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AeroDesign

The original version of this software was written by Dr. Jean-Jacques Chattot in Fortran. This C++ implementation has been created with the permission of Dr. Chattot.

The work done herein is based solely on the vortex line method outlined by Professors J.J. Chattot and M.M. Hafez [1]. The point of contact for questions should be directed to Carlos Pereyra.

Follow the sections below for compiling and using this package.

Build Instructions

Below are the steps required to compile this project.

step one, clone the repository

git clone https://github.com/Transonic-Integrated-AeroDesign/AeroDes

step two, change directory into AeroDes

cd AeroDes

step three, make a new build directory and change into it

mkdir build 
cd build

step four, build code with cmake utility and install to your system

cmake ../.
make
sudo make install

make compiles the code. make install installs the executables to your system.

Re-syncing your code with latest stuff

git fetch
git pull origin master

Depedencies

In order to compile the executables and the shared libraries, you will need the following packages on your computer.

Mac OS X

Windows

  • WSL 2
  • cmake
  • g++

Executables to Use

Listed below are the executables for various design tasks. If you have properly installed AeroDes with Cmake then these executables should be available.

There are two methods of using this code in your design process. You may either use the direct executables in linear fashion where you run each program separately. Or you may import the shared library resource. Lets go through both so you know how to use either of these resources.

ADcanareq
ADprandtline
ADwake
ADcfmactu
ADtsd

Each exectuable will of course require their own input parameters found in their respective examples directory.

See the AeroDes/examples/ directory for more details of running each module. Please actually read the readme.md files for how to use the examples for each of these executables.

Shared Library

Outlined here are instructions for writing your own C++ program utilizing the AeroDes library. Follow these steps for an understanding of importing and using certain functions within the AeroDes framework.

Include the AeroDes library like so.

#include "aerodes.hpp"  // includes definitions and objects

Create a main function. This function effectively does whatever is placed inside the parenthesis.

int main(int argc, char** argv) {
    ...
    return 1;
}

Inside the main function create the AeroDes object for calling canard wake program ('wk').

int main(int argc, char** argv) {
    AD *aero = new AD(argc, argv);    // create new aero object
    
    // aero->some_sub_object->function()
    
    // canard ADwake
    aero->wk->readInputPolar("polarbl.dat"); // reads in 2d polar from xfoil
    
    // canard equilibium
    aero->canary->readInputPolar("polarbl.dat"); // reads in 2d polar from xfoil
    
    delete aero;    // free memory at the end
    return 1;
}

Ultimately all the public functions in the src/wake, src/canareq, src/prandtline directories are accessible thorugh the *aero pointer. Here's a look at the full template C++ program.

main.cpp

#include <cstdlib>
#include <cstdio>
#include <vector>
#include <iostream> // std
#include <iomanip>  // setw
#include <sstream>  // istream
#include <fstream>  // fopen, ifstream
#include <string>
#include <stdio.h>  // strcpy
#include "aerodes.hpp"

int main(int argc, char** argv) {
    AD *aero = new AD(argc, argv);    // create new aero object

    // canard ADwake
    aero->wk->readInputPolar("polarbl.dat");

    // canard equilibium
    aero->canary->readInputPolar("polarbl.dat");
    
    delete aero;
    return 1;
}

Finally once the file above is complete; compile the sample C++ program like so.

g++ -o test main.cpp -laerolib

You absolutely must have the -laerolib flag in the compile line in order for your computer to find the aerodes.hpp library.

Documentation

This package is a compliment to XFoil [2] and can be used to design canard configured aircraft from start to finish. Typical work flows (seen below) obtain global aircraft CL, CD, CQ drag coefficients from the transformation of 2D polars to 3D polars along the wing span. The deployment of ADprandtline and ADcanarline modules perform these transformations for the main wing and canard wing in parallel.

See Normal Workflow and Advanced Workflow for design process.

Normal Workflow

When running the ADcanarline executable or canarline.f code, users must include the [0,...,1] (deg) sweep of the canard angle of attack in order to properly calculate dClda0, arceff, eceff. However in practice users may run tcd angles [0,1,2,...,etc.] (deg).

  flowchart TD;
      subgraph main-wing
        id10("geoprof.f") --->|"(i.e. Naca2017)"| id1(XFoil) -.->|"polarbl.dat \n (2d polar)"| id3(ADprandtline)
      end
      
      subgraph canard-wing
        id11("geoprof.f") --->|"(i.e. OneraD)"| id2(XFoil) -.->|"polarbl.dat \n (2d polar)"| id4(ADcanarline)
      end
      
      id5(ADcanareq)
      id4 -->|"dClcda0, arceff, eceff"| id5 
      id3 -->|"prandtline.clcdceq \n (3d polar)"| id5
Loading

