{
"metadata": {
"name": "",
"signature": "sha256:06f38e289e9f8216cfd07d87aec91d972c15f74d0ec70f7e3421fc091b17b1fb"
},
"nbformat": 3,
"nbformat_minor": 0,
"worksheets": [
{
"cells": [
{
"cell_type": "heading",
"level": 1,
"metadata": {},
"source": [
"Chapter11-Chemical Rocket and Hypersonic propulsion "
]
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex1-pg644"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"#calcualte Diameter of the SSME nozzle exit area\n",
"print(\"Example 11.1\")\n",
"\n",
"Ts=470000. ##in lb\n",
"Tv=375000. ##in lb\n",
"A2=(Ts-Tv)/(14.7*144.)\n",
"D=(4.*A2/math.pi)**(1./2.)\n",
"print'%s %.1f %s'%(\"Diameter of the SSME nozzle exit area :\",D,\"\")"
],
"language": "python",
"metadata": {},
"outputs": []
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex2-pg644"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"print(\"Example 11.2\")\n",
"#calculate rocket thurst and effective thurst\n",
"m=1000 ##in kg/s\n",
"g=9.8 ##m/s**2\n",
"Is=340. ##in s\n",
"F=m*g*Is\n",
"print'%s %.1f %s'%(\"(a)Rocket thrust F in N :\",F,\"\")\n",
"c=F/m\n",
"print'%s %.1f %s'%(\"(b)Effective exhaust velocity c in m/s :\",c,\"\")"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.2\n",
"(a)Rocket thrust F in N : 3332000.0 \n",
"(b)Effective exhaust velocity c in m/s : 3332.0 \n"
]
}
],
"prompt_number": 1
},
{
"cell_type": "heading",
"level": 1,
"metadata": {},
"source": [
"Ex3-pg646"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"print(\"Example 11.3\")\n",
"#calculate optimum thurst and nozzle exit mach number and nozzle area exapnsion\n",
"pc=200. ##in atm\n",
"p2=1. ##in atm\n",
"gm=1.3\n",
"Ath=25. ##in m**2\n",
"Cf=((2.*gm**2.)/(gm-1.)*(2./(gm+1.))**((gm+1.)/(gm-1.))*(1.-(p2/pc)**((gm-1.)/gm)))**(1/2.)\n",
"print'%s %.1f %s'%(\"(a)Optimum thrust coefficient Cf,opt :\",Cf,\"\")\n",
"pc=200.*101. ##converting to MPa\n",
"F=Ath*Cf*pc\n",
"print'%s %.1f %s'%(\"(b)thrust F in N\",F,\"\")\n",
"pc=200.\n",
"M2=((2./(gm-1.))*((pc/p2)**((gm-1.)/gm)-1.))**(1/2.)\n",
"print'%s %.1f %s'%(\"(c)Nozzle exit Mach no. M2 :\",M2,\"\")\n",
"A=1./M2*(2./(gm+1)*(1+(gm-1.)/2.*M2**2.))**((gm+1.)/(2.*(gm-1.)))\n",
"print'%s %.1f %s'%(\"(d)Nozzle area expansion ratio A2/Ath :\",A,\"\")\n"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.3\n",
"(a)Optimum thrust coefficient Cf,opt : 1.7 \n",
"(b)thrust F in N 833262.4 \n",
"(c)Nozzle exit Mach no. M2 : 4.0 \n",
"(d)Nozzle area expansion ratio A2/Ath : 15.9 \n"
]
}
],
"prompt_number": 2
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex4-pg648"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"print(\"Example 11.4\")\n",
"#estimate combustion gas constant and moleculare weight \n",
"Tc=2999 ##in K\n",
"Ccr=2432 ##in m/s\n",
"gm=1.26\n",
"f=4.02\n",
"R=((Ccr*gm*(2./(gm+1))**((gm+1.)/(2.*(gm-1))))**2.)/(gm*Tc)\n",
"print'%s %.1f %s'%(\"Combustion gas constant R in J/kg.K:\",R,\"\")\n",
"RU=8314.6 ##in j/kmol.K\n",
"MW=RU/R\n",
"print'%s %.1f %s'%(\"Molecular weight of the mixture in kg/kmol :\",MW,\"\")"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.4\n",
"Combustion gas constant R in J/kg.K: 858.9 \n",
"Molecular weight of the mixture in kg/kmol : 9.7 \n"
]
}
],
"prompt_number": 3
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex5-pg648"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"#calcualte The oxidizer-to-fuel mixture ratio and The molecular weight of the mixture of gases in the product of combustion in kg/kmol\n",
