AeroE 241                 Homework 9                 Spring, 1995

An untwisted wing has been constucted using NACA 23012 airfoil 
sections and is to be tested in a wind tunnel under standard
atmosphere conditions.

The wing has the following characteristics:

     span       = 3 ft
     root chord = 7 in
     tip chord  = 5 in
     Oswald efficiencies:e=e1= .95 (estimated)
     speed      = 100 ft/s
     alpha      = 4 deg 
The wing is tapered such that the aerodynamic centers of the sections
are not swept foreward or back.
The model sting is supported 12 inches behind the wing root chord
leading edge.
 
Calculate the expected values of 

1. Wing Lift Coefficient
2. Wing Drag Coefficient
3. Wing Moment Coefficient about the aerodynamic center (Use the wing mean geometric chord as a reference chord)
4. Lift Force, lb
5. Drag Force, lb
6. Moment on Support, lb-ft (neglect drag contribution)

NOTE: Make sure you use the problem format specified in the notes.
      Sketch, label and dimension your system.

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