A Hybrid Inverse Design Method for Axisymmetric Bodies in Incompressible Flow

Broughton, Benjamin A.; Selig, Michael S.

doi:10.2514/6.2002-3142

Cited by 2 publications

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“…The iteration procedure as explained earlier was originally implemented into a Newton solver and was able to produce the required pressure distribution on axisymmetric three-dimensional bodies [22] reliably. One equation is added to the multidimensional iteration scheme for each segment on the three-dimensional body where a specified V 3D is required.…”

Section: Three-dimensional Inverse Designmentioning

confidence: 99%

“…An alternative method is to use the surface of an airfoil, whereby this surface is defined by specifying the velocity distribution in two-dimensions. The latter method is adopted in the current work to assist in the design of general bulbous bodies and is a continuation of previous work done on axisymmetric bodies [22]. Several airfoils are designed in an inverse manner in isolation through conformal mapping and then used to define a threedimensional body such as a fuselage.…”

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confidence: 97%

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Hybrid Inverse Design Method for Nonlifting Bodies in Incompressible Flow

Broughton

Selig

2006

Journal of Aircraft

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A methodology for the inverse design of nonlifting axisymmetric and nonaxisymmetric bodies in incompressible flow is presented. In this method, an inverse design approach based on conformal mapping is used to design a set of airfoils in isolation. These airfoils are then assembled into a three-dimensional body and the flow over the body is calculated using a panel method. The inverse design parameters for the isolated airfoils are adjusted by a multidimensional nonlinear solver to achieve the desired aerodynamic properties on the three-dimensional body. The method can be used with fairly complex geometries, such as bodies in the presence of a wing or keel. The suitability and performance of several numerical schemes are compared in the paper. Several examples are presented that demonstrate the flexibility of the design method when applied to various representative design problems and they also show the ability of the method to match a known velocity distribution. Nomenclature A = area B = approximate Jacobian c = chord length c i = control airfoil F = vector of functional relations f i = functional relations to be zeroed h = surface displacement J = Jacobian matrix _ m = mass-flux n = dimension of nonlinear system n = surface normal Re = Reynolds number s = arc length s i = control sectioñ s = arc length relative to beginning of section u = normal velocity u t = transpiration velocity V 1 = freestream velocity _ v = volume flux v i = relative velocity along a splined segment x i = unknown variables x = vector of unknown variables x = correction vector = angle of attack, deg = segment design angle of attack = arc limit = arc limit relative to beginning of segment = source strength V = velocity difference over a segment normalized by the freestream velocity Subscripts i = segment number on an airfoil or the equivalent segment of the body cross-section p = unperturbed surface panel t = transpiration

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Section: Three-dimensional Inverse Designmentioning

confidence: 99%

mentioning

confidence: 97%