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Applied Aerodynamics - Airfoils and Wings
Rating: 4.3 out of 5(322 ratings)
2,577 students

Applied Aerodynamics - Airfoils and Wings

Aerodynamics, Aerodynamic Modeling, Wing and Airfoil analysis
Created byBruno Pacheco
Last updated 10/2025
English

What you'll learn

  • In-depth knowledge on aerodynamcs topics, supported by the coding of your own airfoil and wing analyzer
  • How to evaluate the characteristics of arifoils
  • Matlab coding applied to aerodynamics analysis
  • Design, simulate and optimize your own airfoil and wing designs
  • Vortex panel methods
  • Weissinger method
  • Estimate the stall angle of your wing designs
  • Vortex lattice method

Course content

4 sections • 23 lectures • 10h 14m total length

  • Instructor Presentation and Course Overview3:31

    Hello and welcome. Let's get to know each other and take a look what we will learn in this course.

    References for further studies:

    Fundamentals of Aerodynamics - John D. Anderson Jr.

    Aerodynamics for Engineers - John J. Bertin

    Foundations of Aerodynamics: Bases of Aerodynamic Design - Kuethe and Chow

    The Matlab version used in this course is 2020a. But if you follow the step by step instructions you can use any version after 2012a.

  • From Navier-Stokes to Potential Flow26:24

    We'll learn how to simplify the famous and difficult Navier-Stokes equations to more simple maths in order to allow a fast approach in analyzing airfoils.

  • Irrotationality of the velocity potential
  • Elementary flows16:00

    There are several elementary flows (source, sink, uniform, vortex, etc). In this section will learn how to derive and work with the uniform and vortex flow. Those are the ones that will be used in the future Vortex Panel Method we'll derive.

  • Airfoil Theory - Part 150:16

    In part 1 of the airfoil theory, the goal is to introduce the geometric characterisitcs and explain the physiscs behind lift generation.

    We'll also introduce the pressure coefficient concepts to pave the way to the airfoil analysis to be done on part 2.

  • Airfoil Theory - Part 245:40

    This part 2 will focus on the viscous theory and in the analysis of several design characteristics of airfoils.

    - NACA airfoils characteristics

    - Camber

    - Thickness

    - Leading edge radius

    - Flap deflection

  • Vortex Panel Method - Derivation1:16:25

    We will work on the theoretical derivation of the linear varying Vortex Panel Method. A lot of maths in this section, but it will greatly help our coding in the next lesson.

    The main sources for this section derivations are:

    1- Foundations of Aerodynamics: Bases of Aerodynamic Design - Arnold M. Kuethe / Chuen-yen Chow - 4th Ed - section 5.10

    2- Fundamentals of Aerodynamics - John D. Anderson - 3rd Ed - section 1.5


  • Vortex Panel Method Coding: Part 1 - Airfoil drawing31:12

    After the paved theoretical background from last lesson, let's get into Matlab and code our Panel Method for airfoil analysis.
    The first part is dedicated to the airfoils' drawing. We'll cover NACA 4 and 5 digit airfoils as well as general shapes that can be loaded via an Excel spreadsheet.

  • Vortex Panel Method Coding: Part 2 - Panel geometry17:28

    The second part is dedicated to defining and checking the panel geometry as defined in out theoretical lesson.

  • Vortex Panel Method Coding: Part 3 - Coefficients and Results21:11

    The third part is dedicated to calculating the linear coefficients from the A matrix and solve for zero normal velocities at the panels to determine the circulation and therefore, the lift, drag and moment coefficients.

  • Vortex Panel Method Coding: Part 4 - Streamlines plot29:40

    The last part is just to help the flow visualization by computing the streamlines around the airfoil.

  • Derivation of the general flow integral outside the airfoil
  • Checking the results
  • Exam 1
  • Panel Method Code0:03

    If you have a MATLAB version newer then 2016, you can open the live script (.mlx), otherwise, use the normal script (.m) VPM_lin

Requirements

  • Basic Engineering initial curriculum
  • Willingness to learn one of the most exciting topics in Aeronautical industry

Description

This course starts with a theoretical overview of the famous Navier-Stokes equations and how to simpllify them in order to get easier, yet insightful, potential equations for fast analysis.

Then we will focus in using these equations to derive the Vortex Panel Method (we'll cover all maths aspects also) and code it in Matlab. With that in hands, we will perform several analysis of generic airfoils to better understand how key design characteristics affect the overall results.

On the next section, we'll go from 2D world to 3D, analysing wings now. Similarly, we'll start with a theoretical review of the Weissinger method for general wings (we'll cover all maths aspects also) and then we'll create a Matlab code to simulate the designs. We'll invistigate how several key parameters, such as sweep, aspect ratio, twist and others, can affect the overall behavior of wings.

Finally, we'll include viscous effects on the Weissinger method for a more robust analysis, including flow separation and stall.

This course is filled with real examples and is a more hands-on approach on the analysis of airfoils and wings. If your are an engineering student, aviation enthusiast, industry or academic engineer or just want to learn more about how to apply Aerodynamic theory, this is the right course for you.

Who this course is for:

  • Those who are looking to have an in-depth understanding of aerodynamics
  • People interested in Engineering
  • Aviation enthusiasts in general
  • Those who want to work with Aerospace related Projects
  • Those who want to see a more applied approach in the topic, different from University
  • Aerospace Engineers
  • Mechanical Engineers
  • Those who want a hands-on experience in MATLAB programming

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