Procedures

Append a 1D array as a new row in an extendable 2D dataset (nt x ns)

Append a single scalar to an extendable 1D dataset

Compute force using blade circulation

Compute force using sectional alpha

Compute force using alpha approximated from sec circulation

Compute sec alpha using sec resultant velocity

Compute sectional resultant vel by interpolating local panel vel

Compute important locations at each section coordinates of collocation point located at chord fraction flap moment arm

Convect wake collocation points using velNwake matrix

Compute lift and drag direction vectors

Limits wake velocity to a set value to prevent blow up. Near wake only for predicted wake; near and far for current wake.

Move blade by dshift

Rotate blade by flap angle

Rotate blade by pitch angle about pivotLE

Rotate blade using pts. pts refers to (phi, theta, psi)

Rotate wake about axis at specified origin

Rotate blade geometry about axis at specified origin Rotation angle in radians

Convert force coefficients to dimensional forces

Sum up sectional forces to net forces

Compute induced velocity by bound vortices alone

Compute induced velocity by wake vortex rings

Compute induced velocity by blade bound vorticity

Compute induced velocity by bound vortices alone

Compute induced velocity by bound vortices alone

Compute induced velocity by blade bound vorticity

Maintain continuity between vortex ring elements after convection of wake collocation points

Compute skew

Flush and close HDF5 file. Call after results2hdf5.

Return cossine-spaced array over a specified interval

Return cossine-spaced array over a specified interval

Create an extendable 1D dataset of shape (0,) with unlimited max dim

Create an extendable 2D dataset of shape (0, ns) -- time x span

Compute cross product between two 3d vectors

Compute cross product between two 3d vectors

Deinitialize HDF5 library (h5close_f). file_id unused (kept for API).

Rotor dynamics to file

Write filaments to file for using with grid-based plots

Assign point to nth endpoint of filament

Mirror gamma and coordinates about a specified plane

Rotate using TMat about originVec

Shift coordinates of nth corner by dshift distance (usually for Udt convection)

Calculate inflow velocity along directionVector on the blades of rotor(rotorNumber) at rotor(rotorNumber)%secCP

Plot rotor geometry and wake to file

Plot surface geometry to file

Angle between two 3d vectors using cos formula Assumes no angle > 180 deg exists

Angle between two 3d vectors using cos formula Assumes no angle > 180 deg exists

Angle between two 3d vectors using tan formula Result will be from -pi to pi

Angle between two 3d vectors using tan formula Result will be from -pi to pi

Returns value of 2-d linearly interpolated CD for given alphaQuery and machQuery values

Returns value of 2-d linear interpolated CL for a given alphaQuery and machQuery values

Returns value of 2-d linearly interpolated CM for given alphaQuery and machQuery values

Returns ddflap from blade flap equation

Transformation matrix for theta angular rotation about a 3d axis

Transformation matrix for theta angular rotation about a 3d axis

Return half sine-spaced array over a specified interval

Return half sine-spaced array over a specified interval

Calculate inflow velocity along directionVector on the blades of rotor(rotorNumber) at rotor(rotorNumber)%secCP

Create HDF5 file with extendable structure. Call before results2hdf5, then close_hdf5.

Initialise headers for plot files

1-d Interpolation using 1st and 2nd order Lagrange polynomials

1-d Interpolation using 1st and 2nd order Lagrange polynomials

Native implementation of matrix inverse based on Doolittle method

Native implementation of matrix inverse based on Doolittle method

Inverse of a matrix calculated by finding the LU decomposition using LAPACK

Inverse of a matrix calculated by finding the LU

Checks if a == b within a tolerance

Checks if a == b within a tolerance

Check if Ainv is inverse of matrix A by multiplication

Check if Ainv is inverse of matrix A by multiplication

Compute length of linesegment between points P1 and P2

Compute length of linesegment between points P1 and P2

Return linearly-spaced array over a specified interval

Return linearly-spaced array over a specified interval

Linear Least Squares fitting (2nd order)

Linear Least Squares fitting (2nd order)

Matrix multiplication implemented using BLAS

Matrix multiplication

Matrix multiplication with vector implemented using BLAS

Matrix multiplication with vector

Removes component along dirVec from a vector aVec

Removes component along dirVec from a vector aVec

Compute outer product between two 3d vectors

Compute outer product between two 3d vectors

Write rotor parameters to json file

Display in matrix format

Display in matrix format

Prints status message (or SUCCESS if left blank)

Write velocities at probe locations

Returns 3d vector aVec projected along dirVec

Returns 3d vector aVec projected along dirVec

Piecewise linear 1d interpolation

Piecewise linear 1d interpolation

Read config.nml input file (in namelist format)

Reads from C81 file to C81 class

Append one timestep of data to open HDF5 file.

