RCAIDE.Library.Methods.Aerodynamics.Airfoil_Panel_Method.heads_method

heads_method#

heads_method(npanel, ncases, ncpts, NU, DEL_0, THETA_0, DELTA_STAR_0, CF_0, ShapeFactor_0, RE_L, TURBULENT_COORD, VE_I, DVE_I, TURBULENT_SURF, tol, wrong_columns)[source]#

Computes the boundary layer characteristics in turbulent flow pressure gradients

Source: Head, M. R., and P. Bandyopadhyay. “New aspects of turbulent boundary-layer structure.” Journal of fluid mechanics 107 (1981): 297-338.

Assumptions: None

Inputs: ncases - number of cases [unitless] ncpts - number of control points [unitless] DEL_0 - intital bounday layer thickness [m] DELTA_STAR_0 - initial displacement thickness [m] CF_0 - initial value of the skin friction coefficient [unitless] H_0 - initial value of the shape factor [unitless] THETA_0 - initial momentum thickness [m] TURBULENT_SURF - normalized length of surface [unitless] RE_L - Reynolds number [unitless] TURBULENT_COORD- x coordinate on surface of airfoil [unitless] VE_I - boundary layer velocity at all panels [m/s-m] DVE_I - derivative of boundary layer velocity at all panels [m/s^2] npanel - number of points on surface [unitless] tol - boundary layer error correction tolerance [unitless]

Outputs: RESULTS.

X_H - reshaped distance along airfoil surface [unitless] THETA_H - momentum thickness [m] DELTA_STAR_H - displacement thickness [m] H_H - shape factor [unitless] CF_H - friction coefficient [unitless] RE_THETA_H - Reynolds number as a function of momentum thickness [unitless] RE_X_H - Reynolds number as a function of distance [unitless] DELTA_H - boundary layer thickness [m]

Properties Used: N/A

RK4(ind, dx, x, Theta_var, VeThetaH1_var, Theta_slope, VeThetaH1_slope)[source]#