RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.compute_wing_induced_velocity

compute_wing_induced_velocity#

compute_wing_induced_velocity(VD, mach, compute_EW=False)[source]#

This computes the induced velocities at each control point of the vehicle vortex lattice

Assumptions: Trailing vortex legs infinity are alligned to freestream

Outside of a call to the VLM() function itself, EW does not need to be computed, as C_mn provides the same information in the body-frame.

Source: 1. Miranda, Luis R., Robert D. Elliot, and William M. Baker. “A generalized vortex lattice method for subsonic and supersonic flow applications.” (1977). (NASA CR)

  1. VORLAX Source Code

Inputs: VD - vehicle vortex distribution [Unitless] mach [Unitless]

Outputs: C_mn - total induced velocity matrix [Unitless] s - semispan of the horshoe vortex [m] t - tangent of the horshoe vortex [-] CHORD - chord length for a panel [m] RFLAG - sonic vortex flag [boolean] ZETA - tangent incidence angle of the chordwise strip [-]

Properties Used: N/A

subsonic(Z, XSQ1, RO1, XSQ2, RO2, XTY, T, B2, ZSQ, TOLSQ, X1, Y1, X2, Y2, RTV1, RTV2)[source]#

This computes the induced velocities at each control point of the vehicle vortex lattice for subsonic mach numbers

Assumptions: Trailing vortex legs infinity are alligned to freestream

Source: 1. Miranda, Luis R., Robert D. Elliot, and William M. Baker. “A generalized vortex lattice method for subsonic and supersonic flow applications.” (1977). (NASA CR)

  1. VORLAX Source Code

Inputs: Z Z relative location of the vortices [m] XSQ1 X1 squared [m^2] RO1 coefficient [-] XSQ2 X2 squared [m^2] RO2 coefficient [-] XTY AXIAL DISTANCE BETWEEN PROJECTION OF RECEIVING POINT ONTO HORSESHOE PLANE AND EXTENSION OF SKEWED LEG [m] T tangent of the horshoe vortex [-] B2 mach^2-1 (-beta2) [-] ZSQ Z squared [m^2] TOLSQ coefficient [-] X1 X coordinate of the left side of the vortex [m] Y1 Y coordinate of the left side of the vortex [m] X2 X coordinate of the right side of the vortex [m] Y2 Y coordinate of the right side of the vortex [m] RTV1 coefficient [-] RTV2 coefficient [-]

Outputs: U X velocity [unitless] V Y velocity [unitless] W Z velocity [unitless]

Properties Used: N/A

supersonic(Z, XSQ1, RO1, XSQ2, RO2, XTY, T, B2, ZSQ, TOLSQ, TOL, TOLSQ2, X1, Y1, X2, Y2, RTV1, RTV2, CUTOFF, CHORD, RNMAX, n_cp, TE_ind, LE_ind)[source]#

This computes the induced velocities at each control point of the vehicle vortex lattice for supersonic mach numbers

Assumptions: Trailing vortex legs infinity are alligned to freestream

Source: 1. Miranda, Luis R., Robert D. Elliot, and William M. Baker. “A generalized vortex lattice method for subsonic and supersonic flow applications.” (1977). (NASA CR)

  1. VORLAX Source Code

Inputs: Z Z relative location of the vortices [m] XSQ1 X1 squared [m^2] RO1 coefficient [-] XSQ2 X2 squared [m^2] RO2 coefficient [-] XTY AXIAL DISTANCE BETWEEN PROJECTION OF RECEIVING POINT ONTO HORSESHOE PLANE AND EXTENSION OF SKEWED LEG [m] T tangent of the horshoe vortex [-] B2 mach^2-1 (-beta2) [-] ZSQ Z squared [m^2] TOLSQ coefficient [-] X1 X coordinate of the left side of the vortex [m] Y1 Y coordinate of the left side of the vortex [m] X2 X coordinate of the right side of the vortex [m] Y2 Y coordinate of the right side of the vortex [m] RTV1 coefficient [-] RTV2 coefficient [-] CUTOFF coefficient [-] CHORD chord length for a panel [m] RNMAX number of chordwise panels [-] n_cp number of control points [-] TE_ind indices of the trailing edge [-] LE_ind indices of the leading edge [-]

Outputs: U X velocity [unitless] V Y velocity [unitless] W Z velocity [unitless] RFLAG sonic vortex flag [boolean]

Properties Used: N/A

supersonic_in_plane(RAD1, RAD2, Y1, Y2, TOL, XTY, CPI)[source]#

This computes the induced velocities at each control point in the special case where the vortices lie in the same plane

Assumptions: Trailing vortex legs infinity are alligned to freestream In plane vortices only produce W velocity

Source: 1. Miranda, Luis R., Robert D. Elliot, and William M. Baker. “A generalized vortex lattice method for subsonic and supersonic flow applications.” (1977). (NASA CR)

  1. VORLAX Source Code

Inputs: RAD1 array of zeros [-] RAD2 array of zeros [-] Y1 Y coordinate of the left side of the vortex [m] Y2 Y coordinate of the right side of the vortex [m] TOL coefficient [-] XTY AXIAL DISTANCE BETWEEN PROJECTION OF RECEIVING POINT ONTO HORSESHOE PLANE AND EXTENSION OF SKEWED LEG [m] CPI 2 Pi [radians]

Outputs: W Z velocity [unitless]

Properties Used: N/A