Public Domain Aeronautical Software (PDAS)

The archive file induced.zip contains the files:

 readme.txt general information id.f90 module of induced drag functions and subroutines induced.f90 sample program illustrating use input.txt instructions for input to induced case1.ccl sample cases case2.ccl case3.ccl case4.ccl case1.out expected output from case1.ccl, etc. case2.out case3.out case4.out

To compile this program for your machine, use the command

gfortran induced.f90 -o induced.exe

Linux and Macintosh users may prefer to omit the .exe on the file name.

It is best if you compile the programs using your Fortran compiler with the appropriate options for your computer system. If you do not wish to do this, you may download inducedexecs.zip containing the files induced.exe, induced.mac, and induced.lnx, the executable program for Windows, Mac OS X, and Linux, each compiled generically for an Intel CPU.

In most textbooks on aerodynamics that treat the subject of finite-span wing theory, one usually sees a development of the concept of computing the induced drag of the wing from a knowledge of the spanwise load distribution. The load distribution is a function that defines ccl, i.e., the local chord multiplied by the local lift coefficient at each chord of the wing. This is done by developing the loading as a Fourier sine series and showing that the drag may be calculated from the coefficients of the series.

When a practising engineer is faced with making a numerical calculation of induced drag and plans to use this technique, the textbooks don't give very much support because one rarely has a mathematical expression for the span loading. Instead one usually has a few sparsely spaced values from a wind tunnel or flight test or a theoretical result from a grid that is usually more coarse than desired. The few examples where a numerical example is worked out usually suggest that the number of terms in the series expansion must be the same as the number of data points, and this is rarely enough to insure convergence.

In a note in the Journal of Aircraft, 1977, p. 309, Jerry Lundry described a simple algorithm for computing a curve that in one sense is the smoothest that exactly matches the data points and produces the Fourier sine coefficients as part of the solution. This technique and other similar algorithms are used widely by specialists but do not seem to be well documented and available to students. The routines given here are a coding of Lundry's equations 3 and 5 for asymmetric and symmetric loadings.

The essential routines are encapsulated in a Fortran module which is supplied as id.f90. The coefficients are computed with a call to subroutine ComputeFourierCoefficients. The drag may then be computed from the coefficients by use of the function DragFromCoefficients. Lift coefficient may also be computed. It is simply

PI*span*span*coeff(1)/sref.

If you want only the induced drag and not the coefficients, you may use the functions AsymmetricLoadingInducedDrag and SymmetricLoadingInducedDrag. They take the loadings and return D/q. Be sure to divide by the reference area if you want drag coefficient. Once you have compiled the module, you have access to any of the routines by putting the statement

USE InducedDrag