Separated flow unsteady aerodynamic theory

M., R.

doi:10.2514/3.45231

Cited by 8 publications

(3 citation statements)

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“…The assumption that the separation region is confined to a thin slit region causes the attached flow distribution of C p b to be unchanged upstream of the separation point, with a discontinuity in C p b at the separation point. Note that the upwash difference coefficient is not zero downstream of the trailing edge as was assumed by Chi [5]. Recall that the upwash difference coefficient is zero for attached flow.…”

Section: Unsteady Aerodynamic Lift and Moment Coefficientsmentioning

confidence: 96%

“…= v+ -Δν* = V* AVE + 1-Δν* .Substituting p+ and v*+ into Equation 15a, yields Equation 20.To this point, this analysis is analogous to that of Chi[5]. = v+ -Δν* = V* AVE + 1-Δν* .Substituting p+ and v*+ into Equation 15a, yields Equation 20.To this point, this analysis is analogous to that of Chi[5].…”

mentioning

confidence: 94%

“…In these, the flow is considered to separate at a specified position on the airfoil suction surface, with this separation point fixed throughout the oscillation cycle. More recently, Chi [5] used Fourier transform theory and the linearized small perturbation potential flow Brought to you by | New York University Bobst Library Technical Services Authenticated Download Date | 6/1/15 3:59 PM equation to develop an oscillating airfoil model for compressible flow. Woods [3] developed a model for incompressible potential flow past an isolated airfoil.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Prediction of Airfoil Separated Flow Unsteady Aerodynamics

Eley¹,

Fleeter²

1991

International Journal of Turbo and Jet Engines

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A mathematical model is developed to predict the effect of flow separation on the unsteady aerodynamic lift and moment acting on an harmonically oscillating two-dimensional airfoil in a subsonic flow field. The unsteady flow is considered to be a small perturbation to the uniform steady flow, with the steady flow assumed to separate at a specified fixed position on the airfoil suction surface. This formulation does not require the difference in the upwash velocity across the airfoil in the separated flow region to be determined before calculating the unsteady pressure difference across the airfoil chordline, thereby eliminating the assumption that the upwash difference is zero at the trailing edge when the steady flow is separated. This model is then used to demonstrate the effects of flow separation on the unsteady aerodynamics of an oscillating airfoil.