"import math\n",
"print(\"Example 11.5\")\n",
"\n",
"f=4.\n",
"MW=(2.*18+2*2)/4. ##from equation\n",
"print'%s %.1f %s'%(\"(a)The oxidizer-to-fuel mixture ratio :\",f,\"\")\n",
"print'%s %.1f %s'%(\"(b)The molecular weight of the mixture of gases in the product of combustion in kg/kmol:\",MW,\"\")"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.5\n",
"(a)The oxidizer-to-fuel mixture ratio : 4.0 \n",
"(b)The molecular weight of the mixture of gases in the product of combustion in kg/kmol: 10.0 \n"
]
}
],
"prompt_number": 4
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex6-pg651"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"print(\"Example 11.6\")\n",
"#calculate imporvement in Delv\n",
"g=9.8 ##in m/s**2\n",
"Is=400. ##in s\n",
"\n",
"delv1=g*Is*math.log(1./0.1) ##for pmf=0.9\n",
"delv2=g*Is*math.log(1./0.05) ##for pmf=0.95\n",
"delp=(delv2-delv1)/delv1*100.\n",
"print'%s %.1f %s'%(\"% improvement in delv :\",delp,\"\")"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.6\n",
"% improvement in delv : 30.1 \n"
]
}
],
"prompt_number": 7
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex7-pg653"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"#calcualte reduction in terminal speed\n",
"print(\"Example 11.7\")\n",
"\n",
"g=9.8 ##in m/s**2\n",
"Is=420. ##in s\n",
"the=90. ##in degree\n",
"tb=30. ##in s\n",
"gavg=9.65 ##in m/s**2\n",
"MR=0.1\n",
"delv1=-g*Is*math.log(MR) ##in m/s\n",
"delv2=-g*Is*math.log(MR)-gavg*tb\n",
"delp=abs(delv2-delv1)/delv1*100\n",
"print'%s %.1f %s'%(\"% reduction in terminal speed :\",delp,\"\")"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.7\n",
"% reduction in terminal speed : 3.1 \n"
]
}
],
"prompt_number": 9
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex8-pg656"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"print(\"Example 11.8\")\n",
"#calculate Terminal speed of rocket vehical excluding gravitatinal effect in m/s\n",
"mf=0.8\n",
"g=9.8 ##in m/s**2\n",
"Is=345. ##in s\n",
"delvt=-g*Is*math.log(1-mf)\n",
"m=500000. ##in kg\n",
"q0=100000. ##in Pa\n",
"tb=60. ##in s\n",
"Af=20.##in m**2\n",
"Cd=0.3 ##mean drag coefficient\n",
"delvd=math.log(1-mf)*(Af/m)*q0*(tb/(1-mf))*Cd\n",
"delv=delvt+delvd\n",
"print'%s %.1f %s'%(\"Terminal speed of rocket vehical excluding gravitatinal effect in m/s :\",delv,\"\")\n",
"\n"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.8\n",
"Terminal speed of rocket vehical excluding gravitatinal effect in m/s : 4862.1 \n"
]
}
],
"prompt_number": 10
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex9-pg660"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"#calcualte Effective exhaust speed and propulsive efficiency and Overall efficiency\n",
"print(\"Example 11.9\")\n",
"g=9.8 ##in m/s**2\n",
"Is=421. ##in s\n",
"Qr=120000000.\n",
"v=5000. ##in m/s\n",
"c=g*Is\n",
"print'%s %.1f %s'%(\"(a)Effective exhaust speed c in m/s :\",c,\"\")\n",
"ep=2.*(v/c)/(1.+(v/c)**2.)\n",
"print'%s %.1f %s'%(\"(b)propulsive efficiency :\",ep,\"\")\n",
"eo=c*v/Qr\n",
"print'%s %.1f %s'%(\"(c)Overall efficiency :\",eo,\"\")"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.9\n",
"(a)Effective exhaust speed c in m/s : 4125.8 \n",
"(b)propulsive efficiency : 1.0 \n",
"(c)Overall efficiency : 0.2 \n"
]
}
],
"prompt_number": 11
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex11-pg671"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"print(\"Example 11.11\")\n",
