Airfoil Profile

@PROFILE_DEFINITION {
@PROFILE_NAME {ProfileName} {
@UPPER_PROFILE {
@COORDINATES {0.0, x2, x3}
...
@COORDINATES {0.0, x2, x3}
}
@LOWER_PROFILE {
@COORDINATES {0.0, x2, x3}
...
@COORDINATES {0.0, x2, x3}
}
@TRAILING_EDGE_TANGENT {0.0, t2, t3}
@COMMENTS {CommentText}
}
}

Introduction

Airfoil shapes can be defined in three alternative manners.

  1. The aerodynamic profile is one of the Naca four digit series.
  2. The aerodynamic profile is one of the Naca five digit series.
  3. The aerodynamic profile is defined by a series of points along its upper and lower part.

Notes

  • The aerodynamic profile is defined by a series of points along its upper and lower profiles. All points lie in the plane of the cross-section, i.e., all x1 coordinates must vanish.
  • It is also required to define a training edge tangent vector.
  • It is possible to attach comments to the definition of the object; these comments have no effect on its definition.