Numerical Computation of 3-Dimensional Supersonic Flow Field over Seamless Missiles

Al-Kayiem, Hussain H.; Hussein, Ahmed Kadhim; Jaleel, Jalal M.; Hussain, Salam Hadi

doi:10.17485/ijst/2014/v7i10.17

Cited by 2 publications

(1 citation statement)

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“…Experimental, empirical, and computational approaches were compared in a huge body of studies. Empirical and experimental approaches were compared in [1][2][3][4][5][6][7][8][9][10][11][12][13] whereas in [14][15][16][17][18][19][20][21][22], computational results were compared with experimental measurements. Computational techniques were also compared with empirical ones in [23].Comparative studies aggregating the three approaches were only conducted by Rosema el al.…”

Section: Introductionmentioning

confidence: 99%

A Comparative Study of Prediction Techniques for Supersonic Missile Aerodynamic Coefficients at Incidence

mahdi

Ahmed

Mahmoud

et al. 2017

55th AIAA Aerospace Sciences Meeting

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Evaluating the aerodynamic coefficients of flying vehicles such as missiles is a key step in their design and development procedures. In practice, the aerodynamic coefficients can be estimated using experimental measurements, numerical simulations, or using empirical and semi-empirical engineering tools. In the present paper, these three approaches are compared in the context of examining the aerodynamic coefficients of a fin-stabilized tactical missile. Supersonic flight conditions up to Mach 4 at incidence up to 18 degrees are considered. Lift and drag coefficients as well as the centre of pressure locations based on the three approaches are compared. The flow features around the missile are explored based on the numerical simulations.

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Section: Introductionmentioning

confidence: 99%

A Comparative Study of Prediction Techniques for Supersonic Missile Aerodynamic Coefficients at Incidence

mahdi

Ahmed

Mahmoud

et al. 2017

55th AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

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Fluid Similarity Criterions in Aircraft Landing Gear

Liu

2018

MATEC Web Conf.

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Facing the design difficulty and risk of aircraft landing gear, the fluid similarity theory and model experiments are used to predict large prototype's property, which provide guidance for hydraulic designation and selection to reduce risk. Firstly, the matrix method is used to establish the fluid similarity relationship between the prototype and the model's luffing mechanism, and the above conclusions are used to design the prototype's hydraulic system. Secondly, the luffing mechanism's dynamical model with accumulator was established, the initial motion condition was set, and the pressure's similarity ratio is obtained by simulation method. Finally, the dynamic model and similarity ratio about time, velocity and pressure are verified by the prototype and model's experimental data.

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Numerical Computation of 3-Dimensional Supersonic Flow Field over Seamless Missiles

Cited by 2 publications

References 10 publications

A Comparative Study of Prediction Techniques for Supersonic Missile Aerodynamic Coefficients at Incidence

A Comparative Study of Prediction Techniques for Supersonic Missile Aerodynamic Coefficients at Incidence

Fluid Similarity Criterions in Aircraft Landing Gear

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