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Know All the Wright Angles
Activity Sheet #1
Key
Directions: Use the data table below to help the AIAA pilots answer
their questions.
NASA Ames 40 X 80 Foot Wind Tunnel
This data was collected on March 16, 1999 between 5-6:30 p.m. These
runs were taken with the engine off. A more complete
set of this data is available.
Note:This data is preliminary data. NASA reserves the right
to make changes to the data as the result of further analysis and reduction.
Any conclusions derived from these data are not endorsed by NASA.
| Run # |
Point # |
Alpha |
Lift, w |
Drag, w |
CL, w |
CD, w |
L/D |
| 43 |
1 |
-0.002 |
0 |
0 |
0 |
0 |
NaN |
| 43 |
2 |
-0.002 |
0 |
0 |
0 |
0 |
NaN |
| 43 |
3 |
-0.002 |
-0.493 |
10.374 |
-241.7 |
5085.4 |
-0.061 |
| 43 |
4 |
-0.002 |
637.9 |
126.78 |
0.644 |
0.128 |
5.506 |
| 43 |
5 |
-4.001 |
326.72 |
108.69 |
0.3274 |
0.1089 |
3.1078 |
| 43 |
6 |
-1.999 |
501.53 |
113.76 |
0.4943 |
0.1121 |
4.7027 |
| 43 |
7 |
-1.999 |
513.84 |
113.4 |
0.5088 |
0.1123 |
4.849 |
| 43 |
8 |
0.0006 |
667.28 |
125.54 |
0.6711 |
0.1263 |
5.8659 |
| 43 |
9 |
1.9998 |
812.15 |
143.15 |
0.8102 |
0.1428 |
6.4151 |
| 43 |
10 |
3.9844 |
939.25 |
167.53 |
0.9369 |
0.1671 |
6.4306 |
| 43 |
11 |
5.9992 |
1053.2 |
196.86 |
1.0878 |
0.2033 |
6.2076 |
| 43 |
12 |
0.0006 |
677.65 |
125.77 |
0.6728 |
0.1249 |
5.9556 |
| 44 |
1 |
0.0006 |
650.52 |
117.25 |
0.6482 |
0.1168 |
6.1334 |
| 44 |
2 |
-4.001 |
327.87 |
107.79 |
0.3264 |
0.1073 |
3.146 |
| 44 |
3 |
-1.999 |
474.87 |
109.7 |
0.4729 |
0.1092 |
4.6033 |
| 44 |
4 |
-9E-04 |
639.43 |
117.24 |
0.6392 |
0.1172 |
6.0127 |
| 44 |
5 |
1.9983 |
781.23 |
133.15 |
0.7713 |
0.1315 |
6.6302 |
| 44 |
6 |
3.9991 |
915.91 |
156.57 |
0.9235 |
0.1579 |
6.7413 |
| 44 |
7 |
5.9985 |
1044.6 |
186.31 |
1.0473 |
0.1868 |
6.5221 |
| 44 |
8 |
0.0006 |
644.5 |
117.09 |
0.6334 |
0.1151 |
6.0695 |
Last Updated on 3/24/99
- For Run #43 looking at points #4-11, what is the difference in lift
between the greatest force and the least force?
1053.20 greatest - 326.726 least = 726.48 difference
- For Run #44 looking at points #5-8, what is the difference in drag
between the greatest force and the least force?
186.31 greatest - 117.09 least = 69.22 difference
- Which angle of attack (alpha) overall generated the greatest amount
of lift?
5.9992 from Run #43 Point #11
- Which angle of attack (alpha) overall generated the least amount of
drag?
Run #43 Point #3 -0.002 Alpha with drag at 10.374
- Which angle of attack (alpha) overall generated the lowest positive
L/D?
Run#43 Point #5 generated L/D of 3.1078 at -4.001 alpha
- Which angle of attack (alpha) overall generated the greatest L/D?
3.9991 from Run#44 Point #6 generated L/D of 6.2076
- For Run #43, looking at Points #1-12, find the greatest L/D.
6.4306
- For Run #43, looking at Points #1-10, give the number following the
greatest L/D.
6.2076
- Using the information from questions 7 and 8, what is the angle of
attack (alpha) at which the glider is not generating as much lift as
it was before?
5.9992 from Run #43 Point #1
- Overall, which angle of attack (alpha) generates the greatest CL?
5.9992 from Run #43 Point #1
- From Run #43 Point #4 to Run #44 Point #8, which angle of attack (alpha)
generates the lowest CL?
Run #44 Point #2 0.3264
- From Run #43 Point #4 to Run #44 Point #8, which angle of attack (alpha)
generates the greatest CD?
Run #43 Point #11 0.2033
- From Run #43 Point #4 to Run #44 Point #8, which angle of attack (alpha)
generates the lowest CD?
Run #44 Point #2 0.1073
- Overall, which angle of attack (alpha) do you think is the stall angle?
Explain your reasoning. (Hint: Look over your answers for questions
7 - 12.)
The angle between alpha 3.9844 and 5.9992 because lift is not increasing
as much as before and drag is increasing a lot, and the L/D drops almost
0.2.
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