Steps and  deadlines
 

Step 1:  Linearly-twisted trapezoidal wing at low Mach number: test case.  Develop lifting-line calculation and find spanwise lift distribution.	Sep. 25
Step 2:  Find skin-friction drag per unit span at mid-semi-span for the above wing, using Thwaites method and the chord-wise pressure distribution for the flight condition of Step 1.	Sep. 25
Step 3:   Form teams of 2.  Select one aircraft for each person. Determine a high-subsonic steady level flight condition, and a supersonic steady level flight condition. Estimate the aircraft weight, and determine other parameters such as wing geometry, and engine thrust available, from data about the aircraft.  Note: Start on Steps 4 & 5 concurrently with Step 3!!	Oct. 26
Step 4:  Determine the drag at the subsonic flight condition, and therefore the thrust required.  Also, find the critical Mach number of the airfoil used for the wing at mid-semi-span, and plot this against angle of attack.  Thus estimate the critical Mach number for the aircraft wing and see if this represents a sensible estimate, considering the rest of the aircraft configuration.	Nov. 2
Step 5:  For the wing selected, find the pressure distribution at the wing mid-semi-span, at the supersonic level flight condition, using appropriate methods.Determine the aircraft drag at the supersonic flight condition, and therefore the thrust required.	Nov. 9
Step 6:  Validate the drag calculations.	Nov. 16
Step 7: Present your results.

Your individual web page must contain both team reports with all needed equations, figures, pictures etc, and your individual aircraft presentation.  Note: the presentation must be in big letters, condensed from report and suitable for the AE Design Lab projection system.