/// <summary>
/// формула 5.39
/// </summary>
/// <param name="wing"></param>
/// <param name="mach"></param>
/// <param name="mode">0 - alpha 1- delta</param>
/// <returns></returns>
public double Get_X_Fa_or_delta(WingOrient wing, double mach, int mode = 0)
{
var x_ak = wing.X + wing.Wing.X_ak;
var b_ak = wing.Wing.B_ak;
var x_graf = AeroGraphs.M2min1(mach) * wing.Wing.Lmb_k;
var y_graf = wing.Wing.Etta_k;
var z_graf = wing.Wing.Lmb_k * wing.Wing.GetTgHiM(0.5);
var x_Fizkr_shtr = AeroGr.GetV("5_8", x_graf, y_graf, z_graf);
var x_Fizkr = x_ak + b_ak * x_Fizkr_shtr;
var d_shtr = wing.Wing.D / wing.Wing.L;
var f_1 = AeroGr.GetV("5_11", d_shtr);
f_1 *= 0.5 * wing.Wing.L_k;
var x_Fdelta = x_Fizkr - f_1 * wing.Wing.GetTgHiM(0.5);
var x_b = wing.X + wing.Wing.X_b;
var b_b = wing.Wing.B_b;
var x_Fb_shtr = x_Fizkr_shtr + 0.02 * wing.Wing.Lmb_k * wing.Wing.GetTgHiM(0.5);
var f_Lhv = Get_F_Lhv(wing, mach);
var f_1Lhv = Get_F_1Lhv(wing, mach);
var x_Fif = x_b + b_b * x_Fb_shtr * f_Lhv * f_1Lhv;
var k = mode == 0 ?
Get_kaa(wing, mach, Aero_v, Aero_a) :
Get_kd0(wing, mach, Aero_v, Aero_a);
var K = mode == 0 ?
Get_Kaa(wing, mach, Aero_v, Aero_a) :
Get_kd0(wing, mach, Aero_v, Aero_a);
return((x_Fizkr + (k - 1) * x_Fdelta + (K - k) * x_Fif) / K);
}
public double Z_v_shtr(double mach)
{
var p1 = Lmb_k * AeroGraphs.M2min1(mach);
var p2 = Lmb_k * GetTgHiM(0.5);
var p3 = Etta_k;
return(AeroGr.GetV("3_16", p1, p2, p3));
}
public double GetCy1a(double mach)
{
if (AeroGr == null)
{
return(0.0);
}
return(Lmb_k * AeroGr.GetV("3_5", Lmb_k * AeroGraphs.M2min1(mach), Lmb_k * Math.Pow(C_shtr, 1.0 / 3.0), Lmb_k * GetTgHiM(0.5)));
}
public double Get_X_Fdelta(WingOrient wing, double mach)
{
var x_Fizkr = Get_X_Fizkr(wing, mach);
var d_shtr = wing.Wing.D / wing.Wing.L;
var f_1 = AeroGr.GetV("5_11", d_shtr);
f_1 *= 0.5 * wing.Wing.L_k;
return(x_Fizkr - f_1 * wing.Wing.GetTgHiM(0.5));
}
/// <summary>
/// Cx трения
/// </summary>
/// <param name="mach">мах</param>
/// <param name="x_t">относитальная точка перехода лам погр.слоя в турбул</param>
/// <param name="v">кинематическая вязкость среды</param>
/// <param name="a_m">местная скорость звука</param>
/// <returns></returns>
public double Cx_tr(double mach, double x_t, double v, double a_m)
{
var vel = mach * a_m;
var re = vel * L / v;
var _2CfM0 = AeroGr.GetV("4_2", re, x_t);
var etta = AeroGr.GetV("4_3", mach, x_t);
return(0.5 * _2CfM0 * etta * S_fuse / S_mid);
}
public double Get_X_Fizkr(WingOrient wing, double mach)
{
var x_ak = wing.X + wing.Wing.X_ak;
var b_ak = wing.Wing.B_ak;
var x_graf = AeroGraphs.M2min1(mach) * wing.Wing.Lmb_k;
var y_graf = wing.Wing.Etta_k;
var z_graf = wing.Wing.Lmb_k * wing.Wing.GetTgHiM(0.5);
var x_Fizkr_shtr = AeroGr.GetV("5_8", x_graf, y_graf, z_graf);
return(x_ak + b_ak * x_Fizkr_shtr);
}
public double Cx_tr(double mach, double x_t, double v, double a_m)
{
var vel = mach * a_m;
var re = vel * B_a / v;
var _2CfM0 = AeroGr.GetV("4_2", re, x_t);
var etta = AeroGr.GetV("4_3", mach, x_t);
var _2Cf = _2CfM0 * etta;
var etta_c = AeroGr.GetV("4_28", C_shtr, x_t);
return(_2Cf * etta_c);
}
public double Get_kt_II_shtr(double mach, double alpha)
