From 41f1f72e9502f5c3de6ca16b303803dfcf1df594 Mon Sep 17 00:00:00 2001 From: Thomas Stephen Lee Date: Fri, 4 Sep 2015 22:04:10 +0530 Subject: add/remove/update books --- Fluid_mechanics/Chapter_8.ipynb | 802 ---------------------------------------- 1 file changed, 802 deletions(-) delete mode 100755 Fluid_mechanics/Chapter_8.ipynb (limited to 'Fluid_mechanics/Chapter_8.ipynb') diff --git a/Fluid_mechanics/Chapter_8.ipynb b/Fluid_mechanics/Chapter_8.ipynb deleted file mode 100755 index 76c114d3..00000000 --- a/Fluid_mechanics/Chapter_8.ipynb +++ /dev/null @@ -1,802 +0,0 @@ -{ - "metadata": { - "name": "", - "signature": "sha256:f292d23876c88421bcfc8b761169402a2885837db02032e303215ae83f2c5cf5" - }, - "nbformat": 3, - "nbformat_minor": 0, - "worksheets": [ - { - "cells": [ - { - "cell_type": "heading", - "level": 1, - "metadata": {}, - "source": [ - "Chapter 8 - Fluid compressibility and incompressible flow" - ] - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 1 - Pg 323" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the initial and final volumes. Also, calculate the final temperature of the gas\n", - "#Initialization of variables\n", - "import math\n", - "pi=14.7 #psia\n", - "pf=50. #psia\n", - "cp=0.240 #Btu/lb R\n", - "cv=0.170 #Btu/lb R\n", - "J=778\n", - "T=60+459.6 #R\n", - "#calculations\n", - "R=J*(cp-cv)\n", - "k=cp/cv\n", - "gam=pi*144./(R*T)\n", - "V=1/gam\n", - "Vf=V*math.pow((pi/pf),(1/k))\n", - "Tf=T*(pf*Vf/(pi*V))\n", - "#results\n", - "print '%s %.2f %s' %(\"Initial volume =\",V,\"ft^3\")\n", - "print '%s %.2f %s' %(\"\\n Final volume =\",Vf,\"cu ft\")\n", - "print '%s %.1f %s' %(\"\\n Final temperature =\",Tf,\" R\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Initial volume = 13.37 ft^3\n", - "\n", - " Final volume = 5.62 cu ft\n", - "\n", - " Final temperature = 742.6 R\n" - ] - } - ], - "prompt_number": 2 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 2 - Pg 325" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the pressure difference across the pipe\n", - "#Initialization of variables\n", - "import math\n", - "ratio=0.99\n", - "E=3.19e5 #lb/in^2\n", - "#calculations\n", - "pd=-E*math.log(ratio)\n", - "#ersults\n", - "print '%s %d %s' %(\"Pressure difference =\",pd,\"psi\")\n", - "print '%s' %(\"The answers are a bit different from textbook due to rounding off error\")" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Pressure difference = 3206 psi\n", - "The answers are a bit different from textbook due to rounding off error\n" - ] - } - ], - "prompt_number": 3 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 3 - Pg 329" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the speed of test plane\n", - "#Initialization of variables\n", - "import math\n", - "k=1.4\n", - "g=32.2 #ft/s^2\n", - "R=53.3 #ft-lb/lb R\n", - "T=389.9 #R\n", - "Nm=2\n", - "#calculations\n", - "c=math.sqrt(k*g*R*T)\n", - "V=Nm*c*3600/5280.