aerodynamics.py

Aerodynamic analysis routines usable for multiple purposes / flight phases

class openconcept.aerodynamics.aerodynamics.PolarDrag(**kwargs)

Bases: ExplicitComponent

Calculates drag force based on drag polar formulation

Inputs:

  • fltcond|CL (float) – Lift coefficient (vector, dimensionless)

  • fltcond|q (float) – Dynamic pressure (vector, Pascals)

  • ac|geom|wing|S_ref (float) – Reference wing area (scalar, m**2)

  • ac|geom|wing|AR (float) – Wing aspect ratio (scalar, dimensionless)

  • CD0 (float) – Zero-lift drag coefficient (scalar, dimensionless)

  • e (float) – Wing Oswald efficiency (scalar, dimensionless)

Outputs:

drag (float) – Drag force (vector, Newtons)

Options:

  • num_nodes (int) – Number of analysis points to run (sets vec length) (default 1)

  • vec_CD0 (bool) – Take in zero-lift drag coefficient as a vector of length num_nodes, otherwise take in as a scalar; by default False

class openconcept.aerodynamics.aerodynamics.Lift(**kwargs)

Bases: ExplicitComponent

Calculates lift force based on CL, dynamic pressure, and wing area

Inputs:

  • fltcond|CL (float) – Lift coefficient (vector, dimensionless)

  • fltcond|q (float) – Dynamic pressure (vector, Pascals)

  • ac|geom|wing|S_ref (float) – Reference wing area (scalar, m**2)

Outputs:

lift (float) – Lift force (vector, Newtons)

Options:

num_nodes (int) – Number of analysis points to run (sets vec length) (default 1)

class openconcept.aerodynamics.aerodynamics.StallSpeed(**kwargs)

Bases: ExplicitComponent

Calculates stall speed based on CLmax, wing area, and weight

Inputs:

  • CLmax (float) – Maximum lift coefficient (scalar, dimensionless)

  • weight (float) – Aircraft weight (scalar, kg)

  • ac|geom|wing|S_ref (float) – Reference wing area (scalar, m**2)

Outputs:

Vstall_eas (float) – Stall speed (scalar, m/s)