Computations of Magnus effects for a yawed, spinning body of revolution

Sturek, Walter B.; Dwyer, H. A.; Kayser, Lyle D.; Nietubicz, Charles J.; ReklisJ, Robert P.; Opalka, Klaus O.

doi:10.2514/3.7566

Cited by 39 publications

(17 citation statements)

References 6 publications

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“…Flight tests have shown that, elastic deformation of a projectile body can reach the same order of magnitude as its radius [1,7]. Spin can cause Magnus forces and moments with the distorted boundary layer, the coupling of the elastic deformation and rolling movement of a projectile body will produce a more complicated phenomenon than those previously discussed [2][3][4]. Studies have shown that, non-linear aerodynamic moments can be obtained even with linear aerodynamic theory; these moments will further cause non-linear movements such as spin lock-in and roll-pitch resonance [5][6][7].…”

Section: Introductionmentioning

confidence: 94%

Effect of elastic deformation on the aerodynamic characteristics of a high-speed spinning projectile

Yin

Lei

et al. 2015

Aerospace Science and Technology

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Section: Introductionmentioning

confidence: 94%

Effect of elastic deformation on the aerodynamic characteristics of a high-speed spinning projectile

Yin

Lei

et al. 2015

Aerospace Science and Technology

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“…Detailed comparisons of the computations to experimental data for turbulent boundary layer profile characteristics, wall pressure measurements and Magnus force are reported in Ref. 9. Comparisons shown here will be limited to the aerodynamic coefficients of interest.…”

Section: A Comparisons To Experimentsmentioning

confidence: 99%

Computational Parametric Study of the Aerodynamics of Spinning Slender Bodies at Supersonic Speeds

1981

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Unclassified 15«. DECLASSIFI CATION/DOWNGRADING SCHEDULE Approved for public release; distribution unlimited. 17. DISTRIBUTION STATEMENT (of the abatract entered In Block 20, It different from Report) 18. SUPPLEMENTARY NOTES 19. KEY WORDS (Continue on reverse alda If neceaaary and Identify by block numbed Projectile aerodynamics Supersonic flow Finite difference computations 20, ABSTRACT fCoirtfiiiw ao rmraram sfoto If nccMMty and Identify by block number) Three dimensional finite-difference flow field computation techniques have been employed to generate a parametric aerodynamic study at supersonic speeds. Computations for viscous turbulent and inviscid flow have been performed for cone-cylinder, secant-ogive-cylinder, and tangent-ogive-cylinder bodies for a Mach number range of 1.75 < M < 5. The aerodynamic coefficients computed are pitching moment, normal force, center of pressure, Magnus moment, Magnus force, Magnus center of pressure, form drag, viscous drag, roll damping and pitch damping. All aerodynamic coefficients are computed in a DD/^1473 EDFTION OF » MOV 65 IS OBSOLETE UNCLASSIFIED SECURITY CLASSIFICATION OF THIS PAGE (When Data Entered) UNCLASSIFIED SECURITY CLASSIFICATION OF THIS PAGEfHTian Data Bnland) 20. ABSTRACT (Continued) conceptually exact manner. The only empirical input is that required for turbulence modeling. Computed results are compared to experimental data fron free flight aerodynamic ranges and wind tunnels in order to validate the computational techniques. Parametric comparisons illustrate the effects of body configuration and Mach number for the ten aerodynamic coefficients. The results for Magnus and pitch damping are of particular interest.

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“…Although Magnus force is only 1/100 to 1/10 of normal force, the combination of lateral force and longitudinal force can induce the coning motion of the projectile, which significantly influences the projectile dynamic stability. For example, divergent coning motion was observed for 1/3 of the total 60 flight tests for the American Tomahawk sounding rocket (Curry & Uselton, 1967;Sturek et al, 1978). Predicting the Magnus effect accurately and investigating its flow mechanism are what researches have been longing for.…”

Section: Introductionmentioning

confidence: 99%

Body-fin interference on the Magnus effect of spinning projectile in supersonic flows

Yin

Lei

2017

Engineering Applications of Computational Fluid Mechanics

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The numerical simulations of flow over a spinning finned projectile at angles of attack ranging from 4 • to 30.3 • in supersonic conditions were carried out to investigate the flow mechanism of the Magnus effect. The finite volume method, a dual-time stepping method, and a γ − Re θ transition model were combined to solve the Reynolds-averaged Navier-Stokes (RANS) equations. The validation of temporal resolution, grid independence, and turbulence models were conducted for the accuracy of the numerical method. The numerical results were in certain agreement with archival experimental data. A comparison of the transient lateral force and time-averaged Magnus force between the body of finned projectile and the nonfinned body, the projectile fin and single fin was given. The key lies in the analysis of the reasons for the production of the Magnus force. The simulation provided a profound insight into the flow structure and revealed the following. The fin leading edge shock contributes to the unsteady interference on body lateral force, while the time-averaged body Magnus force is similar to that of the nonfinned body. At α = 30.3 • , the shielding effect of body on crossflow weakens the time-averaged body Magnus force induced by asymmetrical flow separation, the magnitude of which is reduced to the value at α = 8 • . The leeward separation vortices and the resistance on wingroot flow are responsible for the nonlinear interference of the projectile body on fin Magnus force at different angles of attack. When the low pressure region of the vortex core is equivalent to the size and position of fin, leeward separation vortices contribute more the time-averaged Magnus force and induce high frequency variation to the transient fin lateral force. ARTICLE HISTORY

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Computations of Magnus effects for a yawed, spinning body of revolution

Cited by 39 publications

References 6 publications

Effect of elastic deformation on the aerodynamic characteristics of a high-speed spinning projectile

Effect of elastic deformation on the aerodynamic characteristics of a high-speed spinning projectile

Computational Parametric Study of the Aerodynamics of Spinning Slender Bodies at Supersonic Speeds

Body-fin interference on the Magnus effect of spinning projectile in supersonic flows

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