/// <summary>
/// Thrust = Drag Condition
/// </summary>
/// <param name="Cd">Coefficient of Drag of Wing</param>
/// <param name="rho">Density of Air on Planet at Altitude</param>
/// <param name="S">Surface Area of Wing</param>
/// <param name="v">Velocity of Aircraft</param>
/// <returns>Thrust to meet Thrust=Drag Condition</returns>
public static EquationReturnType <Thrust> GetThrust(DragCoefficient Cd, Density rho, SurfaceArea S, Velocity v)
{
EquationReturnType <Thrust> ToReturn = new EquationReturnType <Thrust>();
ToReturn.Data = new Thrust();
ToReturn.Data.Set(Cd.Get() * rho.Get() / 2.0 * S.Get() * v.Get() * v.Get());
ToReturn.Latex = Cd.Latex() + @"\cdot \frac{" + rho.Latex() + @"}{2}\cdot " + S.Latex() + @"\cdot " + v.Latex() + @"^{2}";
return(ToReturn);
}
/// <summary>
/// Power = Force * Velocity Condition
/// </summary>
/// <param name="Cd">Drag Coefficient of Wing</param>
/// <param name="Cl">Lift Coefficient of Wing</param>
/// <param name="g">Acceleration Due to Gravity At Altitude on Planet</param>
/// <param name="m">Mass of Aircraft</param>
/// <param name="rho">Density of Air At Altitude on Planet</param>
/// <param name="S">Surface Area of Wing</param>
/// <returns>Power for Straight and Level Flight at Thrust and Velocity</returns>
public static EquationReturnType <PowerForStraightLevelFlight> GetPowerForStraightLevelFlight(DragCoefficient Cd, LiftCoefficient Cl, Mass m, AccelerationDueToGravity g, SurfaceArea S, Density rho)
{
EquationReturnType <PowerForStraightLevelFlight> ToReturn = new EquationReturnType <PowerForStraightLevelFlight>();
ToReturn.Data = new PowerForStraightLevelFlight();
ToReturn.Data.Set((Cd.Get() / Math.Pow(Cl.Get(), 3.0 / 2.0)) * Math.Sqrt((Math.Pow(m.Get() * g.Get(), 3) / S.Get())) * (Math.Sqrt(2 / rho.Get())));
ToReturn.Latex = @"\frac{" + Cd.Latex() + "}{" + Cl.Latex() + @"^{3/2}}\cdot \sqrt{\frac{(" + m.Latex() + @"\cdot " + g.Latex() + ")^{3}}{" + S.Latex() + @"}}\cdot \sqrt{\frac{2}{" + rho.Latex() + "}}";
return(ToReturn);
}
/// <summary>
/// Lift = Weight Condition
/// </summary>
/// <param name="m">Mass of Aircraft</param>
/// <param name="g">Acceleration Due to Gravity on Planet at Altitude</param>
/// <param name="Cl">Coefficient of Lift of Wing</param>
/// <param name="rho">Density of Air on Planet at Altitude</param>
/// <param name="S">Surface Area of Wing</param>
/// <returns>Velocity needed for straight level flight</returns>
public static EquationReturnType <Velocity> GetVelocity(Mass m, AccelerationDueToGravity g, LiftCoefficient Cl, Density rho, SurfaceArea S)
{
EquationReturnType <Velocity> ToReturn = new EquationReturnType <Velocity>();
ToReturn.Data = new Velocity();
ToReturn.Data.Set(Math.Sqrt((2 * m.Get() * g.Get()) / (Cl.Get() * rho.Get() * S.Get())));
ToReturn.Latex = @"\sqrt{\frac{2\cdot " + m.Latex() + @"\cdot " + g.Latex() + "}{" + Cl.Latex() + @"\cdot " + rho.Latex() + @"\cdot " + S.Latex() + "}}";
return(ToReturn);
}
