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Optimal Lift-to-Drag Ratio
Core Numerical Engine in Fortran 90 • 24 total downloads
optimal_ld.f90
! =========================================================================
! Source File: optimal_ld.f90
! =========================================================================
!==============================================================================
! ThermoFluidCalc — Calculator #25 : Optimal L/D Ratio
!==============================================================================
! Physics : For a parabolic drag polar CD = CD0 + CL^2 / (pi*e*AR) :
!
! Max Range (max L/D) : CDi = CD0
! CL = sqrt(pi*e*AR*CD0) , (L/D)_max = 1/(2*sqrt(CD0/(pi*e*AR)))
!
! Max Endurance (min CL^(3/2)/CD) : CDi = 3*CD0
! CL = sqrt(3*pi*e*AR*CD0)
!
! Max Climb Rate (min excess power) : CDi = CD0/3
! CL = sqrt(pi*e*AR*CD0/3)
!
! V_opt = sqrt(2*W / (rho*S*CL_opt))
!
! Reference : Gupta, Appendix 7.2
!
! Build:
! gfortran -O2 -o optimal_ld optimal_ld.f90
!
! Input (stdin, one line):
! CD0 e AR rho S W CL_max npts_sensitivity
!==============================================================================
program optimal_ld
implicit none
integer, parameter :: dp = selected_real_kind(15, 307)
real(dp), parameter :: PI = 3.141592653589793238_dp
integer, parameter :: MAX_PTS = 2000
integer :: npts, i
real(dp) :: CD0, e, AR, rho, S, W, CL_max
real(dp) :: k ! k = 1/(pi*e*AR)
! Max range
real(dp) :: CL_r, CD_r, LD_r, V_r
! Max endurance
real(dp) :: CL_e, CD_e, LD_e, V_e
! Max climb
real(dp) :: CL_c, CD_c, LD_c, V_c
! Min speed
real(dp) :: V_min, CD_min, LD_min
! Sensitivity
real(dp) :: cd0_lo, cd0_hi, dcd0, cd0_v, cl_v, ld_v
read(*,*) CD0, e, AR, rho, S, W, CL_max, npts
! Validate
if (CD0 <= 0.0_dp) then; write(*,'(A)') 'ERROR=CD0 must be positive.'; stop; end if
if (e <= 0.0_dp .or. e > 1.0_dp) then; write(*,'(A)') 'ERROR=Oswald e must be (0,1].'; stop; end if
if (AR <= 0.0_dp) then; write(*,'(A)') 'ERROR=AR must be positive.'; stop; end if
if (rho <= 0.0_dp) then; write(*,'(A)') 'ERROR=Density must be positive.'; stop; end if
if (S <= 0.0_dp) then; write(*,'(A)') 'ERROR=Wing area must be positive.'; stop; end if
if (W <= 0.0_dp) then; write(*,'(A)') 'ERROR=Weight must be positive.'; stop; end if
if (CL_max <= 0.0_dp) then; write(*,'(A)') 'ERROR=CL_max must be positive.'; stop; end if
if (npts < 5) npts = 5
if (npts > MAX_PTS) npts = MAX_PTS
k = 1.0_dp / (PI * e * AR)
! ── 1. Max Range (CDi = CD0) ──────────────────────────────────────────
CL_r = sqrt(CD0 / k) ! = sqrt(pi*e*AR*CD0)
CD_r = 2.0_dp * CD0
LD_r = CL_r / CD_r
V_r = sqrt(2.0_dp * W / (rho * S * CL_r))
! ── 2. Max Endurance (CDi = 3*CD0) ────────────────────────────────────
CL_e = sqrt(3.0_dp * CD0 / k)
CD_e = 4.0_dp * CD0
LD_e = CL_e / CD_e
V_e = sqrt(2.0_dp * W / (rho * S * CL_e))
! ── 3. Max Climb Rate (CDi = CD0/3) ──────────────────────────────────
CL_c = sqrt(CD0 / (3.0_dp * k))
CD_c = CD0 + CD0 / 3.0_dp ! = 4/3 CD0
LD_c = CL_c / CD_c
