Back to **Aerodynamic Design of Aircraft with Computational Software**

Back to overview: **Preamble Exercises and Projects**

Chapter 8[pdf]:

8.1 Introduction to Airfoil Design

8.2 Subcritical-Speed Airfoils M < 0.7

8.3 Transonic Airfoils 0.7 < M < 0:9

8.4 Supersonic-Speed Airfoils 0.9 < M < 2

8.5 Multi-element Airfoils for High Lift

8.6 Optimization Example - ADODG Test Case RAE2822

**Exercises and Projects **– software here Tutorials, MSES, and SU2

**Review questions to consider before doing calculations**

- Explain the scenarios leading edge stall and trailing edge stall.

- Sketch pressure distributions for peaky, roof-top, and supercritical airfoils at Mach-numbers where the differences are of importance.

- Sketch the effect on the lift curve of applying leading edge slats and/or trailing edge flaps

(four cases !)

- Explain the “inverse mode” airfoil design principle

**Airfoil computations**

- The P-80 airfoil used in Fig. 8.9 is much thicker than the competitors in that graph and predictably comes in last in the race. Find the NACA65-213 airfoil coordinates e.g. on the
*UIUC airfoil data site*. Download the coordinates, write a program to read the file, scale y-coordinates to 10% thickness, and write to a new file. Complete that file to conform to the`blade.xxx`file format used for`mses`, and compute its transonic drag rise and compare to that of the other airfoils in Figure 8.9.

- Compare by
`msis`calculations the Goe298 and RAF15 airfoils at*M*and*Re*relevant for the WW 1 aircraft. The idea is to look for maximum lift. The RAF foil was used in the Ch. 5 exercises and many other foils are found there. You will find that`msis`gives up on the RAF foil with quite low c_{lmax}, even when the lift curve has only small slope decrease. Is this bona fide stall or just`msis`incompetence?

Look at the separation bubble movement on RAF foil. One may expect large-scale separation when the bubble moves into the high adverse pressure gradients at the foil nose. Is this what you observe? Compare to similar computations with the Goe298 foil.

- The c
_{lmax}problem is to be analyzed by RANS calculations for a naca2315 airfoil at M 0.5. Run an alpha sweep as high as`SU2`will converge with all-turbulent flow and Re for sea-level flight and a wing chord of 2 m. How does this compare to the`msis`results?