Advanced Workflow

Shown in cyan blue is the feedback from the canard equilibrium code canareq.f or the executable ADcanareq which obtains the optimal canard setting angle tcd and aircraft angle theqd. It is intended that users will input these optimal settings into canarline.data, the input script for canarline.f.

  flowchart TD;
      subgraph main-wing
        id11("geoprof.f") --> id1(XFoil) -.->|"polarbl.dat \n (2d polar)"| id3(ADprandtline)
      end
      
      subgraph canard-wing
        id10("geoprof.f") --> id2(XFoil) -.->|"polarbl.dat \n (2d polar)"| id4(ADcanarline)
      end
      
      id5(ADcanareq)
      id4 --->|"dClcda0, arceff, eceff"| id5 
      id3 --->|"prandtline.clcdceq \n (3d polar)"| id5

      id4 --> |"canarwash.ylwl"| id3
      id5 -.->|"tcd,theqd"| id4
      
      linkStyle 5 stroke-width:2px,fill:none,stroke:red;
      linkStyle 4 stroke-width:2px,fill:none,stroke:red;
      linkStyle 6 stroke-width:2px,fill:none,stroke:cyan;
      linkStyle 7 stroke-width:2px,fill:none,stroke:cyan;
Loading

TSD Workflow

For acquiring the wave drag (Cdw) users are expected to utilize the tsd module/code. This process is highlighted in four main steps; (0) generate the number of discrete points, (1) generate a rudimentary 2D mesh, (2) linearly interpolate the 2D mesh, and (3) finally run the tsd.f or ADtsd (executable).

Note: We can use the air-brake (in canard-equilibrium) to implement the Cdw drag in addition to all other drag acting on the canard and main-wing.

Be aware that the interpolated mesh should be in the same directory as the tsd executable once it is compiled. See the directory structure below.

tsd/
├── geoprofortsd.data
├── geoprofortsd.f
├── geoprofortsd.xde
├── geoprofortsd.xzu
├── tsd.data
└── tsd.f

Here is a diagram of how these files are related. The overall process flow ranging from generating the linearly interpolated mesh points (given by Xfoil or online) and the transonic solver is shown below.

flowchart TD
    id6("tsd.f") -->|"'ile', 'ite'"| id2(geoprofortsd.f)
    id1(Xfoil) -.->|"geoprofortsd.xzu"| id2(geoprofortsd.f)
    id2(geoprofortsd.f) --> id7[/geoprofortsd.xzmses/]
    id5[/geoprofortsd.data/] --> id2(geoprofortsd.f)
    id2(geoprofortsd.f) -.->|"geoprofortsd.xde"| id3("tsd.f")
    id4[/tsd.data/] --> id3("tsd.f")
Loading

Sequentially, the zero'th step is to gather the number of discrete points in the mesh system. These will be defined in the variables ile and ite printed to screen when you run the tsd.f executable. The number of discrete points are of course dictated by dx0, dy0, dz0 variables set in the tsd data file. Gathering the number of discrete points is a matter of reading the text output and looking for the values corresponding to ile and ite.

Now the first step is to generate a rudimentary geometry file, called geoprofortsd.xzu. This file essentially contains the x-coordinates and upper thickness of your profile. This 2D foil (in Xfoil or any online resource there is) should be formatted with columns shown below.

x[i]   zu[i]
==   ===
x1    z1
x2    z2
...    ...

Second ensure geoprofortsd.xzu is in the same directory as geoprofortsd.f. This is also demonstrated in the tree directory printed previously (above). The purpose of running this code is to effectively smooth the profile and output a new profile into the appropriate format for tsd.f, called geoprofortsd.xde.

Third it should be noted that the full and complete profile for plotting is output to a file called geoprofortsd.xzmses for post processing and analysis.

Finally you may run tsd.f to solve for transonic flow around a symmetrical, thin airfoil.

Citation

Coming soon...

Contributors

  • Jean-Jacques Chattot, University of California, Davis, Professor
  • Carlos Pereyra, University of California, Davis, Grad. Student (czpereyra at ucdavis.edu)

References

[1] J. J. Chattot. and M.M. Hafez. Theoretical and Applied Aerodynamics and Related Numerical Methods. Springer Nether- lands, Dordrecht, 1st ed. 2015.

[2] Mark Drela. Xfoil: An analysis and design system for low reynolds number airfoils. In Thomas J. Mueller, editor, Low Reynolds Number Aerodynamics, pages 1–12, Berlin, Heidelberg, 1989. Springer Berlin Heidelberg.