Wing sizing via constraint analysis

Let us consider a key step in the conceptual design of any fixed wing aircraft: the initial sizing of the wing. This follows the construction of a parametric geometry model, which establishes the shape of the wing – here we look at how to give it its initial scale.

A commonly used technique involves plotting the performance constraints contained in the design brief onto a single chart in the thrust to weight ratio (or power to weight ratio) versus wing wing loading space of the design (an example of such a chart is shown above).

In the book we discuss the construction of this type of chart in great detail and the interested reader may also wish to consult Snorri Gudmundsson’s rather excellent text on general aviation aircraft design.

This type of constraint analysis can be readily implemented in Excel, Matlab or just about any other programming language with a plotting library. The most convenient constraint analysis environment we have found, however, is a Jupyter notebook. These are parametric documents, which can contain text, diagrams and, most importantly, snipets of computer code (we use Python). The beauty of using a Jupyter notebook is that what results at the end of the constraint analysis process is a document capturing all the calculations and their results – this can be integrated into a report or used as a standalone components of the design audit trail.

Using Gudmundsson’s equations, we have captured the constraint analysis in a Jupyter notebook – or rather, two notebooks, one written in Python 2, another in Python 3. The notebooks are self-contained, save for one package: Kevin Horton’s Aero-Calc. This needs to be installed first before the notebooks can be run (a version translated into Python 3 can be found here). pip can be used to install the Python 2 version of the package (type pip install aerocalc in a terminal window); the Python 3 version can simply be copied to a folder where your Python installation looks for packages.

Design Optimization tools – some completely biased suggestions

These pages are all about parametric geometry. The ultimate goal of geometry parameterization is, however,  usually some type of systematic design search process guided by an objective function computed through a (most often numerical) analysis/simulation process. So, here are some suggestions for building blocks to create such a design search system.

We have a sister site called optimization.codes, following a format similar to this site’s. It is the home page of a book on engineering design via surrogate modeling, a technique that facilitates design search when the analysis code used to measure the performance of a design (a geometry) is expensive to compute. The site is also home to an extensive toolset, comprising Matlab code for generating sampling plans (design of experiments) and for building surrogate models based on these. It also includes code for surrogate-assisted optimization (expected improvement and error-based update schemes). Like over here, all that code is free to download.

If you’d prefer to do your surrogate modeling in Python, some of the same technology is implemented on pyKriging.com. As the name suggests, this is a Python implementation of the surrogate modeling technique called Kriging. The code also allows you to iteratively improve the accuracy of your surrogates via error-based updating – an expected improvement updates code is in the pipeline.

And finally, a suggestion if you are looking for a CFD capability to assist aircraft performance prediction. Chris Paulson has a free wrapper for OpenFOAM specially designed for the analysis of small to medium scale airframes – you can download it from DroneCFD.com.

AirCONICS v0.2.0 now available

The next major update to AirCONICS is now live and can be downloaded as described here. Here is a summary of what is new in this release:

– a major new addition is a parametric airliner geometry – run transonic_airliner.py to see it, uncomment the appropriate lines at the end of the file to get it to generate geometries approximating a few existing aircraft types (B787-8, -9, A380 – shown above).

– another new parametric model is the one adding a pylon and a turbofan engine
(external surface model) to a given wing surface – see engine.py

– AirCONICStools.py now includes the function AddTEtoOpenAirfoil, which adds a trailing edge closure to an open airfoil curve with a finite trailing edge.

– Another new addition to AirCONICStools.py is a simple routine for assigining
basic material properties to an object (AssignMaterial). This will have an effect
on renderings.

– The liftingsurface object now has an additional attribute, the variable
TipRequired. When set to False, the wing is not closed off with a tip surface
(see, for example, the script nacelle_as_wrapped_around_wing_example.py – here there is no such thing as a wing tip – it would be inside the nacelle, so it is
best not to generate it at all).

– the wing_example_transonic_airliner.py example script now features more realistic airfoils and twist distribution, loosely based on the CRM (Common Research Model)

– a tailfin/tailplane example has been added (airlinertail.py)

– A bug has been fixed in the liftingsurface class, which caused an error in the
calculation of the leading edge shape with certain highly non-linear sweep angle
variations

– Other improvements throughout the code improving performance, functionality
and stability

AirCONICS v0.2 to be released shortly…

A major update to AirCONICS is being tested and is due for release in the next few days. This includes a number of bug fixes and enhancements, as well as a parametric airliner model, built upon the AirCONICS lifting surface class and other methods included in the toolbox. Watch this space…

AirCONICS (Aircraft CONfiguration through Integrated Cross-disciplinary Scripting)

AirCONICS is a free collection of parametric geometries defined as Rhinoceros/Python objects and scripts. They use the OpenNURBS framework through Rhinoceros and they can be run (using the RunPythonScript command) in Rhinoceros. The MacOS X version of Rhinoceros is available for free, while a trial version is available for free under Windows (the latter also features a neat IDE for developing Python code). The fundamental principle behind AirCONICS is that conceptual and preliminary design geometries can be defined (and stored) as scripts. This allows for:

• easy parameterization of the geometry – all the variables of the code (including function handles) can be considered as potential parameters of the geometry
• portability
• the integration of complex design algorithms into the geometry – these can simply be part of the parametric ‘recipe’ that builds the geometry

You can get started with AirCONICS by downloading it here.

Aircraft geometry – tools, articles, and a forum for discussions

Edgar Schmued, the man responsible for the aerodynamic design of the P-51 Mustang, extolled the virtues of shapes “the air likes to touch”. Whether you like your air similarly anthropomorphic or not, the cornerstone of modern aircraft design is the parametric description of their shape. At the heart of every aircraft design process lies a geometry.

These pages are dedicated to the type of parametric aircraft geometry that exposes a design to optimization processes.

Ostensibly, this is a repository of the codes that accompany the book shown on the left and the Rhino/Python & Matlab code related to each chapter of the book can be found by clicking on the corresponding links on the left. We aim, however, to provide more than that: regular updates, applications and further free resources, as well as a forum for discussion on parametric aircraft geometry.

This site is also home to AirCONICS, a Rhino/Python aircraft parametric geometry code built upon the principles described in the book. Scroll down for updates on AirCONICS or click here to download it (it is free).