nlwing2
This package allows efficient computation of nonlinear aerodynamic
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Calculates vortex-induced velocities using Biot-Savart law.
Runs the automatic calculation of a wing's aerodynamic characteristics for a whole range of angles of attack.
Combines two polars to get a specific interpolation.
applies a newton/levenberg-marquardt corrector to a flow state, in order to reach local lift/circulation balance.
this function calculates the jacobian of floweq w.
evaluates the right-hand sides of the spanwise flow equations given the spanwise distribution of flow control quantities (scaled circulations).
analyzes a lift curve.
Load an airfoil polar data in the form of 4 column matrix, specified as
The angles of attack should form an increasing seqLoads the basic wing geometry from file FILENAME.
Initializes the flow at a particular global angle of attack by computing the sensitivity matrices.
Creates the wing structure necessary for further computations.
@deftypefn{Function File} {ppd =} polppder (pp) Differentiates a piecewise polynomial structure.
Predicts a flow change when the global angle of attack is increased, using a Euler finite-difference method.
Calculates local spanwise quantities for a given flow state.
Sets angle of attack directly for a flow.
spanwise inerpolation of polar data.
Computes the induced velocities tensors on a lifting line approximated by a chain of vortex segments.
