Computational Study of Aerodynamic Characteristics of Reusable Rocket at High-Angle-of-Attack

Aogaki, Takuya; Kitamura, Keiichi; Nonaka, Satoshi

doi:10.2514/6.2017-1212

Cited by 4 publications

(9 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Shimojima 5) and Kinami 6) found experimentally that the area of the nose-up moment can be made almost identical to that of the nose-down moment by using a body configuration which has a square-like crosssection. Aogaki et al 7) numerically investigated the aerodynamics of a reusable rocket in detail, including the surrounding flowfields, and clarified that wakes of such vehicles greatly affect their aerodynamic characteristics.…”

Section: Aoamentioning

confidence: 99%

See 1 more Smart Citation

Computational Study on Finned Reusable Rocket Aerodynamics during Turnover

Aogaki

Kitamura

Nonaka

2019

AEROSPACE TECHNOLOGY JAPAN

Self Cite

View full text Add to dashboard Cite

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 turnover maneuvers during return flight where the pitching moment plays a key role. It is known that aerodynamic characteristics can be controlled by installing aerodynamic devices, but the relationship between the aerodynamic characteristics and the flowfields has not been explored. To clarify this relationship using computational fluid dynamics (CFD), we investigated these flowfields and aerodynamic characteristics, in the case where we install such devices (fins) in the nose part of a reusable rocket. We found that vortices form downstream of the aerodynamic devices. For angles of attack between 0 and 90 degrees (in which the fins are located in the upstream portion), these vortices significantly affect the surface pressure on the rocket and increase the pitching moment. On the other hand, for AOAs between 90 to 180 degrees (in which the fins are in the downstream portion), the effect of these vortices on the on-surface pressure is negligible, and only vortices formed near the surface of the fins increase the pitching moment.

show abstract

Section: Aoamentioning

confidence: 99%

“…Figure 7 shows the pitching moment coefficients of the configuration both with and without fins. 7) Both results are obtained by DDES (details of the computational methods, grid, and so forth for the configuration without fins can be found in Ref. 7).…”

Section: Lmentioning

confidence: 99%

Computational Study on Finned Reusable Rocket Aerodynamics during Turnover

Aogaki

Kitamura

Nonaka

2019

AEROSPACE TECHNOLOGY JAPAN

Self Cite

View full text Add to dashboard Cite

show abstract

“…The same trend has been observed when the body has 45 deg. of rotation angle (not shown) as in [43].…”

Section: Numerical Examplesmentioning

confidence: 99%

“…Three-Dimensional Slender Body at High Angle-of-Attack (M = 0.086, Re = 6×10 5 , = 50º)This is a more practical case of a three-dimensional, slender body at a high angle-of-attack (= 50º). This configuration consists of hemisphere-cone-square_prism [i.e., its cross-sectional shape gradually changes from the circle (near the nose) to the (filleted) square (near the base)], and considered as one of candidates as a new reusable rocket at JAXA (for details, see Refs [43,44]…”

mentioning

confidence: 99%

Postlimiters and Simple Dirty-Cell Detection for Three-Dimensional Unstructured (Unlimited) Aerodynamic Simulations

et al. 2018

View full text Add to dashboard Cite

show abstract

“…), producing yaw force. 4,5) A large yaw force will destabilize the flight. In fact, an earlier study on a particular configuration 4) reported large CY (yaw force coefficient) and high flow asymmetry at high AoAs (50 degrees or more).…”

Section: Introductionmentioning

confidence: 99%

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

Inatomi

Kitamura

Nonaka

2019

AEROSPACE TECHNOLOGY JAPAN

Self Cite

View full text Add to dashboard Cite

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.

show abstract

Computational Study of Aerodynamic Characteristics of Reusable Rocket at High-Angle-of-Attack

Cited by 4 publications

References 7 publications

Computational Study on Finned Reusable Rocket Aerodynamics during Turnover

Computational Study on Finned Reusable Rocket Aerodynamics during Turnover

Postlimiters and Simple Dirty-Cell Detection for Three-Dimensional Unstructured (Unlimited) Aerodynamic Simulations

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

Contact Info

Product

Resources

About