Update age of wake filaments

Assign coordinates to first rowNear of wake from last row of blade

Compute force from circulation

Compute force from sec alpha

Compute force from sec alpha

Compute AIC matrix for rotor

Deinitialise rotor variables

Dissipation model based on the paper: Generalized Viscous Vortex Model for Application to Free-Vortex Wake Calculations,Bhagwat and Leishman (2002) The apparent viscosity coefficient is 'delta' and kept a constant value. delta has to be 100 for small-scale rotors and around 1000 for large-scale rotors

Dissipation model based on the paper: Generalized Viscous Vortex Model for Application to Free-Vortex Wake Calculations,Bhagwat and Leishman (2002) The apparent viscosity coefficient is 'a1' known as Squire's app. viscosity parameter and this allows the dissipation to be dependent on the vortex strength The apparent viscosity is kinematic viscosity plus the turbulent viscosity (a1*|gamma|)) a1 has to be O(1e-4) for rotary wings (usually set to 2e-4) and O(1e-5) for fixed wings

Erase a far wake row by setting gamma to zero

Erase a near wake row by setting gamma to zero

Get z coordinate on wing from x, y values

Prescribed flap [rad]: flap0 + flapCcos(psi) + flapSsin(psi)

Prescribed flap rate: d(flap)/dt = Omega * d(flap)/d(psi) [rad/s]

Get pitch angle corresponding to blade azimuthal location

Initialize variables of rotor geometry and wake

Map gam from vector to matrix format

Mirrors gamma from another rotor

Mirrors velCP, velCPm from another rotor (flip velocity component in mirror plane)

Mirrors wake positions from another rotor

Read blade geometry from PLOT3D formatted file

Read rotor geometry from geomXX.nml in namelist format

Rotate rotor by dpsi angle about axis

Rotate blades by flap angle

Rotate using pts => phi theta psi Warning: This rotation is about the global reference frame

Shift wake locations of Fwake for truncation

Shift wake locations on rollup

Read ASCII stl file for non-lifting surface geometry

Converts -ve nsteps to nsteps for corresponding no. of chords or revs

Attaches prescribed far wake

Compute induced velocity by all wing vortices at P

Compute induced velocity by bound vortices at P

Skew parameter to file

Return tan-spaced array over a specified interval

Return tan-spaced array over a specified interval

Transformation matrix (body to global frame)

Transformation matrix (body to global frame)

Transformation matrix (global to body frame)

Transformation matrix (global to body frame)

Wake tip to file

Trapezoid integration with unequal intervals

Trapezoid integration with unequal intervals

Normalizes a non-zero 3d vector

Normalizes a non-zero 3d vector

Calculate 2nd order accurate induced velocity on far wake

Calculate 2nd order accurate induced velocity on near wake

Compute length of vortex filament

Compute induced velocity by unit strength vortex filament

Compute induced velocity by rotor (wing + wake) on Fwake corner points

Compute induced velocity by rotor (wing + wake) on Nwake corner points

Assign coordinates to nth corner

Burst vortex filaments if skewLimit is exceeded

Calculate length of filaments in vortex ring

Obtain angle between bimedians

Obtain interior angles of vortex ring

Obtain median angle of vortex ring

Mirror gamma and coordinates about a specified plane

Rotate vortex ring using Tmat about origin

Shift coordinates of nth corner by dshift distance (usually for U*dt convection)

Compute induced velocity by unit strength 4-element vortex ring

Compute induced velocity by unit strength 3-element source ring

Assign coordinates to nth corner

Compute panel resultant velocities using local velocities

Calculate mean chord and mean span

Compute collocation point location

Compute normal vector

Compute chordwise and spanwise tangential vectors

Check whether collocation point lies inside viscous core region of vortex ring

Rotate panel using transformation matrix

Shift corners of vortex ring by dshift

Write a fixed-size 1D dataset (not extendable) -- used for r_R

Write a fixed-size 2D dataset (1 x ncols) for snapshot files

Write geom.nml parameters to geom sub-group under the rotor

Writes C81 class data to C81 file