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Know All the Wright Angles
Activity Sheet #1
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 lowest force?
- For Test #44 looking at points #5-8, what is the difference in drag
between the lowest force and the highest force?
- Which angle of attack (alpha) overall generated the greatest amount
of lift?
- Which angle of attack (alpha) overall generated the least amount of
drag?
- Which angle of attack (alpha) overall generated the lowest L/D?
- Which angle of attack (alpha) overall generated the greatest L/D?
- For Run #43, looking at Points # 1-12, find the greatest L/D. __________
- For Run #43, looking at Points #1-10, give the number following the
greatest L/D.__________
- 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?
- Overall, which angle of attack (alpha) generates the greatest CL?
- From Run #43 point #4 to Run #44 point 8, which angle of attack (alpha)
generates the lowest CL?
- From Run #43 point #4 to Run #44 point 8, which angle of attack (alpha)
generates the greatest CD?
- From Run #43 point #4 to Run #44 point 8, which angle of attack (alpha)
generates the lowest CD?
- From Run #43 point #4 to Run #44 point 8, which angle of attack (alpha)
do you think is the stall angle? Explain your reasoning. (Hint: Look
over your answers for questions 7 – 12.)
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