PAN AIR - A higher order panel method for predicting subsonic or supersonic linear potential flows about arbitrary configurations

Carmichael, R. L.; Erickson, L. L.

doi:10.2514/6.1981-1255

Cited by 100 publications

(45 citation statements)

References 3 publications

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“…These solutions pred1ct the flu1d dynamics of 1nV1scid reg10ns Wh1Ch 1nclude the Ilft1ng properties of nonseparated wings in subson1c or supersonic flows (refs. 4,7,8). An addit10nal advantage of the potential problem emerges from the use of Green's theorem (ref.…”

Section: Description Of the Prediction Methodsmentioning

confidence: 99%

Evaluation of an aerodynamic-load prediction method on a STOL fighter configuration

Katz

1986

24th Aerospace Sciences Meeting

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Section: Description Of the Prediction Methodsmentioning

confidence: 99%

Evaluation of an aerodynamic-load prediction method on a STOL fighter configuration

Katz

1986

24th Aerospace Sciences Meeting

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“…11) They derived a formula to calculate the Laplace equation using Green's theorem and the Neumann and Dirichlet boundary conditions. In the 1980s, Johnson,12) Carmichael and Ericson, 13) Maskew 14) and Youngren et al 15) studied various panel methods. Cho,16) Katz,17) Gordon and Rom 18) and Yeh and Plotkin 19) studied the steady state panel method to calculate wake simulation at high angles of attack, and the nonlinearity of the flow.…”

Section: Introductionmentioning

confidence: 99%

Unsteady Aerodynamic Analysis and Wake Simulation of Helicopter Rotors using the Time-Domain Panel Method

Lee

Cho

2012

Trans. Japan Soc. Aero. S Sci.

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An unsteady panel method based on potential flow theory is developed for unsteady aerodynamic analysis of helicopter rotors. The panel method uses a piecewise constant source and doublet singularities in the solution. This potential-based panel method is based on the Dirichlet boundary condition coupled with a time-stepping method. The proposed method uses a time-stepping loop to simulate the unsteady motion of helicopter rotors. A free wake model is used for the wake simulation of a helicopter rotor. The proposed method is validated by comparing our results with experimental data. The incompressible results of the proposed method for helicopter rotors are in good agreement with the experimental data for hovering and forward flight. The proposed method can be used for practical applications such as aerodynamic designs and the analysis of various helicopter rotor configurations.

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“…For separated flows, as for example occurring behind blunt bodies, an option has been introduced by Carmichael and Erickson [24] to set the internal potential equal to the onset potential and set the external potential to zero. This fixes the jump in potential across the surface and results in a specified strength of the dipole distribution.…”

Section: Body Surfacementioning

confidence: 99%

“…The work done by the static pressure per unit time iṡ 24) and for the work done by viscous forces per unit time we havė…”

Section: B3 Energy Conservationmentioning

confidence: 99%

“…The panel method was extended to the numerical simulation of linearized supersonic flows [24], [56], but due to the panel method's inability to simulate high speed transonic flows, the aerospace CFD community soon set it sights at the development of computational methods based on the steady Euler equations so that shock waves occurring in the flow around high speed airplanes could be simulated. Flow solvers that could simulate these flows around three-dimensional configurations in a production setting started to appear after 1980.…”

Section: Wind Turbine Aerodynamicsmentioning

confidence: 99%

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Multilevel panel method for wind turbine rotor flow simulations

Garrel¹

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SummaryThe ongoing trend in wind turbine development is towards larger rotors because of the resulting lower cost of energy. These large rotors lead to relatively flexible structures that are more susceptible to the unsteady aerodynamic loading occurring in normal operating conditions. An accurate prediction of these loadings is important for the design of an economically viable and technically reliable wind turbine. Simulation methods of wind turbine aerodynamics currently in use mainly fall into two categories: the first is the group of traditional low-fidelity engineering models and the second is the group of computationally expensive CFD methods based on the Navier-Stokes equations.For an engineering environment the search is for "medium fidelity" wind turbine simulation methods that bridge the gap between the computationally inexpensive low-fidelity methods and the computationally expensive CFD methods. The ultimate goal is a balanced mixture of higher accuracy of the representation of the physics and shorter simulation times for wind turbine aerodynamics simulation methods. This can be found in the combination of the theories for panel methods, integral boundary layer methods, strong viscous-inviscid coupling, and fluid structure interaction.The present study focuses on the development of the theory and the practical implementation of a fast multilevel integral transform in a computer program. We utilize this multilevel scheme in a low-order panel method. It is demonstrated that for the simulation of the wake flow of wind turbine rotors the computational burden is reduced from O(N 2 ) for a conventional panel method to O(N ) for the present method. This implies that the computational effort is reduced to grow linearly with problem size N , with N the number of panels.We consider the unsteady, incompressible flow around wind turbine rotors and assume the effects of viscosity to be confined to infinitesimal thin boundary layers and wake regions and assume irrotational flow elsewhere. These assumptions allows us to reduce the flow problem to the problem of solving the Laplace equation for a (scalar) velocity potential function. This makes it possible to reformulate the problem as an integral equation over the surface of the rotor and the wakes that emanate from the trailing edges of the rotating wind turbine blades.The mathematical model is discretized in the form of a low-order panel iii Multilevel Panel Method method. The implementation of the panel method is verified by considering the flow over a stationary ellipsoid in a uniform onset velocity field, the flow over a rotating ellipsoid in a fluid at rest, and by considering the flow over a high aspect ratio wing with elliptic planform with as cross-section a von Kármán-Trefftz airfoil. For the first two test cases the numerical results are compared with analytical solutions. The error in the velocity potential is shown to be O(h 2 ), with h a characteristic panel size. The third test case uses the analytical solution for the 2D von Kármán-Trefftz airfoil ...

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PAN AIR - A higher order panel method for predicting subsonic or supersonic linear potential flows about arbitrary configurations

Cited by 100 publications

References 3 publications

Evaluation of an aerodynamic-load prediction method on a STOL fighter configuration

Evaluation of an aerodynamic-load prediction method on a STOL fighter configuration

Unsteady Aerodynamic Analysis and Wake Simulation of Helicopter Rotors using the Time-Domain Panel Method

Multilevel panel method for wind turbine rotor flow simulations

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