RCAIDE.Library.Methods.Aerodynamics.Common.Lift.BET_calculations
BET_calculations#
Functions
|
Cl, Cdval = compute_airfoil_aerodynamics( beta,c,r,R,B, |
|
Computes the inflow, lamdaw, and the tip loss factor, F. |
- compute_airfoil_aerodynamics(beta, c, r, R, B, Wa, Wt, a, nu, airfoils, airfoil_locations, ctrl_pts, Nr, Na, tc, use_2d_analysis)[source]#
- Cl, Cdval = compute_airfoil_aerodynamics( beta,c,r,R,B,
Wa,Wt,a,nu, airfoils,a_loc ctrl_pts,Nr,Na,tc,use_2d_analysis )
Computes the aerodynamic forces at sectional blade locations. If airfoil geometry and locations are specified, the forces are computed using the airfoil polar lift and drag surrogates, accounting for the local Reynolds number and local angle of attack.
If the airfoils are not specified, an approximation is used.
Assumptions: N/A
Source: N/A
- Inputs:
beta blade twist distribution [-] c chord distribution [-] r radius distribution [-] R tip radius [-] B number of rotor blades [-]
Wa axial velocity [-] Wt tangential velocity [-] a speed of sound [-] nu viscosity [-] airfoil_data Data structure of airfoil polar information [-] ctrl_pts Number of control points [-] Nr Number of radial blade sections [-] Na Number of azimuthal blade stations [-] tc Thickness to chord [-] use_2d_analysis Specifies 2d disc vs. 1d single angle analysis [Boolean]
- Outputs:
Cl Lift Coefficients [-] Cdval Drag Coefficients (before scaling) [-] alpha section local angle of attack [rad]
- compute_inflow_and_tip_loss(r, R, Wa, Wt, B, et1=1, et2=1, et3=1)[source]#
Computes the inflow, lamdaw, and the tip loss factor, F.
Assumptions: N/A
Source: N/A
- Inputs:
r radius distribution [m] R tip radius [m] Wa axial velocity [m/s] Wt tangential velocity [m/s] B number of rotor blades [-] et1 tuning parameter for tip loss function et2 tuning parameter for tip loss function et3 tuning parameter for tip loss function
- Outputs:
lamdaw inflow ratio [-] F tip loss factor [-] piece output of a step in tip loss calculation (needed for residual) [-]