Changeset 17150


Ignore:
Timestamp:
07/22/19 18:56:41 (5 weeks ago)
Author:
gkronber
Message:

#3014: fixed zero-lift angle of attack in formula for aircraft lift

File:
1 edited

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  • trunk/HeuristicLab.Problems.Instances.DataAnalysis/3.3/Regression/Physics/AircraftLift.cs

    r17094 r17150  
    2828namespace HeuristicLab.Problems.Instances.DataAnalysis {
    2929  public class AircraftLift : ArtificialRegressionDataDescriptor {
    30     public override string Name { get { return "Aircraft Lift Coefficient C_L = C_Lα (α + α0) + C_Lδ_e δ_e S_HT / S_ref"; } }
     30    public override string Name { get { return "Aircraft Lift Coefficient C_L = C_Lα (α - α0) + C_Lδ_e δ_e S_HT / S_ref"; } }
    3131
    3232    public override string Description {
     
    3636          "modeling generalized separable systems\", Expert Systems with Applications, Volume 109, 2018, " +
    3737          "Pages 25-34 https://doi.org/10.1016/j.eswa.2018.05.021. " + Environment.NewLine +
    38           "Function: C_L = C_Lα (α + α0) + C_Lδ_e δ_e S_HT / S_ref" + Environment.NewLine +
     38          "Function: C_L = C_Lα (α - α0) + C_Lδ_e δ_e S_HT / S_ref" + Environment.NewLine +
    3939          "the lift coefficient of the main airfoil C_Lα ∈ [0.4, 0.8]," + Environment.NewLine +
    4040          "tha angle of attack α ∈ [5°, 10°]," + Environment.NewLine +
     
    8888
    8989      for (int i = 0; i < C_La.Count; i++) {
    90         double C_Li = C_La[i] * (a[i] + a0) + C_Ld_e[i] * d_e[i] * S_HT[i] / S_ref[i];
     90        double C_Li = C_La[i] * (a[i] - a0) + C_Ld_e[i] * d_e[i] * S_HT[i] / S_ref[i];
    9191        C_L.Add(C_Li);
    9292      }
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