\n", - "#results\n", - "print '%s %.1f %s' %(\"Speed of test plane =\",V,\"mph\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Speed of test plane = 1319.9 mph\n" - ] - } - ], - "prompt_number": 4 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 4a - Pg 337" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the velocity at section 2\n", - "#Initialization of variables\n", - "import math\n", - "T1=584.6 #R\n", - "g=32.2 #ft/s^2\n", - "k=1.4\n", - "R=53.3 #ft-lb/lb R\n", - "V1=600 #ft/s\n", - "T2=519.6 #R\n", - "#calculations\n", - "Nm1=V1/(math.sqrt(k*g*R*T1))\n", - "Nm22= ((1+ (k-1)/2 *Nm1*Nm1)/(T2/T1) -1)*(2/(k-1))\n", - "Nm2=math.sqrt(Nm22)\n", - "V2=Nm2*math.sqrt(k*g*R*T2)\n", - "#results\n", - "print '%s %d %s' %(\"Velocity at section 2 =\",V2,\"ft/s\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Velocity at section 2 = 1068 ft/s\n" - ] - } - ], - "prompt_number": 4 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 4b - Pg 337" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the pressure difference between two stations\n", - "#Initialization of variables\n", - "import math\n", - "T1=584.6 #R\n", - "g=32.2 #ft/s^2\n", - "k=1.4\n", - "R=53.3 #ft-lb/lb R\n", - "V1=600 #ft/s\n", - "T2=519.6 #R\n", - "pa=14.7 #psi\n", - "p1=50 #psia\n", - "#calculations\n", - "Nm1=V1/(math.sqrt(k*g*R*T1))\n", - "Nm22= ((1+ (k-1)/2 *Nm1*Nm1)/(T2/T1) -1)*(2/(k-1))\n", - "Nm2=math.sqrt(Nm22)\n", - "pr=math.pow(((1+ (k-1)/2 *Nm1*Nm1)/(1+ (k-1)/2 *Nm2*Nm2)),(k/(k-1)))\n", - "p2=pr*(p1+pa)\n", - "dp=p1+pa-p2\n", - "#results\n", - "print '%s %.1f %s' %(\"Pressure difference between two stations =\",dp,\"psi\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Pressure difference between two stations = 21.9 psi\n" - ] - } - ], - "prompt_number": 5 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 4c - Pg 338" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the area ratio\n", - "#Initialization of variables\n", - "import math\n", - "T1=584.6 #R\n", - "g=32.2 #ft/s^2\n", - "k=1.4\n", - "R=53.3 #ft-lb/lb R\n", - "V1=600 #ft/s\n", - "T2=519.6 #R\n", - "#calculations\n", - "Nm1=V1/(math.sqrt(k*g*R*T1))\n", - "Nm22= ((1+ (k-1)/2 *Nm1*Nm1)/(T2/T1) -1)*(2/(k-1))\n", - "Nm2=math.sqrt(Nm22)\n", - "Ar= Nm1/Nm2 *math.pow(((1+ (k-1)/2 *Nm2*Nm2)/(1+ (k-1)/2 *Nm1*Nm1)),((k+1)/(2*(k-1))))\n", - "#results\n", - "print '%s %.3f' %(\"Area ratio = \",Ar)\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Area ratio = 0.754\n" - ] - } - ], - "prompt_number": 6 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 4d - Pg 338" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the density of air at both the stations\n", - "#Initialization of variables\n", - "import math\n", - "T1=584.6 #R\n", - "g=32.2 #ft/s^2\n", - "k=1.4\n", - "R=53.3 #ft-lb/lb R\n", - "V1=600 #ft/s\n", - "T2=519.6 #R\n", - "pa=14.7 #psi\n", - "p1=50 #psia\n", - "#calculations\n", - "Nm1=V1/(math.sqrt(k*g*R*T1))\n", - "Nm22= ((1+ (k-1)/2 *Nm1*Nm1)/(T2/T1) -1)*(2/(k-1))\n", - "Nm2=math.sqrt(Nm22)\n", - "pr=math.pow(((1+ (k-1)/2 *Nm1*Nm1)/(1+ (k-1)/2 *Nm2*Nm2)),(k/(k-1)))\n", - "p2=pr*(p1+pa)\n", - "rho1=(p1+pa)*144./(g*R*T1)\n", - "rho2=p2*144./(g*R*T2)\n", - "#results\n", - "print '%s %.5f %s' %(\"Density of air at station 1 =\",rho1,\"slug/ft^3\")\n", - "print '%s %.5f %s' %(\"\\n Density of air at station 2 =\",rho2,\"slug/ft^3\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Density of air at station 1 = 0.00929 slug/ft^3\n", - "\n", - " Density of air at station 2 = 0.00692 slug/ft^3\n" - ] - } - ], - "prompt_number": 7 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 5 - Pg 345" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the mass rate of air flow\n", - "#Initialization of variables\n", - "import math\n", - "p0=19.7 #psia\n", - "R=53.3 #lb-ft/lb-R\n", - "T0=539.6 #R\n", - "g=32.2 #ft/s^2\n", - "pa=14.7 #psia\n", - "d=1 #in\n", - "k=1.4\n", - "#calculations\n", - "rho0=p0*144/(g*R*T0)\n", - "pr=pa/p0\n", - "G=math.pi/4 *(d/12.)