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- W577162990 abstract "A two-dimensional model of the aerodynamics of rotor blades inforward flight is proposed in which the motion of the blade isrepresented by periodical variations of the freestrearn velocity andincidence. A novel implicit methodology for the solution of thecompressible Reynolds averaged Navier-Stokes equations and a twoequationmodel of turbulence is developed. The spatial discretisation isbased upon Osher's approximate Riernann solver, while time integrationis performed using a Newton-Krylov method.The method is employed to calculate the steady transonicaerodynamics of two supercritical aerofoils and the unsteadyaerodynamics of pitching aerofoils. Comparison with experiment andindependent calculations for these test cases is satisfactory. Furthercalculations are performed for the self-excited periodic flow around a biconvexaerofoil. Comparison of quasi-steady and unsteady calculationssuggests that the flow instability responsible for the self-excited flow isdue to the presence of a shock induced separation bubble in thecorresponding steady flow.Finally the method is used to predict the aerodynamics of aerofoilsperforming inplane and combined inplane-pitching motions. Resultsshow that quasi-steady aerodynamic models are unsuitable at conditionsrepresentative of high-speed forward flight. For shock free flows, theunsteady effects of freestrearn oscillations can be represented by asimple phase lag. For transonic flows the influence of unsteadiness onshock wave dynamics is shown to be complex. Calculations for indicialmotion show that the unsteady behaviour of the flow is related to thefinite time taken by disturbance waves to travel to the shock wave fromthe leading and trailing edges of the aerofoil." @default.
- W577162990 created "2016-06-24" @default.
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- W577162990 date "1999-03-01" @default.
- W577162990 modified "2023-09-23" @default.
- W577162990 title "Numerical study of the unsteady aerodynamics of helicopter rotor aerofoils" @default.
- W577162990 hasPublicationYear "1999" @default.
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