Flat spin of slender bodies at high angles of attack

Kubota, Hirotoshi; Arai, Isao; Matsuzaka, M.

doi:10.2514/3.28365

Cited by 26 publications

(3 citation statements)

References 7 publications

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“…8) It is already reported, however, that the Reynolds number can significantly affect CY and the asymmetry of the flowfield, particularly at turbulent transition (as in this work). 20) Thus, we would like to simulate the flowfields at different Reynolds numbers (e.g., flight Reynolds number) in the future. Such a work on Reynolds effects is deferred to the future work.…”

Section: % 90% 10% 0%mentioning

confidence: 99%

Numerical Analysis on Reusable Rocket Aerodynamics with Reduced-Yaw-Force Configurations

Inatomi

Kitamura

Nonaka

2019

AEROSPACE TECHNOLOGY JAPAN

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It is known that aerodynamic characteristics of a slender body vary substantially at high angles-of-attack (AoAs), and then, will have strong impacts on its flight. For, example, the yaw force makes flight unstable. In this study, we investigated the relation between the yaw force and the configuration, and details of flowfield around the slender-bodied-vehicle numerically. The configuration consisting of "nose cone" and "square aftbody" parts was employed as the baseline, and then, compared with other three configurations having different fineness ratios. According to our computed results, in the case of 50 degrees of AoA, the longer the model became, the more asymmetry appeared: yaw force and asymmetry were found to be attributed not only to the length of the body, but also to the nose bluntness. On the contrary, in the case of 140 degrees, the shorter the model became, the more asymmetry appeared. Furthermore, the large nose bluntness increased CY. Interestingly, this trend is totally opposite to that observed at 50 degrees. It had been considered that the large nose bluntness and the small fineness ratio can reduce asymmetry and CY, however, this study showed that it is not true in the case over 90 degrees, due to complex wake flow structure discovered in the present numerical simulations.

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confidence: 99%

Numerical Analysis on Reusable Rocket Aerodynamics with Reduced-Yaw-Force Configurations

Inatomi

Kitamura

Nonaka

2019

AEROSPACE TECHNOLOGY JAPAN

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“…These negative coefficients were obtained through data reduction from free-flight tests of projectiles and thus can be used as the foundation for studying aerodynamic nonlinearities. In fact, several studies over the last decades [4][5][6][7][8][9][10][11][12][13] have focused on the nonlinear aerodynamic characteristics of slender bodies at high angles of attack. In Jernell's experiment, 4 aerodynamic characteristics of slender bodies with various fineness ratios were studied at very high angles of attack (more than 90 deg).…”

Section: Introductionmentioning

confidence: 99%

The cubic pitching moment coefficient of spin-stabilized projectiles

Chang

Zhang

Wei³

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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This technical note presents a feasible method to effectively predict the cubic pitching moment coefficient for spin-stabilized projectiles. First, a surrogate model for predicting the cubic moment coefficient is constructed by using the Kriging method to relevant published data of several typical spin-stabilized projectiles. The result of a wind tunnel test validates the accuracy of the Kriging prediction, implying that this prediction model complements the current research literature. Second, the global sensitivity analysis combined with this prediction model is used to assess the effect of the shape parameters of spin-stabilized projectiles on the cubic pitching moment coefficient. As a result, the relationship between the shape parameters and the nonlinear pitching moment coefficient is preliminarily explored. The results of an example show that the cylindrical part length, the head shape parameter and the nose length have greater influence, whereas the boat-tail length has the weakest influence.

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“…Many studies investigating aerodynamic characteristics of slender bodies at high angle of attack have been conducted [8][9][10], but only a limited number of these studies focus on AOAs of more-than-90-degrees or pitching moment characteristics. In Jernell's experiment [11], aerodynamic characteristics of slender bodies with various cross-I sections and fineness ratios were explored for AOAs between -5 and 185 degrees and at supersonic Mach numbers between 1.50 and 2.86.…”

Section: Introductionmentioning

confidence: 99%

High Angle-of-Attack Pitching Moment Characteristics of Slender-Bodied Reusable Rocket

Aogaki

Kitamura

Nonaka

2018

Journal of Spacecraft and Rockets

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The development of a fully reusable vertical-takeoff-and-vertical-landing (VTVL) rocket is indispensable for reducing space transportation costs. However, there are many technical issues associated with such vehicles, such as the safe execution of a turnover maneuver during return flight. It is known that a relatively desirable pitching moment characteristic for turnover can be accomplished by employing a slender body configuration, but the reason for this is not well understood. In this study, we carried out a delayed detached-eddy simulation (DDES) on the aerodynamic characteristics of such a slender-bodied reusable rocket for angles of attack between 0 and 180 degrees using unstructured compressible computationalfluid-dynamics (CFD). We also conducted inviscid calculations in order to distinguish the pitching moment contribution of the body configuration itself from the effects of viscosity and turbulence. It was found that two types of vortices were formed at 0-90 degrees, and also these vortices affected the pitching moment distribution. We also observed three types of vortices generated at 90-180 degrees. Combined with the results of the inviscid simulation, we concluded that the pitching moment characteristic is greatly impacted by the behaviors of these vortices and bubbles.

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Flat spin of slender bodies at high angles of attack

Cited by 26 publications

References 7 publications

Numerical Analysis on Reusable Rocket Aerodynamics with Reduced-Yaw-Force Configurations

Numerical Analysis on Reusable Rocket Aerodynamics with Reduced-Yaw-Force Configurations

The cubic pitching moment coefficient of spin-stabilized projectiles

High Angle-of-Attack Pitching Moment Characteristics of Slender-Bodied Reusable Rocket

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