aerodynamics.py

Aerodynamic analysis routines usable for multiple purposes / flight phases

class openconcept.analysis.aerodynamics.PolarDrag(**kwargs)[source]

Bases: openmdao.core.explicitcomponent.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)
class openconcept.analysis.aerodynamics.Lift(**kwargs)[source]

Bases: openmdao.core.explicitcomponent.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.analysis.aerodynamics.StallSpeed(**kwargs)[source]

Bases: openmdao.core.explicitcomponent.ExplicitComponent

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

Inputs:
  • CLmax (float) – Maximum lfit coefficient (scalar, dimensionless)
  • weight (float) – Dynamic pressure (scalar, kg)
  • ac|geom|wing|S_ref (float) – Reference wing area (scalar, m**2)
Outputs:

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