*(d/12.) *math.pow((2*k/(k-1) *p0*144*rho0),(0.5)) *math.pow((pr),(1/k)) *math.pow((1-math.pow(pr,((k-1)/k))),0.5)\n", - "#results\n", - "print '%s %.5f %s' %(\"Mass rate of air flow =\",G,\"slug/sec\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Mass rate of air flow = 0.00978 slug/sec\n" - ] - } - ], - "prompt_number": 8 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 6 - Pg 346" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the mass rate of air flow\n", - "#Initialization of variables\n", - "import math\n", - "p0=64.7 #psia\n", - "R=53.3 #lb-ft/lb-R\n", - "T0=539.6 #R\n", - "g=32.2 #ft/s^2\n", - "pa=14.7 #psia\n", - "d=1. #in\n", - "k=1.4\n", - "#calculations\n", - "rho0=p0*144/(g*R*T0)\n", - "pr=pa/p0\n", - "G=math.pi/4 *(d/12)*d/12. *math.pow((k*p0*144*rho0),(0.5)) *math.pow((2/(k+1)),((k+1)/(2*(k-1))))\n", - "#results\n", - "print '%s %.5f %s' %(\"Mass rate of air flow =\",G,\"slug/sec\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Mass rate of air flow = 0.03616 slug/sec\n" - ] - } - ], - "prompt_number": 9 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 7a - Pg 347" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the weight of air flow through the nozzle\n", - "#Initialization of variables\n", - "import math\n", - "k=1.4\n", - "R=53.3 #lb-ft/lb R\n", - "pe=14.7 #psia\n", - "p0=114.7 #psia\n", - "T0=524.6 #R\n", - "g=32.2 #ft/s^2\n", - "d=0.5 #in\n", - "#calculations\n", - "pr=pe/p0\n", - "prcr=0.528\n", - "pr=prcr*p0\n", - "rho0= p0*144/(g*R*T0)\n", - "G=math.pi/4 *(d/12)*d/12. *math.pow((k*p0*144*rho0),(0.5)) *math.pow((2/(k+1)),((k+1)/(2*(k-1))))\n", - "Wt=G*g\n", - "#results\n", - "print '%s %.4f %s' %(\"weight of air flow through the nozzle =\",Wt,\"lb/s\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "weight of air flow through the nozzle = 0.5233 lb/s\n" - ] - } - ], - "prompt_number": 10 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 7b - Pg 348" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the exit Mach number, exit velocity and the exit area\n", - "#Initialization of variables\n", - "import math\n", - "k=1.4\n", - "R=53.3 #lb-ft/lb R\n", - "pe=14.7 #psia\n", - "p0=114.7 #psia\n", - "T0=524.6 #R\n", - "g=32.2 #ft/s^2\n", - "d=0.5 #in\n", - "Nm1=1.\n", - "#calculations\n", - "pr=pe/p0\n", - "Nme=math.sqrt(2/(k-1) *(math.pow(1./pr,(k-1)/k) -1))\n", - "Te=T0/(1+ (k-1)/2 *Nme*Nme)\n", - "Ve=Nme*math.sqrt(k*g*R*Te)\n", - "At=math.pi/4. *(d)*d\n", - "Ae=Nm1/Nme *math.pow(((1+ (k-1)/2 *Nme*Nme)/(1+ (k-1)/2 *Nm1*Nm1)),((k+1)/(2*(k-1)))) *At\n", - "#results\n", - "print '%s %.2f' %(\"Mach number exit = \",Nme)\n", - "print '%s %d %s' %(\"\\n Exit velocity =\",Ve,\"ft/s\")\n", - "print '%s %.3f %s' %(\"\\n Exit area =\",Ae,\" in^2\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Mach number exit = 2.00\n", - "\n", - " Exit velocity = 1672 ft/s\n", - "\n", - " Exit area = 0.331 in^2\n" - ] - } - ], - "prompt_number": 11 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 8a - Pg 349" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the exit mass flow rate, pressure, temperature, velocity and mach number\n", - "#Initialization of variables\n", - "import math\n", - "k=1.4\n", - "R=53.3 #lb-ft/lb R\n", - "p0=100. #psia\n", - "T0=534.6 #R\n", - "g=32.2 #ft/s^2\n", - "d=0.5 #in\n", - "Nm1=1.