Aerodynamic Measurements and Computational Analyses in Hypersonic Rarefied Flows

Ozawa, Takashi; Suzuki, Toshiyuki; Fujita, Kazuhisa

doi:10.2514/1.j053889

Cited by 12 publications

(2 citation statements)

References 28 publications

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“…For flight vehicles, aerothermal responses are crucial in the testing of flight parameters for an infrared radiation tracking measurement system, such as coordinate, attitude, and yaw [1][2][3][4]. Furthermore, aerothermal analysis methods are also essential to design the thermal protection structure and infrared stealth technology [5][6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Dynamic Aerothermal Analysis of a Cone-Cylinder Flight Body

Zhang

Jia

Mkumbuzi

et al. 2020

International Journal of Aerospace Engineering

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Exploring the aerothermal characteristic of a flight body has great military applications in tracking, locating, thermal protection, and infrared stealth technologies. Available studies are mostly focused on the transient aerothermal characteristics of vehicles in some specific flight datum, which are not able to satisfy the requirements in real-time tracking for an infrared system. This paper probes into a method of dynamic thermal analysis of a cone-cylinder flight body with a high spinning speed. Firstly, a theoretical model for analyzing the dynamic aerothermal characteristics is established using the thermal node-network method. Then, trajectory datum and the convective heat-transfer coefficients are solved simultaneously. Besides, the trajectory datum in supersonic, transonic, and subsonic regimes is separately defined as the boundary conditions, and fluid-thermal analysis methods are implemented by a combination of sliding mesh and multicoordinate approaches. Finally, the flow characteristics are analyzed and compared with disregarding the rotational speed. The results demonstrate that there are significant differences between the two cases, especially at the high-speed regimes. This study further confirms that it is essential to conduct the aerothermal analysis from a dynamic point of view, and taking the impacts of coupling motion into account is also of vital importance.

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Section: Introductionmentioning

confidence: 99%

Dynamic Aerothermal Analysis of a Cone-Cylinder Flight Body

Zhang

Jia

Mkumbuzi

et al. 2020

International Journal of Aerospace Engineering

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“…6) However, this wind tunnel is currently limited for inert gases, such as nitrogen. 7) Thus, we plan to expand this wind tunnel capability into CO 2 flows for Mars missions.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Rarefaction and Condensation Effects in Hypersonic Rarefied Flows

Ozawa

Suzuki

Fujita

2016

AEROSPACE TECHNOLOGY JAPAN

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The improvement of prediction accuracy for rarefied aerodynamics is one of the important factors for space missions. In order to improve rarefied aerodynamic prediction, rarefaction and condensation effects have been investigated experimentally and numerically in this work. Pitot pressure measurements for N 2 nozzle flows have been carried out in the hypersonic rarefied wind tunnel (HRWT). The rarefaction phenomenon was found to impact the measurements, and thus, we have developed a rarefaction model using a bridging function, which represents the rarefaction phenomenon well on pitot pressure for hypersonic rarefied flows in HRWT. In addition, condensation effect has been analyzed for N 2 and CO 2 nozzle flows in the HRWT test section. Although condensation does not impact rarefied aerodynamic measurements for N 2 , stagnation temperature should be higher than 700 K for CO 2 to generate hypersonic rarefied flows for M > 10, Kn > 0.1 and reduce the risk of condensation phenomenon.

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