RCAIDE.Library.Methods.Aerodynamics.Airfoil_Panel_Method

Airfoil_Panel_Method

RCAIDE Package Setup

Modules

aero_coeff(x, y, cp, al, npanel)	Compute airfoil force and moment coefficients about
airfoil_analysis(airfoil_geometry, alpha, Re_L)	This computes the aerodynamic polars as well as the boundary layer properties of an airfoil at a defined set of reynolds numbers and angle of attacks
cf_filter(ncpts, ncases, npanel, CF)
chordwise_distribution(x, y, cp, al, npanel, ...)	Compute chordwise distribution of lift and drag for
heads_method(npanel, ncases, ncpts, NU, ...)	Computes the boundary layer characteristics in turbulent flow pressure gradients
hess_smith(x_coord, y_coord, alpha, Re, npanel)	Computes the incompressible, inviscid flow over an airfoil of arbitrary shape using the Hess-Smith panel method.
infl_coeff(x, y, xbar, ybar, st, ct, npanel, ...)	Compute the matrix of aerodynamic influence coefficients for later use
panel_geometry(x, y, npanel, ncases, ncpts)	Computes airfoil surface panelization parameters for later use in the computation of the matrix of influence coefficients.
thwaites_method(npanel, ncases, ncpts, NU, ...)	Computes the boundary layer characteristics in laminar flow pressure gradients
velocity_distribution(qg, x, y, xbar, ybar, ...)	Compute the tangential velocity distribution at the