GOE 491 AIRFOIL (goe491-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 491 AIRFOIL (goe491-il) Reynolds number: 200,000 Max Cl/Cd: 62.8 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe491-il-200000.txt Download as CSV file: xf-goe491-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 491 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4900 0.10580 0.10216 -0.0033 1.0000 0.0325
-8.500 -0.4925 0.10391 0.10034 -0.0068 1.0000 0.0328
-8.250 -0.4928 0.10123 0.09770 -0.0090 1.0000 0.0329
-8.000 -0.4901 0.09824 0.09474 -0.0117 1.0000 0.0330
-7.750 -0.4836 0.09486 0.09136 -0.0145 1.0000 0.0330
-7.500 -0.4810 0.08945 0.08598 -0.0158 1.0000 0.0334
-7.250 -0.4773 0.08438 0.08095 -0.0122 1.0000 0.0342
-7.000 -0.4703 0.08096 0.07755 -0.0117 1.0000 0.0349
-6.750 -0.4630 0.07765 0.07424 -0.0122 1.0000 0.0358
-6.500 -0.4545 0.07438 0.07095 -0.0134 1.0000 0.0368
-6.250 -0.4447 0.07101 0.06756 -0.0149 1.0000 0.0381
-6.000 -0.4331 0.06761 0.06413 -0.0166 1.0000 0.0395
-5.750 -0.4180 0.06418 0.06064 -0.0188 1.0000 0.0417
-5.500 -0.3879 0.06183 0.05800 -0.0237 1.0000 0.0439
-5.250 -0.3700 0.05872 0.05472 -0.0242 1.0000 0.0442
-5.000 -0.3613 0.05281 0.04874 -0.0243 1.0000 0.0448
-4.750 -0.3521 0.04890 0.04487 -0.0232 1.0000 0.0458
-4.500 -0.3391 0.04602 0.04198 -0.0221 1.0000 0.0470
-4.250 -0.3237 0.04344 0.03934 -0.0212 1.0000 0.0496
-4.000 -0.2925 0.04258 0.03796 -0.0209 1.0000 0.0569
-3.750 -0.2807 0.03745 0.03266 -0.0198 1.0000 0.0581
-3.500 -0.2668 0.03438 0.02958 -0.0185 1.0000 0.0594
-3.250 -0.2505 0.03203 0.02714 -0.0169 1.0000 0.0610
-3.000 -0.2282 0.02620 0.02061 -0.0141 1.0000 0.0424
-2.750 -0.2099 0.02287 0.01690 -0.0120 1.0000 0.0406
-2.500 -0.1889 0.02032 0.01387 -0.0099 1.0000 0.0424
-2.250 -0.1670 0.01804 0.01107 -0.0081 1.0000 0.0450
-2.000 -0.1457 0.01664 0.00954 -0.0068 1.0000 0.0486
-1.750 -0.1232 0.01580 0.00844 -0.0053 1.0000 0.0555
-1.500 -0.1017 0.01515 0.00771 -0.0042 1.0000 0.0665
-1.250 -0.0796 0.01444 0.00687 -0.0030 1.0000 0.0771
-1.000 -0.0460 0.01409 0.00647 -0.0045 0.9964 0.0909
-0.750 -0.0020 0.01372 0.00595 -0.0078 0.9891 0.0986
-0.500 0.0411 0.01282 0.00514 -0.0110 0.9824 0.1055
-0.250 0.0830 0.01228 0.00460 -0.0138 0.9729 0.1110
0.000 0.1230 0.01165 0.00407 -0.0162 0.9623 0.1173
0.250 0.1638 0.01112 0.00364 -0.0188 0.9509 0.1297
0.500 0.2050 0.01057 0.00324 -0.0213 0.9389 0.1519
0.750 0.3066 0.00827 0.00319 -0.0371 0.9437 1.0000
1.000 0.3601 0.00806 0.00290 -0.0421 0.9196 1.0000
1.250 0.4183 0.00786 0.00256 -0.0480 0.8736 1.0000
1.500 0.4502 0.00794 0.00242 -0.0481 0.8040 1.0000
1.750 0.4733 0.00818 0.00235 -0.0464 0.7288 1.0000
2.000 0.4940 0.00854 0.00236 -0.0444 0.6619 1.0000
2.250 0.5149 0.00891 0.00244 -0.0427 0.6084 1.0000
2.500 0.5364 0.00925 0.00256 -0.0412 0.5658 1.0000
2.750 0.5576 0.00960 0.00267 -0.0397 0.5236 1.0000
3.000 0.5792 0.00993 0.00284 -0.0383 0.4868 1.0000
3.250 0.6018 0.01023 0.00302 -0.0372 0.4614 1.0000
3.500 0.6247 0.01052 0.00323 -0.0361 0.4397 1.0000
3.750 0.6478 0.01079 0.00346 -0.0351 0.4177 1.0000
4.000 0.6707 0.01106 0.00371 -0.0340 0.3953 1.0000
4.250 0.6938 0.01127 0.00393 -0.0330 0.3693 1.0000
4.500 0.7167 0.01150 0.00415 -0.0319 0.3394 1.0000
4.750 0.7392 0.01177 0.00436 -0.0308 0.2963 1.0000
5.000 0.7591 0.01240 0.00465 -0.0294 0.2150 1.0000
5.250 0.7744 0.01385 0.00541 -0.0275 0.0932 1.0000
5.500 0.7943 0.01476 0.00621 -0.0259 0.0714 1.0000
5.750 0.8148 0.01553 0.00702 -0.0245 0.0629 1.0000
6.000 0.8342 0.01642 0.00794 -0.0229 0.0563 1.0000
6.250 0.8531 0.01744 0.00905 -0.0212 0.0523 1.0000
6.500 0.8724 0.01841 0.01005 -0.0196 0.0467 1.0000
6.750 0.8878 0.02055 0.01222 -0.0175 0.0431 1.0000
7.000 0.9090 0.02173 0.01358 -0.0160 0.0405 1.0000
7.250 0.9291 0.02308 0.01505 -0.0145 0.0364 1.0000
7.500 0.9488 0.02506 0.01715 -0.0131 0.0343 1.0000
7.750 0.9675 0.02805 0.02034 -0.0116 0.0328 1.0000
8.000 0.9828 0.03207 0.02476 -0.0097 0.0320 1.0000
8.250 0.9958 0.03396 0.02712 -0.0074 0.0302 1.0000
8.500 1.0086 0.03633 0.02994 -0.0051 0.0292 1.0000
8.750 1.0160 0.04004 0.03408 -0.0026 0.0295 1.0000
9.000 1.0177 0.04463 0.03909 0.0000 0.0302 1.0000
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Polar data table (+)
Polar graphs
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