Как позвонить или открыть онлайн калькулятор сайта и заполнить его автоматически для расчета для использования в задаче в кодировке Фортран?

Question

в этой кодировке я хочу открыть онлайн калькулятор сайта и использовать его для расчета в этой задаче. Итак, как можно позвонить или открыть эту страницу в Фортране.

program propulsion
  implicit none
  real(kind=4):: Mo, g=1.4,M9,a9,V9,gb=1.25, Pin=6.67
  real(kind=4):: Po, Pto, To, Tto,Pt2,Tt2,Pt21,Tt21,Pt3,Tt3is,Tt3,Tt3h,Tt5h,Tt4,Ttcc,Ptcc,Pt4,Tt9,Pt9,P9,T9,Tt4h
  real(kind=4):: teta, delta, pi, neta,y,D,Ma,Z,Mf,Phi,Rb,ra,Cpb,b,rho9,Rhoo,Aro,Ar9,ao,Vo,Tn,Tr,N,x
  integer,parameter::Dn=180
  Real::Cp=1005,Cph=14330,LH2=461000, Ttoh=21,Ro=287,Dst=34.04
  print*,"Enter the value of Mo"
  Read*, Mo
  print*,"Enter the value of Po"
  Read*, Po
  print*,"Enter the value of To"
  Read*, To
  Pto = Po*(1+((g-1)/2)*(Mo)**2)**(g/(g-1))
  Tto = To*(1+((g-1)/2)*(Mo)**2)
  write(*,*)"Pto", Pto,"Tto", Tto
   Tt2=Tto
  if (Mo<=1) then
    Pt2=Pto*0.95
    else
        Pt2= Pto*(0.95-(0.075*((Mo-1)**1.35)))
  end if
  write(*,*) "Pt2",Pt2,"Tt2",Tt2
   if (Mo<=2) then
     Tt21=Tt2
    else
    1 print*,"Enter the value of compressor inlet temperature"
  Read*, Tt21
  end if
   Pt21=0.9*Pt2
    write(*,*) "Pt21",Pt21,"Tt21",Tt21
    teta=Tt21/288
    delta=Pt21/1.013
     N=1/((teta)**0.5)
     Z = (-8.9249*((N)**5))+ (24.139*((N)**4)) - (22.441*((N)**3)) + (8.8606*((N)**2)) -(0.7158*(N)) + 0.0597
    write(*,*) "corrected mass flow rate", Z
    D=z*Dn
    Ma=(D*delta)/((teta)**0.5)
     write(*,*) "Ma",Ma,"delta",delta,"D",D
     write(*,*) "teta",teta
     write(*,*) "N",N
    Y= (0.9937*((Z)**4))-(1.5131*((Z)**3)) + (1.794*((Z)**2))- (0.2253*(Z)) + 0.0155
    write(*,*) "corrected pressure ratio",Y
neta=0.95-((100-(y*100))/240)
    pi=y*Pin
    Pt3=pi*Pt21
    Tt3is=Tt21*((pi)**((g-1)/g))
    Tt3=((Tt3is-Tt21)/neta)+Tt21
    write(*,*) "neta",neta
    write(*,*) "Pt3",Pt3,"Tt3",Tt3,"Tt3is",Tt3is
     2 print*,"Enter the value of Phi"
     Read*, Phi

 if (phi>1) then
    b=(70.64+((phi-1)*2))/(phi+1.8802)
    Rb=8314/b
    else if (phi==1) then
    Rb=338.604
    else
          b=(18*phi+((0.5-((phi)/2))*32)+57.06)/((phi/2)+2.5)
           Rb=8314/b
            end if
  write(*,*) "Rb",Rb
  Mf=(phi/Dst)*Ma
  write(*,*) "Mf",Mf
  ra=Ma/Mf
  Tt5h=Tt3
  Tt4h=(((Tt3-Tt21)*Ma*Cp)/(Mf*Cph))+Tt5h
  if(Tt4h>1200) then
    goto 2
  end if
  write(*,*) "Tt4h",Tt4h
  Cpb=(gb*Rb)/(gb-1)
  if (Mo<=2)then
    Tt3h=Ttoh
    else
        Tt3h=(((ra*Cp*(Tt2-Tt21))-LH2)/Cph)+Ttoh
  end if
  if (Tt3h>1600) then
    goto 1
  end if
  write(*,*) " EXIT TEMPERATURE OF PRE COOLER Tt3h",Tt3h
open(unit=10, file='http://elearning.cerfacs.fr/combustion/tools/adiabaticflametemperature/index.php')
  print*,"Enter the value of Ttcc"
  Read*, Ttcc
  If (Mo<=2) then
    Tt4=Ttcc-((LH2+Cph*(Tt4h-Tt3h))/(Cpb*(ra+1)))
  else
     Tt4=Ttcc-((Cph*(Tt4h-Tt3h))/(Cpb*(ra+1)))
     end if
     if (Tt4>2200) then
        goto 2
     end if
  write(*,*) "Tt4",Tt4
    write(*,*) "Cpb",Cpb
  Tt9=Tt4
  Ptcc=0.95*Pt3
  Pt4=0.9*Ptcc
  Pt9=Pt4
  P9=Po
  M9=((((Pt9/P9)**((gb-1)/gb))-1)*(2/(gb-1)))**0.5
  T9=Tt9*((1+((gb-1)/2)*(M9)**2)**(-1))
  a9=(gb*Rb*T9)**0.5
  V9=M9*a9
  ao=(g*Ro*To)**0.5
  Vo=Mo*ao
  write(*,*) "Ptcc",Ptcc,"Pt4",Pt4
  write(*,*) "Tt5h",Tt5h
  write(*,*) "Tt4",Tt4
  write(*,*) "Pt9",Pt9,"Tt9",Tt9
  write(*,*) "M9",M9,"a9",a9,"V9",V9
  write(*,*) "ao",ao,"Vo",Vo
  write(*,*) "T9",T9,"P9",P9
  Rho9=((10**5)*P9)/(Rb*T9)
  Ar9=(Ma+Mf)/(Rho9*V9)

   Rhoo=((10**5)*Po)/(Ro*To)
   Aro=(Ma)/(Rhoo*Vo)
    write(*,*) "Rho9",Rho9
    write(*,*) "Rhoo",Rhoo
    write(*,*) "A9",Ar9
    write(*,*) "Ao",Aro

     Tn=(((Ma+Mf)*V9)-Ma*Vo)+(A9*(P9-Po))
     Tr=0.5*Rhoo*((Vo)**2)*320*0.03
     x=Tr/Tn
     write(*,*) "Tn",Tn
     write(*,*) "Tr",Tr
     write(*,*) "thrust required by thrust available",x
   close(10)

  end program propulsion