CoeffCalc.ipynb

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    "# Drag Coefficients \n",
    "substitute in the drag equation \n",
    "D = Cd * Ar * 0.5 * rho * (V**2)\n",
    "Cd is drag coefficient \n",
    "Ar is reference area \n",
    "rho is density of air \n",
    "v is velocity of the rocket at that instant \n"
   ]
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    "import math as m \n",
    "\n",
    "def DragCoeff(M, N, At, Ar, S, rl, tl,Abf, lc, cr, hr, tr, Awb, fb, Ab, Aw):\n",
    "    \n",
    "#M = Mach Number\n",
    "#N = number of Fins \n",
    "#At = Planform area of one exposed fin \n",
    "#Ar = reference Area \n",
    "#S = fin semi span\n",
    "#rl = fin leading edge radius \n",
    "#tl = leading edge sweep angle \n",
    "#Abf = base area of one fin \n",
    "#lc = midchord line sweep angle\n",
    "#cr = fin root chord\n",
    "#hr = root fin trailing edge thickness \n",
    "#tr = root fin thickness \n",
    "#Awb = wetted area of body\n",
    "#fb = body and nose fineness ratio \n",
    "#Ab = base area at tail \n",
    "#Aw = total wetted area \n",
    "\n",
    "    Cf = 1.328/((Re)**0.5)\n",
    "    Cfc = Cf*(1-(0.12*M*M))\n",
    "    Cfb = 2*Cf*(cr/hr)\n",
    "    Kdbt = ((1+((18*Cfc*(tr/hr)**2)/(N*(1-0.52)*(Abf/Ar)))) * ((0.135*N*(Abf/Ar))/(Cfc**(1/3)))) + ((m.cos(lc))**2)\n",
    "    del_Cd = ((1-(M**2))**-0.417)-1\n",
    "    Kdp = 1 + (((6.82*Awb*Cfc*((fn+0.7)**1.29))/((fb**3)*Ar))**(5/3))\n",
    "    Kdbb = 1 +  (1/((6.38 + 39.7*(hr/cr))(Cfc*(Aw/Ab))))\n",
    "    \n",
    "    \n",
    "    \n",
    "    CDft = 2*N*Cfc*(At/Ar)\n",
    "    CDlt = (2*N*S*rl*(m.cos(tl)**2)*del_Cd)/Ar\n",
    "    CDbt = (0.135*N*Abf)/(Ar*(Cfb**(1/3))*(Kdbt-M*M*(m.cos(lc))**2)**0.5)\n",
    "    CDtt = (4*N*Cfc) * (At/At) * ((tr/cr)*(m.cos(lc)**2) + ((30 * (tr/cr)**4 * m.cos(lc)**2) / ((K - M*M*(m.cos(lc)**2))**1.5)))       \n",
    "\n",
    "    Cdtt = CDft + CDlt + CDbt + CDtt\n",
    "\n",
    "    CDp = (6*Awb*Cfc) / (((fb)**3) * Ar * ((Kdp-(M**2))**0.6))\n",
    "    CDbb = (0.29*(Ab / Ar)) / ((Cfc*(Aw/Ab)*(Kdbb-(M**2)))**0.5)\n",
    "    \n",
    "    Cdtb = CDp + CDbb\n",
    "\n",
    "\n",
    "    Cd = Cdtt + Cdtb \n",
    "    return Cd \n",
    "\n",
    "\n",
    "Ar = 1 #Reference Area \n",
    "\n",
    "\n",
    "\n",
    "\n",
    "\n",
    "\n"
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   "source": [
    "# Normal Coefficients"
   ]
  },
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   "source": [
    "import math as m \n",
    "\n",
    "def NormalCoeff(Abn, Ar, Af, ar, rt, s, lc, M):  \n",
    "    \n",
    "#Abn = Nosecone Base Area\n",
    "#Ar = Reference Area \n",
    "#Af = total area of one fin \n",
    "#ar = aspect ratio\n",
    "#rt = body radius at tail \n",
    "#s = exposed fin semi span \n",
    "#lc = midchord line sweep angle \n",
    "#M = mach no. \n",
    "\n",
    "    B = (1-(M**2))**0.5\n",
    "    pi = 3.141592\n",
    "    tou = (s + rt)/rt\n",
    "\n",
    "\n",
    "    Cnab = 2 * (Abn / Ar)\n",
    "\n",
    "    Cnat = (N*pi*ar*(Af/Ar))/(2+(4+((B*ar)/(m.cos(lc)))**2)**0.5)\n",
    "    Ktb = (2/(pi*((1-(1/tou))**2)))*(((1+(1/(tou**2)))*(0.5*m.atan(0.5*(tou-(1/tou)))))-((1/(tou**2))*(tou - (t/tou)+ 2*m.atan(1/tou))))\n",
    "    Cnatb = Cnat * Ktb \n",
    "\n",
    "\n",
    "    Kbt = (((1-(1/(tou**2)))/(1-(t/tou)))**2) - Ktb \n",
    "    Cnabt = Cnat * Kbt \n",
    "\n",
    "    Cna = Cnab + Cnatb + Cnabt \n",
    "    \n",
    "    return Cna \n",
    "\n",
    "\n",
    "\n",
    "\n",
    "\n"
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   "source": [
    "# Moment Coefficient \n",
    "multiply this with the Thrust vector "
   ]
  },
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   "source": [
    "import math as m \n",
    "\n",
    "def MomentCoeff(xtb, xcg, Lr, q, v, rt, s, M, lc, Ar, Af, ar):\n",
    "    \n",
    "#xtb = longitudinal tail cp \n",
    "#xcg = location of cg from nosecone tip \n",
    "#Lr = length of rocket \n",
    "#q = pitch rate\n",
    "#v = velocity \n",
    "#rt = body radius at tail \n",
    "#s = exposed fin semi span \n",
    "#M = mach no. \n",
    "#lc = midchord line sweep angle \n",
    "#Ar = Reference Area \n",
    "#Af = total area of one fin \n",
    "#ar = aspect ratio\n",
    "\n",
    "    delx = xtb - xcg \n",
    "    B = (1-(M**2))**0.5\n",
    "    pi = 3.141592\n",
    "    tou = (s + rt)/rt\n",
    "    Ktb = (2/(pi*((1-(1/tou))**2)))*(((1+(1/(tou**2)))*(0.5*m.atan(0.5*(tou-(1/tou)))))-((1/(tou**2))*(tou - (t/tou)+ 2*m.atan(1/tou))))        \n",
    "    \n",
    "    Cnat = (N*pi*ar*(Af/Ar))/(2+(4+((B*ar)/(m.cos(lc)))**2)**0.5)\n",
    "    Kbt = (((1-(1/(tou**2)))/(1-(t/tou)))**2) - Ktb \n",
    "    Cnabt = Cnat * Kbt \n",
    "\n",
    "    Cm = Cnatb * (((delx)**2)/Lr) * (q/v)\n",
    "    \n",
    "    return Cm \n",
    "\n",
    "\n",
    "\n"
   ]
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