Normal force calculations for rocket-like configurations

Bigarella, E. D. V.; Azevedo, João Luiz F.; Mello, Olympio

doi:10.1590/s1678-58782004000300005

Cited by 8 publications

(5 citation statements)

References 9 publications

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“…4). The Reynolds number based on the airfoil chord and the midvalue of interval (5) is 5:4 Â 10 6 . In order to assess the numerical accuracy of the solution, we tested three different meshes by varying both the number of grid nodes and the grid clustering.…”

Section: Formulation Of the Problem And A Numerical Methodsmentioning

confidence: 99%

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Bifurcations and buffet of transonic flow past flattened surfaces

Kuzmin

2009

Computers & Fluids

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Section: Formulation Of the Problem And A Numerical Methodsmentioning

confidence: 99%

“…The small local curvature is attributed also to surfaces of engine nacelles [4], compressor blades [5], and enlarged diameter bays of missiles [6,7]. At the same time, physical phenomena associated with transonic flow over flattened surfaces have not been well understood.…”

Section: Introductionmentioning

confidence: 99%

Bifurcations and buffet of transonic flow past flattened surfaces

Kuzmin

2009

Computers & Fluids

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“…By analyzing existing records of flying squid events, the squid launches out of water in a short time. To reduce pitch moment induced by lateral loads (especially when moving underwater), the body longitudinal axis and velocity vector of a launching vehicle are consistent during each launching phase [44,45]. The same principle applies to the squid motion as well.…”

Section: Launch Angles and Assumptionsmentioning

confidence: 99%

Locomotor transition: how squid jet from water to air

et al. 2020

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The amazing multi-modal locomotion of flying squid helps to achieve fast-speed migration and predator-escape behavior. Observation of flying squid has been rarely reported in recent years, since it is challenging to clearly record the flying squid’s aquatic-aerial locomotion in a marine environment. The existing reports of squid-flying events are rare and merely record the in-air motion. Therefore, the water-air locomotor transition of flying squid is still unknown. This paper proposes the idea of using CFD to simulate the process of the flying squid (Sthenoteuthis oualaniensis (S. oualaniensis)) launching from water into air. The results for the first time reveal the flow field information of squid in launching phase and show the kinematic parameters of flying squid in quantification. Both a trailing jet and pinch-off vortex rings are formed to generate launching thrust, and the formation number L ω /D ω is 5.22, demonstrating that the jet strategy is to produce greater time-averaged thrust rather than higher propulsion efficiency. The results also indicate that the maximum flying speed negatively correlates with the launch angle, indicating that a lower launch angle could result in a larger flying speed for the flying squid to escape. These findings explore the multi-modal locomotion of flying squid from a new perspective, helping to explain the trade-off strategy of water-to-air transition, and further enhance the performance of aquatic-aerial vehicles.

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“…Fig. 8 is normal force distribution along body-axis (x-direction) 16 (or, sectional line-load 12 ). This is obtained only from simulation, and shows that Nose Faring and SMSJ give local peaks (it is confirmed that SMSJs play a major role).…”

Section: B Normal Force and Pitching Moment: Case A5_phi00_epsilonrewtmentioning

confidence: 99%

“…Similar studies for other rocket configurations were conducted in Refs. [8][9][10][11][12][13][14][15][16], but our work differs from them in the following aspects. Firstly, those studies [8][9][10][11][12][13][14][15][16] presented either of aerodynamic characteristics, flow simulations, or wind-tunnel experiments independently; however, our study shows all those results and relates them together to thoroughly understand detailed flow structure and aerodynamics of the rocket.…”

Section: Introductionmentioning

confidence: 96%

Numerical and Experimental Investigations of Epsilon Launch Vehicle Aerodynamics at Mach 1.5

Kitamura

Nonaka

Kuzuu

et al. 2013

Journal of Spacecraft and Rockets

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The Epsilon Launch Vehicle, successor of M-V rocket which conveyed "MUSES-C (Hayabusa)," is currently under the development in Japan. The Epsilon is also designed for sending scientific satellites to outer space and its first flight is scheduled to be in 2013. In this study, by conducting both numerical simulations and wind tunnel tests, the aerodynamic characteristics and associated flow features of the Epsilon Launch Vehicle are extensively investigated at Mach 1.5. The results provided are axial/normal/side forces, pitching/yawing/ rolling moments, detailed three-dimensional flow structure, along with effects of Reynolds number (between wind-tunnel and flight conditions), Skin Stringers (small devices on the main body), and difference from another configuration called "NextGenEpsilon." This set of data includes unavailable ones at either the experiment standalone or the actual flight. Magnitudes of computed aerodynamic coefficients are in good agreement with the experiment and within the design criteria. According to the results, axial force is not affected by those above-mentioned factors, but local normal force is influenced around Skin Stringers by Reynolds number, and rolling moment can change even its sign. Detailed M x = rolling moment, (y-y cg )f z -(z-z cg )f y ] [N·m] M y = pitching moment, (z-z cg )f x -(x-x cg )f z ] [N·m] M z = yawing moment, (x-x cg )f y -(y-y cg )f x ] [N·m] p = static pressure [Pa] Pr = Prandtl number, 0.72 [-] q = dynamic pressure [Pa] Re = Reynolds number [-] S = reference area, πD 2 /4 [m 2 ] T = temperature [K] u, v, w = velocity components in Cartesian coordinates [m/s] x, y, z = Cartesian coordinates [m] x cg , y cg , z cg = center of gravity coordinates, (0.6363L, 0, 0) [m] x n , y n , z n = normal vector components in Cartesian coordinates [-]  = angle of attack [deg.]  = slip angle [deg.]  = roll angle [deg.]  = specific heat ratio, 1.4 [-]  = thermal conductivity [W/(m·K)]  = (molecular) viscosity [Pa·s]  = density [kg/m 3 ] Subscripts FL = flight condition F = forebody t = turbulent WT = wind-tunnel test condition ∞ = freestream value 0 = initial or stagnation value American Institute of Aeronautics and Astronautics 4

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Normal force calculations for rocket-like configurations

Cited by 8 publications

References 9 publications

Bifurcations and buffet of transonic flow past flattened surfaces

Bifurcations and buffet of transonic flow past flattened surfaces

Locomotor transition: how squid jet from water to air

Numerical and Experimental Investigations of Epsilon Launch Vehicle Aerodynamics at Mach 1.5

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