RCAIDE.Library.Methods.Aerodynamics.Airfoil_Panel_Method.airfoil_analysis

airfoil_analysis

airfoil_analysis(airfoil_geometry, alpha, Re_L, initial_momentum_thickness=1e-05, tolerance=1.0, H_wake=1.05, Ue_wake=0.99)

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

Assumptions: Michel Criteria used for transition

Squire-Young relation for total drag (exrapolates theta from end of wake). However, since we do not have a wake we will assume H_wake = 1.05 and Ue_wake = 0.99 The freestream velocity is taken to be 1 m/s. Airfoil has a unit chord length [1 m].

Source: N/A

Inputs: airfoil_geometry - airfoil geometry points [unitless] alpha - angle of attacks [radians] Re_L - Reynolds numbers [unitless] batch_analysis - boolean : If True: the specified number of angle of attacks and Reynolds [boolean]

numbers are used to create a table of 2-D results for each combination Note: Can only accomodate one airfoil

If False:The airfoils specified are run and corresponding angle of attacks and Reynolds numbers Note: The number of airfoils, angle of attacks and reynolds numbers must all the same dimension

Outputs: airfoil_properties.

AoA - angle of attack [radians Re - Reynolds number [unitless] Cl - lift coefficients [unitless] Cd - drag coefficients [unitless] Cm - moment coefficients [unitless] normals - surface normals of airfoil [unitless] x - x coordinate points on airfoil [unitless] y - y coordinate points on airfoil [unitless] x_bl - x coordinate points on airfoil adjusted to include boundary layer [unitless] y_bl - y coordinate points on airfoil adjusted to include boundary layer [unitless] Cp - pressure coefficient distribution [unitless] Ue_Vinf - ratio of boundary layer edge velocity to freestream [unitless] dVe - derivative of boundary layer velocity [m/s-m] theta - momentum thickness [m] delta_star - displacement thickness [m] delta - boundary layer thickness [m] H - shape factor [unitless] Cf - local skin friction coefficient [unitless] Re_theta_t - Reynolds Number as a function of theta transition location [unitless] tr_crit - critical transition criteria [unitless]

Properties Used: N/A

concatenate_surfaces(X_BOT, X_TOP, FUNC_BOT_SURF, FUNC_TOP_SURF, npanel, ncases, ncpts, wrong_columns)

Interpolation of airfoil properties

Assumptions: None

Source: None

Inputs: X_BOT - bottom surface of airfoil [unitless] X_TOP - top surface of airfoil [unitless] FUNC_BOT_SURF - airfoil property computation discretization on bottom surface [multiple units] FUNC_TOP_SURF - airfoil property computation discretization on top surface [multiple units] npanel - number of panels [unitless] ncases - number of angle of attacks [unitless] ncpts - number of Reynolds numbers [unitless]

Outputs: FUNC - airfoil property in user specified discretization on entire

surface of airfoil [multiple units]

Properties Used: N/A