V_c = sqrt(2.0_dp * W / (rho * S * CL_c))
! ── 4. Minimum speed ──────────────────────────────────────────────────
V_min = sqrt(2.0_dp * W / (rho * S * CL_max))
CD_min = CD0 + CL_max**2 * k
if (CD_min > 0.0_dp) then
LD_min = CL_max / CD_min
else
LD_min = 0.0_dp
end if
! ── Output ────────────────────────────────────────────────────────────
write(*,'(A,ES15.8)') 'CD0=', CD0
write(*,'(A,F8.4)') 'OSWALD_E=', e
write(*,'(A,F10.4)') 'AR=', AR
write(*,'(A,ES15.8)') 'RHO=', rho
write(*,'(A,ES15.8)') 'S=', S
write(*,'(A,ES15.8)') 'W=', W
write(*,'(A,F8.4)') 'CL_MAX=', CL_max
write(*,'(A,ES15.8)') 'K=', k
! Range
write(*,'(A,F10.6)') 'CL_RANGE=', CL_r
write(*,'(A,F10.6)') 'CD_RANGE=', CD_r
write(*,'(A,F10.4)') 'LD_RANGE=', LD_r
write(*,'(A,F10.3)') 'V_RANGE=', V_r
! Endurance
write(*,'(A,F10.6)') 'CL_ENDUR=', CL_e
write(*,'(A,F10.6)') 'CD_ENDUR=', CD_e
write(*,'(A,F10.4)') 'LD_ENDUR=', LD_e
write(*,'(A,F10.3)') 'V_ENDUR=', V_e
! Climb
write(*,'(A,F10.6)') 'CL_CLIMB=', CL_c
write(*,'(A,F10.6)') 'CD_CLIMB=', CD_c
write(*,'(A,F10.4)') 'LD_CLIMB=', LD_c
write(*,'(A,F10.3)') 'V_CLIMB=', V_c
! Min speed
write(*,'(A,F10.3)') 'V_MIN=', V_min
write(*,'(A,F10.6)') 'CD_VMIN=', CD_min
write(*,'(A,F10.4)') 'LD_VMIN=', LD_min
! ── Sensitivity sweep ─────────────────────────────────────────────────
cd0_lo = 0.5_dp * CD0
cd0_hi = 2.0_dp * CD0
dcd0 = (cd0_hi - cd0_lo) / real(npts - 1, dp)
write(*,'(A)') 'SENSITIVITY_START'
do i = 0, npts - 1
cd0_v = cd0_lo + real(i, dp) * dcd0
cl_v = sqrt(cd0_v / k)
ld_v = cl_v / (2.0_dp * cd0_v)
write(*,'(ES15.8,A,F12.4)') cd0_v, ',', ld_v
end do
write(*,'(A)') 'SENSITIVITY_END'
end program optimal_ld
Solver Description
Determine the maximum lift-to-drag ratio (L/D) and optimal cruise angle of attack for aircraft wings.
Key Numerical Methods & Architecture
- Input Redirection: Reads parameters sequentially from standard input (`stdin`) using Fortran sequential read (`read(*,*)`), ensuring modular integration.
- Modular Design: Formulated using pure mathematical routines, separation of equations from output formatting, and precise numerical solvers (e.g. bisection, Newton-Raphson).
- Standard Compliant: Written in clean, standards-compliant Fortran 90 to ensure cross-compiler compatibility.
🛠️ Local Compilation
To test this code on your machine, compile the source code file(s) using a standard Fortran compiler (e.g., `gfortran`).
Compilation Command:
gfortran -O3 optimal_ld.f90 -o optimal_ld
Execution Command:
Execute the program by feeding the sample input file into the program using stdin redirection:
optimal_ld < input.txt
📥 Downloads & Local Files
Preview of the required input file (input.txt):
! CD0\ne (Oswald)\nAR\n(kg/m³)\nS wing area (m²)\nW weight (N)\nCL,max\nSensitivity pts
0.034
! Parameter 2
0.8
! Parameter 3
7.46
! Parameter 4
1.225
! Parameter 5
16.2
! Parameter 6
10680
! Parameter 7
1.6
! Parameter 8
100
0.034
! Parameter 2
0.8
! Parameter 3
7.46
! Parameter 4
1.225
! Parameter 5
16.2
! Parameter 6
10680
! Parameter 7
1.6
! Parameter 8
100