{
double b_a_I = W_I.Wing.B_ak;
double x1 = W_I.X + W_I.Wing.X_ak + b_a_I;
double x2 = W_II.X + W_II.Wing.X_ak + 0.5 * W_II.Wing.B_ak;
double x = x2 - x1;
double x_shtr = x / b_a_I;
double k_t_star = AeroGr.GetV("3_22", mach, x_shtr);
double s_I = W_I.Wing.S_k;
double s_II = W_II.Wing.S_k;
return((k_t_star + s_II / s_I) / (1 + s_II / s_I));
}
public double Cx_v(double mach)
{
if (mach <= 1.0)
{
return(0.0);
}
double lmM21 = Lmb_k * AeroGraphs.M2min1(mach);
double lmbC3 = Lmb_k * Math.Pow(C_shtr, 1.0 / 3.0);
double lmbTgHi = Lmb_k * GetTgHiM(Profile.B_c_shtr);
double cx_romb = AeroGr.GetV("4_30", lmM21, lmbC3, lmbTgHi, Etta_k) * Lmb_k * C_shtr * C_shtr;
double fi = AeroGr.GetV("4_32", AeroGraphs.M2min1(mach) - GetTgHiM(Profile.B_c_shtr));
return(cx_romb * (1 + fi * (Profile.K - 1)));
}
public double Get_F_Lhv(WingOrient wing, double mach)
{
if (mach < 1.0)
{
return(1.0);
}
double d_shtr = Body.D / wing.Wing.L;
double b_b_shtr = wing.Wing.B_b / (0.5 * Math.PI * Body.D * Math.Sqrt(mach * mach - 1));
double l_hv = Body.L - wing.X - wing.Wing.X_b - wing.Wing.B_b;
double l_hv_shtr = l_hv / (0.5 * Math.PI * Body.D * Math.Sqrt(mach * mach - 1));
double c = (4 + 1 / wing.Wing.Etta_k) * (1 + 8 * d_shtr * d_shtr);
double lapl1 = AeroGr.GetV("gauss", (b_b_shtr + l_hv_shtr) * Math.Sqrt(2 * c));
double lapl2 = AeroGr.GetV("gauss", l_hv_shtr * Math.Sqrt(2 * c));
return(1.0 - (Math.Sqrt(Math.PI) * (lapl1 - lapl2)) / (2 * b_b_shtr * Math.Sqrt(c)));
}
public double Cx_korm(double mach)
{
if (D1 == D || L_korm == 0)
{
return(0);
}
double etta = D1 / D;
return(AeroGr.GetV("4_24", mach, Lmb_korm, etta));
//double S_dno_shtr = D1 * D1 / (D * D);
//double expr = D1 < D ?
// Math.Sqrt(1 - S_dno_shtr) :
// Math.Sqrt(S_dno_shtr * (S_dno_shtr - 1));
//double sinBetta = Math.Sin(Math.Atan(Math.Abs((D1 - D) * 0.5) / L_korm));
//double sinBettaSqr = sinBetta* sinBetta;
//return expr * (2.09 * sinBettaSqr + 0.19 * sinBettaSqr / Math.Sqrt(AeroGraphs.M2min1(mach)));
}
/// <summary>
/// формула 5.49
/// </summary>
/// <param name="wing"></param>
/// <param name="mach"></param>
/// <returns></returns>
public double Get_F_1Lhv(WingOrient wing, double mach)
{
if (mach < 1.0)
{
return(1.0);
}
double d_shtr = Body.D / wing.Wing.L;
double b_b_shtr = wing.Wing.B_b / (0.5 * Math.PI * Body.D * Math.Sqrt(mach * mach - 1));
double l_hv = Body.L - wing.X - wing.Wing.X_b - wing.Wing.B_b;
double l_hv_shtr = l_hv / (0.5 * Math.PI * Body.D * Math.Sqrt(mach * mach - 1));
double c = (4 + 1 / wing.Wing.Etta_k) * (1 + 8 * d_shtr * d_shtr);
var expr1 = (Math.Exp(-c * l_hv_shtr * l_hv_shtr) - Math.Exp(-c * (b_b_shtr + l_hv_shtr) * (b_b_shtr + l_hv_shtr))) / (c * b_b_shtr * b_b_shtr);
double lapl1 = AeroGr.GetV("gauss", l_hv_shtr * Math.Sqrt(2 * c));
var expr2 = Math.Sqrt(Math.PI) * lapl1 / (b_b_shtr * Math.Sqrt(c));
return(1.0 - expr1 + expr2);
}
public double Get_m_z_omg_z_wing(double x_ct, int mode)
{
double machm1 = mode == 2 ?
AeroGraphs.M2min1(M_II) :
AeroGraphs.M2min1(M_I);
double tg05 = mode == 2 ?
W_II.Wing.GetTgHiM(0.5) :
W_I.Wing.GetTgHiM(0.5);
double lmbk = mode == 2 ?
W_II.Wing.Lmb_k :
W_I.Wing.Lmb_k;
double etta = mode == 2 ?
