enthalpy levels were selected to compare with a blow-down type hypersonic wind tunnel and to alleviate uncertainties inherent in high-enthalpy facilities. The force test results correlated well with other hypersonic wind-tunnel data for the axial force coefficient at the enthalpy level of 4 MJ/kg, while a notable discrepancy was observed at the higher enthalpy levels of 8 and 11 MJ/kg. The real gas effects on aerodynamic characteristics are examined and discussed. In the heat test, a comparison of the heat flux distribution along the surface with data obtained in a blow-down type hypersonic wind tunnel showed good agreement in the nose part, typically within several percent. The present experiment was conducted as a series of comparative test campaigns between two hypersonic facilities in JAXA. Since the tunnel stagnation conditions and the corresponding data are tabulated in detail for each shot, the present test data are believed to serve as a complete database for evaluating aerodynamic force and heat flux data obtained at large-scale high-enthalpy shock tunnels.
Comparative force/heat flux measurements between JAXA hypersonic test facilities using standard model HB-2
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