### Abstract

A method of multipoint inverse airfoil design for incompressible potential flow is presented. Multipoint design is handled by dividing the airfoil into a number of desired segments. For each segment, the velocity distribution is prescribed together with an angle of attack at which the prescribed velocity distribution is to be achieved. In this manner, multipoint design objectives can be taken into account in the initial specification of the velocity distribution. In order for the multipoint inverse airfoil design problem to be well posed, three integral constraints and several conditions arise that must be satisfied. Further restrictions are imposed if the airfoil is to have a specified pitching moment, thickness ratio, or other constraints. The system of equations is solved partly as a linear system and partly through multidimensional Newton iteration. Since the velocity distribution is prescribed about the circle in terms of the arc limit, specification of the velocity in terms of arc length is also handled through multidimensional Newton iteration.

Original language | English (US) |
---|---|

Pages (from-to) | 1162-1170 |

Number of pages | 9 |

Journal | AIAA journal |

Volume | 30 |

Issue number | 5 |

DOIs | |

State | Published - Jan 1 1992 |

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### All Science Journal Classification (ASJC) codes

- Aerospace Engineering

### Cite this

*AIAA journal*,

*30*(5), 1162-1170. https://doi.org/10.2514/3.11046

}

*AIAA journal*, vol. 30, no. 5, pp. 1162-1170. https://doi.org/10.2514/3.11046

**Multipoint inverse airfoil design method based on conformal mapping.** / Selig, Michael S.; Maughmer, Mark David.

Research output: Contribution to journal › Article

TY - JOUR

T1 - Multipoint inverse airfoil design method based on conformal mapping

AU - Selig, Michael S.

AU - Maughmer, Mark David

PY - 1992/1/1

Y1 - 1992/1/1

N2 - A method of multipoint inverse airfoil design for incompressible potential flow is presented. Multipoint design is handled by dividing the airfoil into a number of desired segments. For each segment, the velocity distribution is prescribed together with an angle of attack at which the prescribed velocity distribution is to be achieved. In this manner, multipoint design objectives can be taken into account in the initial specification of the velocity distribution. In order for the multipoint inverse airfoil design problem to be well posed, three integral constraints and several conditions arise that must be satisfied. Further restrictions are imposed if the airfoil is to have a specified pitching moment, thickness ratio, or other constraints. The system of equations is solved partly as a linear system and partly through multidimensional Newton iteration. Since the velocity distribution is prescribed about the circle in terms of the arc limit, specification of the velocity in terms of arc length is also handled through multidimensional Newton iteration.

AB - A method of multipoint inverse airfoil design for incompressible potential flow is presented. Multipoint design is handled by dividing the airfoil into a number of desired segments. For each segment, the velocity distribution is prescribed together with an angle of attack at which the prescribed velocity distribution is to be achieved. In this manner, multipoint design objectives can be taken into account in the initial specification of the velocity distribution. In order for the multipoint inverse airfoil design problem to be well posed, three integral constraints and several conditions arise that must be satisfied. Further restrictions are imposed if the airfoil is to have a specified pitching moment, thickness ratio, or other constraints. The system of equations is solved partly as a linear system and partly through multidimensional Newton iteration. Since the velocity distribution is prescribed about the circle in terms of the arc limit, specification of the velocity in terms of arc length is also handled through multidimensional Newton iteration.

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U2 - 10.2514/3.11046

DO - 10.2514/3.11046

M3 - Article

VL - 30

SP - 1162

EP - 1170

JO - AIAA Journal

JF - AIAA Journal

SN - 0001-1452

IS - 5

ER -