" #calcualte the new chamber pressure and burning rate and the corresponding reduction in burn time\n",
"p=7. ##in MPa, \n",
"n=0.5 ##and \n",
"a=5. ##cm/s \n",
"Tdg=15. ##in degree C\n",
"Td=15+273 ##in K\n",
"br=0.002 ##per degree C\n",
"pk=0.004 ##per degree C\n",
"t=60.##s, \n",
"\n",
"DT=30. ## temp difference in degree C\n",
"pc=p*(1.+pk*DT)\n",
"print'%s %.1f %s'%(\"(a)The new chamber pressure when the initial grain temp. is 45 degree C in MPa\",pc,\"\")\n",
"r=a*(pc/p)**n\n",
"r=r*(1+br*DT) ##correcting for the effect of the grain temperature on burning rate.\n",
"print'%s %.1f %s'%(\"Burning rate when grain temp. is 45 degree C\",r,\"\")\n",
"L=a*t/100.\n",
"tb=L*100./r ##time to burn 3m of end burning grain at 5.61cm/s\n",
"tbn=t*(p/pc) ##burn time for a constant total impulse\n",
"\n",
"dt=t-tb\n",
"print'%s %.1f %s'%(\"(b)The corresponding reduction in burn time in seconds:\",dt,\"\")\n",
"\n",
"\n",
"\n",
"\n",
"\n",
"\n",
"\n",
"\n",
"\n"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.11\n",
"(a)The new chamber pressure when the initial grain temp. is 45 degree C in MPa 7.8 \n",
"Burning rate when grain temp. is 45 degree C 5.6 \n",
"(b)The corresponding reduction in burn time in seconds: 6.5 \n"
]
}
],
"prompt_number": 12
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex12-pg678"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"#calculate heat flux and total heat flux and convection heat flux and wall temperature on the gas side \n",
"print(\"Example 11.12\")\n",
"Tg=2750. ##in K\n",
"Ttg=Tg\n",
"Tc=300. ## coolant bulk temp. in K\n",
"tw=0.002 ##Wall thickness in m\n",
"kw=43. ##thermal conductivity of the wall in W/m.C\n",
"hg=657. ##Gas side film coefficient in W/m**2K\n",
"hc=26000. ##Coolant side film coefficient in W/m**2K\n",
"eg=0.05 ##emissivity of the gas \n",
"sigma=5.67*10**(-8)##in W/m**2K\n",
"Taw=Ttg\n",
"\n",
"rhf=eg*sigma*Tg**4/1000.\n",
"print'%s %.1f %s'%(\"(a)The radiation heat flux in kW/m**2 :\",rhf,\"\")\n",
"qw=(Ttg-Tc+(rhf*1000./hg))/((1./hg)+(tw/kw)+(1./hc))/1000.\n",
"print'%s %.1f %s'%(\"(b)The total heat flux in kW/m**2:\",qw,\"\")\n",
"qc=qw-rhf\n",
"print'%s %.1f %s'%(\"(c)The convection heat in kW/m**2:\",qc,\"\")\n",
"Twg=Taw-qc*1000./hg\n",
"print'%s %.1f %s'%(\"(d)Wall temp. on the gas side in K:\",Twg,\"\")\n",
"Twc=Tc+(qw*1000./hc)\n",
"print'%s %.1f %s'%(\"(e)Wall temp. on the coolant side in K:\",Twc,\"\")\n",
"\n"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.12\n",
"(a)The radiation heat flux in kW/m**2 : 162.1 \n",
"(b)The total heat flux in kW/m**2: 1678.1 \n",
"(c)The convection heat in kW/m**2: 1516.0 \n",
"(d)Wall temp. on the gas side in K: 442.6 \n",
"(e)Wall temp. on the coolant side in K: 364.5 \n"
]
}
],
"prompt_number": 13
},
{
"cell_type": "heading",
"level": 1,
"metadata": {},
"source": [
"Ex13-pg690"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"import math\n",
"#calculate ratio of specific impulse\n",
"print(\"Example 11.13\")\n",
"\n",
"Cpg=2006. ##in J/kg.K\n",
"Cs=903. ##J/kg.K\n",
"X1=0.18\n",
"X2=0.16\n",
"Tr=1.057\n",
"Ir=(((1.-X1)*Cpg+X1*Cs)*Tr/((1.-X2)*Cpg+X2*Cs))**(1/2.) ##Ratio of specific impulse \n",
"print'%s %.3f %s'%(\"Raio of specific impulse :\",Ir,\"\")\n"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"Example 11.13\n",
"Raio of specific impulse : 1.022 \n"
]
}
],
"prompt_number": 14
}
],
"metadata": {}
}
]
}