Study of Aerodynamic Characteristics Evaluation under Hypersonic Rarefied Flows

Preliminary studies are made to determine the aerodynamic and accommodation characteristics of the wind tunnel model under hypersonic rarefied flow. In the method, the wind tunnel models are exposed to the test flow in the hypersonic rarefied wind tunnel in JAXA. The displacements of the models due to the aerodynamic forces are measured during the testing. The flowfield around the wind tunnel model in the test section is also analyzed by using the numerical calculation. In the calculation, the accommodation coefficient of wind tunnel model surface is parametrically changed. The accommodation parameter of the wind tunnel model surface is then deduced from the comparison between the calculation and the measurement. For the sphere wind tunnel model, agreement between measurement and calculation could be obtained by present method with the accommodation coefficient from 0.8 to 0.9. It is also found that the determination of accommodation parameter becomes more achievable by using the displacement along the flow direction rather than that along the horizontal direction. On the other hand, further detailed modeling is required in the numerical analysis for the flat plate model. The uncertainties in the force measurement in the HRWT are discussed in this paper.

[1]  K. Fujita,et al.  Analysis of Rarefaction Effects in the Hypersonic Rarefied Wind Tunnel , 2013 .

[2]  K. Fujita,et al.  Coupling particle simulation with aerodynamic measurement in hypersonic rarefied wind tunnel in JAXA , 2012 .

[3]  Kazuhisa Fujita,et al.  Prediction of Forebody and Aftbody Heat Transfer Rate for Mars Aerocapture Demonstrator , 2012 .

[4]  K. Fujita,et al.  Investigation of Martian-Dust Drag and Heat Transfer for Mars Sample Return Mission , 2011 .

[5]  K. Fujita,et al.  Analysis of Non-Continuum Hypersonic Flows for the Hayabusa Reentry , 2011 .

[6]  K. Fujita,et al.  Development of a Pilot Model of Hypersonic Rarefied Wind‐Tunnel , 2011 .

[7]  A. Noda,et al.  Rarefied Aerodynamics of a Super Low Altitude Test Satellite , 2009 .

[8]  W. Steckelmacher.  Molecular gas dynamics and the direct simulation of gas flows , 1996 .

[9]  G Wilmoth Richard,et al.  Comparisons of the Maxwell and CLL Gas/Surface Interaction Models Using DSMC , 1995 .

[10]  Claus Borgnakke,et al.  Statistical collision model for Monte Carlo simulation of polyatomic gas mixture , 1975 .

[11]  G. Gyarmathy,et al.  Condensation of air and nitrogen in hypersonic wind tunnels. , 1968 .

[12]  G. Thodos,et al.  Vapor pressures of liquid nitrogen between the triple and critical points , 1967 .

[13]  H. Dijk,et al.  The vapour pressure of liquid nitrogen , 1966 .

[14]  I. Vas,et al.  THE PRINCETON UNIVERSITY HIGH PRESSURE HYPERSONIC NITROGEN TUNNEL N-3. PART I. FACILITY DESCRIPTION. PART II. CALCULATION OF GAS CHARACTERISTICS AND EVALUATION OF EFFECTS OF VIBRATIONAL NON-EQUILIBRIUM. PART III. PRELIMINARY MEASUREMENTS, , 1964 .

[15]  G. Goglia.  Limit of supersaturation of nitrogen vapor expanding in a nozzle , 1961 .

[16]  W. Willmarth,et al.  The Condensation of Nitrogen in a Hypersonic Nozzle , 1952 .

[17]  Meng-Sing Liou,et al.  A Flux Splitting Scheme with High-Resolution and Robustness for Discontinuities(Proceedings of the 12th NAL Symposium on Aircraft Computational Aerodynamics) , 1994 .

[18]  F. K. Hill,et al.  The Supersaturation of Nitrogen in a Hypersonic Wind Tunnel , 1952 .