\n", - "A=2./144. #ft^2\n", - "#calculations\n", - "print '%s' %(\"Exit mach number is found using trial and error\")\n", - "Nme=2.44\n", - "rho0=p0*144/(g*R*T0)\n", - "G= A*math.sqrt(k*p0*144*rho0) *math.pow((2/(k+1)),((k+1)/(2*(k-1))))\n", - "pe=p0*math.pow((1/(1+(k-1)/2 *Nme*Nme)),(k/(k-1)))\n", - "Te=T0/(1+ (k-1)/2 *Nme*Nme)\n", - "Ve=Nme*(math.sqrt(k*g*R*Te))\n", - "#results\n", - "print '%s %.3f %s' %(\"\\n Exit mass flow rate =\",G,\"slug/s\")\n", - "print '%s %.2f %s' %(\"\\n Exit pressure =\",pe,\"psia\")\n", - "print '%s %.1f %s' %(\"\\n Exit temperature =\",Te,\" R\")\n", - "print '%s %d %s' %(\"\\n Exit velocity =\",Ve,\"ft/s\")\n", - "print '%s %.2f' %(\"\\n Exit mach number = \",Nme)\n", - "print '%s' %(\"The answers are a bit different from textbook due to rounding off error\")" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Exit mach number is found using trial and error\n", - "\n", - " Exit mass flow rate = 0.143 slug/s\n", - "\n", - " Exit pressure = 6.43 psia\n", - "\n", - " Exit temperature = 244.0 R\n", - "\n", - " Exit velocity = 1868 ft/s\n", - "\n", - " Exit mach number = 2.44\n", - "The answers are a bit different from textbook due to rounding off error\n" - ] - } - ], - "prompt_number": 5 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 8b - Pg 350" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the exit mass flow rate, pressure, temperature,velocity and mach number\n", - "#Initialization of variables\n", - "import math\n", - "k=1.4\n", - "R=53.3 #lb-ft/lb R\n", - "p0=100. #psia\n", - "T0=534.6 #R\n", - "g=32.2 #ft/s^2\n", - "d=0.5 #in\n", - "Nm1=1.\n", - "A=2./144. #ft^2\n", - "#calculations\n", - "print '%s' %(\"Exit mach number is found using trial and error\")\n", - "Nme=0.24\n", - "rho0=p0*144/(g*R*T0)\n", - "G= A*math.sqrt(k*p0*144*rho0) *math.pow((2/(k+1)),((k+1)/(2*(k-1))))\n", - "pe=p0*math.pow((1/(1+(k-1)/2 *Nme*Nme)),(k/(k-1)))\n", - "Te=T0/(1+ (k-1)/2 *Nme*Nme)\n", - "Ve=Nme*(math.sqrt(k*g*R*Te))\n", - "#results\n", - "print '%s %.3f %s' %(\"\\n Exit mass flow rate =\",G,\"slug/s\")\n", - "print '%s %.2f %s' %(\"\\n Exit pressure =\",pe,\"psia\")\n", - "print '%s %.1f %s' %(\"\\n Exit temperature =\",Te,\" R\")\n", - "print '%s %d %s' %(\"\\n Exit velocity =\",Ve,\"ft/s\")\n", - "print '%s %.2f' %(\"\\n Exit mach number = \",Nme)\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Exit mach number is found using trial and error\n", - "\n", - " Exit mass flow rate = 0.143 slug/s\n", - "\n", - " Exit pressure = 96.07 psia\n", - "\n", - " Exit temperature = 528.5 R\n", - "\n", - " Exit velocity = 270 ft/s\n", - "\n", - " Exit mach number = 0.24\n" - ] - } - ], - "prompt_number": 13 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 9 - Pg 355" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the upstream Mach number, pressure, Temperature\n", - "#Initialization of variables\n", - "import math\n", - "k=1.4\n", - "R=53.3 #lb-ft/lb R\n", - "pu=6.43 #psia\n", - "Tu=244. #R\n", - "Nmu=2.44\n", - "#calculations\n", - "Nmd = math.sqrt(((k-1)*Nmu*Nmu +2)/(2*k*Nmu*Nmu - (k-1)))\n", - "pd=pu*(2*k*Nmu*Nmu - (k-1))/(k+1)\n", - "Td=Tu*(2*k*Nmu*Nmu - (k-1))/(k+1) *((k-1)*Nmu*Nmu +2)/((k+1)*Nmu*Nmu)\n", - "#results\n", - "print '%s %.3f' %(\"Mach number upstream = \",Nmd)\n", - "print '%s %.1f %s' %(\"\\n Pressure