W_II.Wing.Etta_k :
W_I.Wing.Etta_k;
double x_ak = mode == 2 ?
W_II.Wing.X_ak + W_II.X :
W_I.Wing.X_ak + W_I.X;
double b_ak = mode == 2 ?
W_II.Wing.B_ak :
W_I.Wing.B_ak;
var expr1 = AeroGr.GetV("5_15", lmbk * machm1, lmbk * tg05, etta);
var b1 = AeroGr.GetV("5_16", lmbk * machm1, lmbk * tg05, etta);
var x_t_shtr = (x_ct - x_ak) / b_ak;
//5.74
var mzCya_izkr = expr1 - b1 * (0.5 - x_t_shtr) - AeroGraphs._180divPI * (0.5 - x_t_shtr) * (0.5 - x_t_shtr);
var cyaIzkr = mode == 2 ?
Cy1a_II :
Cy1a_I;
var Kaa = mode == 2 ?
Kaa_II :
Kaa_I;
double delta_mz = 0.0;
if (mode == 2)
{
//5.82
var expr11 = (x_ct - (W_I.Wing.X_ak + W_I.X + 0.5 * W_I.Wing.B_ak)) / W_II.Wing.B_ak;
var expr12 = (x_ct - X_Fa_II) / W_II.Wing.B_ak;
delta_mz = -AeroGraphs._180divPI * Cy1a_II * Kaa_II * Eps_sr_a * expr11 * expr12;
}
return(mzCya_izkr * cyaIzkr * Kaa + delta_mz);
}
public double Get_A(double mach)
{
var cy1a = GetCy1a(mach);
double A;
if (mach <= 1.1)
{
A = AeroGr.GetV("3_35_M1", cy1a);
}
else if (mach >= 2.0)
{
A = AeroGr.GetV("3_35_M2", cy1a, 1.0 / Etta_k);
}
else
{
var A1 = AeroGr.GetV("3_35_M1", cy1a);
var A2 = AeroGr.GetV("3_35_M2", cy1a, 1.0 / Etta_k);
A = A1 + (mach - 1.1) * (A2 - A1) / (2.0 - 1.1);
}
return(A);
}
public double Get_eps_sr_alpha()
{
var z_v_shtr = W_I.Wing.Z_v_shtr(M_I);
var d_I = W_I.Wing.D;
var l_I = W_I.Wing.L;
var z_v = 0.5 * (d_I + z_v_shtr * (l_I - d_I));
var x_v = W_I.Wing.GetX(z_v) + W_I.Wing.GetB(z_v) - W_I.Wing.X_b - W_I.Wing.B_b * W_I.X_povor_otn;
var x_II = W_II.Wing.X_ak + W_II.Wing.B_ak * 0.5 -
W_I.Wing.X_b + W_I.Wing.B_b * W_I.X_povor_otn + x_v * Math.Cos(W_I.Delta * AeroGraphs.PIdiv180);
var y_II = 0.0;
var y_v = Math.Abs(x_II * SinAlpha - x_v * Math.Sin(W_I.Delta * AeroGraphs.PIdiv180) + y_II);
var _1_div_etta = 1 / W_II.Wing.Etta_k;
var _2zv_div_lII = 2.0 * z_v / W_II.Wing.L;
var _2yv_div_lII = 2.0 * y_v / W_II.Wing.L;
var d_II_shtr = W_II.Wing.D / W_II.Wing.L;
var i = AeroGr.GetV("3_17", _2zv_div_lII, _2yv_div_lII, d_II_shtr, _1_div_etta);
var ksi = 1.0;
return(AeroGraphs._180divPI * i * W_I.Wing.L_k * W_I.Wing.GetCy1a(M_I) * kaa_I * ksi / (2 * Math.PI * z_v_shtr * W_II.Wing.L_k * W_I.Wing.Lmb_k * Kaa_II));
}
public double Get_kt_I_shtr(double mach, double alpha)
{
double lmbda_nos;
if (Body.Nose is RocketNos_ConePlusCyl)
{
lmbda_nos = Body.Lmb_nos;
}
else
{
double cx_nos = Body.Cx_nose(mach);
InterpXY lmb_ot_Cx = new InterpXY();
foreach (var item in (AeroGr.Graphs["4_11"] as Interp2D)._data)
{
double lmb = item.Key;
double cx_tmp = item.Value.GetV(mach);
lmb_ot_Cx.Add(cx_tmp, lmb);
}
lmbda_nos = lmb_ot_Cx.GetV(cx_nos);
}
return(AeroGr.GetV("3_21", lmbda_nos, mach));
}
/// <summary>
/// 3.13
/// </summary>
/// <param name="mach"></param>
/// <returns></returns>
public double Get_hi_M(double mach)
{
return(AeroGr.GetV("3_13", mach));
}
public double Get_n(WingOrient wing, double mach)
{
var k_sh = AeroGr.GetV("k_shel", mach);
return(k_sh * Math.Cos(wing.Hi_rulei * AeroGraphs.PIdiv180));
}
