On 27 Sept 2017, I gave a servo lecture to the UA senior design teams.

The lecture notes are at: ServoTalk

Aeronautical Physics, Math, and Engineering with Dr. Charles O'Neill

On 27 Sept 2017, I gave a servo lecture to the UA senior design teams.

The lecture notes are at: ServoTalk

Comments Off on ServoLecture

Posted in Uncategorized

Recently, someone asked a good question.

How can I find the aerodynamic properties of an airfoil?

Here’s my quick suggestion:

**Simple low-fidelity incompressible** (camber line only, but works amazingly well):

- Thin airfoil theory (Anderson, Fundamentals of Aerodynamics, Chapter 4)
- Lesson 13 at https://charles-oneill.com/aem313/

**Medium low fidelity incompressible** (camber and thickness)

- Panel methods (Katz & Plotkin book is best…)
- Lesson 12 at https://charles-oneill.com/aem614/

**Numerical incompressible** with boundary layers

- XFOIL software (free MIT software. My students have coupled it with other solvers. Lesson 12 at https://charles-oneill.com/aem313/)

**Expensive computational**

- CFD (don’t unless you need a compressible viscous solution)

Comments Off on Airfoil Characteristics

Posted in Uncategorized

AEM 368 is an introduction to aircraft dynamics including performance and stability and control. Dr. O’Neill taught this course in the Spring of 2017.Example Lectures:

Required Books:

*Flight Stability and Automatic Control*, R. Nelson, McGraw-Hill, 2^{nd}ed, 1998.*Aircraft Performance and Design*, John Anderson, McGraw-Hill, 1999.

**Goals:**

By the end of the course, students should be able to:

- Understand basic aircraft performance and stability and control (S&C) terminology
- Estimate aircraft performance in steady and accelerated flight mission phases
- Size S&C surfaces of an aircraft
- Demonstrate a physical and mathematical understanding of aircraft flight modes

**Topics:**

We will cover S&C and performance topics in the textbooks. Selected topics and sources supplement the text.

- Aircraft Nomenclature, Atmosphere, Instruments
- Static stability and control (FSAC, Chap 1)
- Aircraft equations of motion (FSAC, Chap 2)
- Longitudinal motion (FSAC, Chap 3)
- Lateral motion (FSAC, Chap 4)
- Steady Flight (APD, Chap 5)
- Accelerated Flight (APD, Chap 6)
- Aircraft Performance and Control Projects

Comments Off on Flight Dynamics and Control 1 (AEM 368)

Posted in Uncategorized

In the Fall of 2016, I taught AEM 313 Aerodynamics I.

**Objectives**: Introduction to subsonic aerodynamics, including properties of the atmosphere; aerodynamic characteristics of airfoils, wings, and other components; lift and drag phenomena; and topics of current interest.

**Required Book**: *Fundamentals of Aerodynamics*, John Anderson, McGraw-Hill, 5^{th} ed, 2010

**Topics: **

We will cover subsonic and transonic topics in the textbook. Selected topics and sources supplement the text.

- Conservation Equations
- Similarity Parameters
- Flow Kinematics
- Euler and Bernoulli Equation
- Velocity Potential and Stream Function
- Elementary Potential Flows
- Laminar and Turbulent Boundary Layers
- Airfoil and Wing Geometry
- Thin Airfoil Theory
- Lifting Line Theory (
**Example**: Lesson16-PrandtlLiftingLine) - Lift, Drag and Pitching Moment
- Low-Re and High-Alpha Effects
- Subsonic Compressible Flow
- Transonic and Supercritical Airfoils
- Aircraft Aerodynamic Design Project (MemoAEM313Project)

Student Evaluations (Fall 2016): 16C Charles O’Neill (AEM 313-001 Aerodynamics)

Comments Off on Aerodynamics I

Posted in Uncategorized

More soon…..

Comments Off on Induced Drag for Linearly Tapered Wings

Posted in Uncategorized

My son’s class has a stuffed animal as a class mascot, a worm named…. Wormie. Each child takes the worm home for a few days and shows the class what adventures Wormie had at home.

We decided to take Wormie up for a flight over Tuscaloosa. And this is not just any flight, but a aerobatic flight into the sunset. The result is one very happy son (and some neat photos).

Yes, the worm increased the drag considerably.

Comments Off on One happy son

Posted in Uncategorized

Prandtl Lifting Line theory remains an excellent tools for preliminary design and gaining intuition about the aerodynamics of unswept wings.

Implementing a PLL solver is relatively simple; I made this version in a few hours with Fortran. The solver generates SVG files displaying the wing geometry, gamma and lift distributions as well as the integrated lift and drag coefficients for arbitrary wing geometries (as approximated by linear sections). The program and input files are available at: https://charles-oneill.com/code/prandtl/prl2.zip

A flat elliptical wing demonstrates the flat sectional lift coefficient distribution resulting from an elliptical lift distribution.

The beauty of the Prandtl lifting line theory is the ability to modify the wing geometry and airfoil sections. For example, given a 20% flap deflected 20 degrees on inner wing sections, the sectional lift distribution reflects the flap deflection. Of particular interest is that the shed vorticity is proportional to the slope of the green lift distribution.

The PLL theory is also instructive for understanding control surface behaviors. In the following image, the 20% ailerons are deflected approximately +-10 degrees (Thin airfoil theory is used to determine the equivalent zero lift line.). Of particular concern is that aileron deflections at high AOA can push the local angle of attack into a stalled state.

Comments Off on Prandtl Lifting Line Tool

Posted in Uncategorized

**Unmanned Aerial Vehicles**

Thanks to the Civitan Club of Tuscaloosa and Mr. Brett Laney for the invitation to discuss unmanned vehicles and drones on the 5th of October 2016.

Presentation slides: uav-civitan

**Resources:**

- FAA Part 107 Rules
- Drone Flights at UA https://www.youtube.com/watch?v=SWdLy5ZUDAM
- Aerospace Engineering and Mechanics Department http://aem.eng.ua.edu/

Comments Off on Civitan Drone Talk

Posted in Uncategorized

**Can a flyable aircraft be designed and built in 1 hour?**

The Delta Wing Demonstrator is the result of this challenge in rapid aircraft design. Unfortunately, the answer was **no**. The aircraft actually required 1 hour and 20 minutes.

Comments Off on Delta Wing Demonstrator (DWD16)

Posted in Uncategorized

Back in 2006 as part of an independent study course, I used an inviscid CFD solver to estimate the aerodynamic performance of actual low aspect ratio wing configurations. The report (lowargeometryco2006.pdf) was written in a handbook style inspired by the classic Hoerner Lift and Drag books. The configurations were: monoplane, biplane, joined-tip biplane “box”, disc, monoplane with endplates, and a shroud cowl. Biplane gap, stagger, and decalage were considered. Performance criteria such as lift slope, induced drag, lift to drag ratio (L/D) were compared for multiple configurations and aspect ratios.The final portion of the report provides a visual display of the pressures and flow fields near the configurations.

Wake rollup of an AR=1 wing:

Wake aft of a biplane:

Pressure field interference with respect to biplane gap.

The full report from 2006 is available: LowARGeometryco2006.

The report was intended to support the OSU 2007 AIAA Design/Build/Fly teams during a competition year where the total aircraft span was severely limited:

Comments Off on Low Aspect Ratio Wings

Posted in Uncategorized