WsfAero2D.hpp

Go to the documentation of this file.

// ****************************************************************************
// CUI
//
// The Advanced Framework for Simulation, Integration, and Modeling (AFSIM)
//
// Copyright 2003-2015 The Boeing Company. All rights reserved.
//
// The use, dissemination or disclosure of data in this file is subject to
// limitation or restriction. See accompanying README and LICENSE for details.
// ****************************************************************************
// ****************************************************************************
// Updated by Infoscitex, a DCS Company.
// ****************************************************************************
 
#ifndef WSFAERO2D_HPP
#define WSFAERO2D_HPP
 
#include "wsf_export.h"
 
#include <vector>
 
class UtInput;
#include "WsfAero.hpp"
class WsfPlatform;

 
class WSF_EXPORT WsfAero2D : public WsfAero
{
public:
   WsfAero2D(const UtAtmosphere& aAtmosphere);
   ~WsfAero2D() override;
 
   WsfAero* Clone() const override;
 
   bool Initialize(double aSimTime, UtEntity* aPlatformPtr) override;
 
   void Update(double aSimTime, double aRequestedYForce = 0.0, double aRequestedZForce = 0.0, double aTVC_Force = 0.0) override;
 
   bool ProcessInput(UtInput& aInput) override;
 
   double CalculateDrag(double aAltitude_m, double aMach, double aWeight_N) const override;
 
protected:
   WsfAero2D(const WsfAero2D& aSrc);
 
   // Prevent use of operator= by declaring, but not defining.
   WsfAero2D& operator=(const WsfAero2D& aRhs) = delete;
 
   bool SetInternalValues(double aSimTime);
 
   void CalcCd0();
   void CalcCdTotal();
 
   struct DragPoint
   {
   public:
      DragPoint(double aMach, double aCd0)
         : mMach(aMach)
         , mCd0(aCd0)
      {
      }
      double mMach;
      double mCd0;
   };
 
   enum DragSpecType
   {
      cINCOMPRESSIBLE, 
      cPARAMETRIC, 
      cCURVE_POINTS 
   };
 
   // Characteristic attributes are listed first (intrinsic to the object),
   // and State values (which may vary with time) are listed later:
 
   double mAR; // Aspect Ratio
   // Oswald's Efficiency Factor
   double mE;
   // Maximum Obtainable Lift Coefficient:
   double mClMax;
   // Run-time constant that aggregates 1.0 / Pi * mAR * mE
   // (Multiplied times CL squared to get delta Cd.)
   double mK;
   double mCdZeroSubsonic;
   double mCdZeroSupersonic;
   double mMachBeginCdRise;
   double mMachEndCdRise;
   double mSubsonicCdSlope;
   double mSupersonicCdSlope;
   double mMachMaxSupersonic;
 
   // Drag Coefficient at Zero Lift,
   // as a function of Mach Number:
   std::vector<DragPoint> mCd0s;
 
   double                            mCl;
   double                            mCd0;
   double                            mCdTotal;
   DragSpecType                      mType;
   std::vector<DragPoint>::size_type mIndex;
 
   double mLateralForce;
 
 
private:
   double GetCd0(double aMach) const;
 
   double GetCdTotal(double aRequiredForce_N, double aReferenceArea_m2, double aAltitude_m, double aMach) const;
};
 
#endif