upstream =\",pd,\"psia\")\n", - "print '%s %.1f %s' %(\"\\n Temperature upstream =\",Td,\"R\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Mach number upstream = 0.519\n", - "\n", - " Pressure upstream = 43.6 psia\n", - "\n", - " Temperature upstream = 507.2 R\n" - ] - } - ], - "prompt_number": 14 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 10 - Pg 359" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the pressure and temperature at section 1\n", - "#Initialization of variables\n", - "import math\n", - "k=1.4\n", - "R=53.3 #lb-ft/lb R\n", - "e=0.0005 #ft\n", - "mu=3.77e-7 #lb-sec/ft^2\n", - "pe=14.7 #psia\n", - "Te=524.6 #R\n", - "g=32.2 #ft/s^2\n", - "Vi=12.5 #ft/s\n", - "l=6. #in\n", - "b=8. #in\n", - "L=100. #ft\n", - "#calculations\n", - "rhoe=pe*144/(R*g*Te)\n", - "Ve=Vi/(g*rhoe*(l*b/144.))\n", - "Nme=Ve/(math.sqrt(k*g*R*Te))\n", - "Rd=l*b/(2*(l+b)) /12.\n", - "rr=2*R/e\n", - "Nr=Ve*4*Rd*rhoe/mu\n", - "f=0.019\n", - "f2=1/(2*k) *(1/Nme*Nme -1) - (k+1)/(4*k) *math.log((1+ (k-1)/2 *Nme*Nme)/(Nme*Nme *(1+(k-1)/2)))\n", - "ff=f*L/(8*Rd) +f2\n", - "Nm1=0.305\n", - "Tr2=(1+ (k-1)/2 *Nm1*Nm1)/(1+ (k-1/2))\n", - "Tre=(1+ (k-1)/2 *Nme*Nme)/(1+ (k-1/2))\n", - "pr2=Nm1*math.pow((1+ (k-1)/2 *Nm1*Nm1),(0.5)) /math.pow((1+(k-1)/2),0.5)\n", - "pre=Nme*math.pow((1+ (k-1)/2 *Nme*Nme),(0.5)) /math.pow((1+(k-1)/2),0.5)\n", - "p1=pe/pr2 *pre\n", - "T1=Te/Tr2 *Tre\n", - "#results\n", - "print '%s %.1f %s' %(\"Pressure at section 1 =\",p1,\"psia\")\n", - "print '%s %.1f %s' %(\"\\n Tempreature at section 1 =\",T1,\"R\")\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Pressure at section 1 = 21.5 psia\n", - "\n", - " Tempreature at section 1 = 535.1 R\n" - ] - } - ], - "prompt_number": 15 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 11 - Pg 364" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "#calculate the limiting pressure and distance in both adiabatic and non-adiabatic cases\n", - "#Initialization of variables\n", - "import math\n", - "k=1.4\n", - "R=53.3 #lb-ft/lb R\n", - "g=32.2 #ft/s^2\n", - "T1=534.6 #R\n", - "V1=400. #ft/s\n", - "p1=350. #psia\n", - "f=0.02\n", - "D=6./12. #ft\n", - "#calculations\n", - "Nm1=V1/math.sqrt(k*g*R*T1)\n", - "Nm2= 1. /math.sqrt(k)\n", - "p2=p1*(Nm1)/Nm2\n", - "fl= math.log(Nm1/Nm2) + 1./(2.*k*Nm1*Nm1) *(1- Nm1*Nm1/Nm2*Nm2)\n", - "L12=fl*2*D/f\n", - "ps=p1*Nm1*math.pow((1+ (k-1)/2 *Nm1*Nm1),0.5) /math.pow((1+(k-1)/2),0.5)\n", - "Nm2=1.\n", - "fl2= -(k+1)/(4*k) *math.log((1+ (k-1)/2 *Nm1*Nm1)/(Nm1*Nm1 *(1+ (k-1)/2.))) + 1/(2*k*Nm1*Nm1) *(1- Nm1*Nm1 /Nm2*Nm2)\n", - "L2=fl2*2*D/f\n", - "#results\n", - "print '%s %.1f %s' %(\"Limiting pressure =\",p2,\" psia\")\n", - "print '%s %.1f %s' %(\"\\n Distance =\",L12,\" ft\")\n", - "print '%s %.1f %s' %(\"\\n Limiting pressure in adiabatic case =\",ps,\" psia\")\n", - "print '%s %.1f %s' %(\"\\n Distance required =\",L2,\"ft\")\n", - "print '%s' %(\"the answer is a bit different due to rounding of error in textbook\")" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Limiting pressure = 146.2 psia\n", - "\n", - " Distance = 81.8 ft\n", - "\n", - " Limiting pressure in adiabatic case = 114.2 psia\n", - "\n", - " Distance required = 84.2 ft\n", - "the answer is a bit different due to rounding of error in textbook\n" - ] - } - ], - "prompt_number": 16 - } - ], - "metadata": {} - } - ] -} \ No newline at end of file -- cgit