AG37 (ag37-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG37 (ag37-il) Reynolds number: 100,000 Max Cl/Cd: 49.78 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag37-il-100000-n5.txt Download as CSV file: xf-ag37-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG37
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5109 0.10416 0.09917 -0.0050 1.0000 0.0520
-9.750 -0.5147 0.10050 0.09559 -0.0106 1.0000 0.0527
-9.500 -0.5160 0.09645 0.09159 -0.0157 1.0000 0.0530
-9.250 -0.5122 0.09152 0.08667 -0.0221 1.0000 0.0531
-8.250 -0.4834 0.06785 0.06290 -0.0300 1.0000 0.0299
-8.000 -0.4744 0.06346 0.05847 -0.0320 1.0000 0.0291
-7.750 -0.4636 0.05853 0.05342 -0.0344 1.0000 0.0282
-7.500 -0.4511 0.05332 0.04801 -0.0368 1.0000 0.0274
-7.250 -0.4367 0.04800 0.04242 -0.0386 1.0000 0.0267
-7.000 -0.4206 0.04279 0.03684 -0.0398 1.0000 0.0261
-6.750 -0.4026 0.03817 0.03179 -0.0402 1.0000 0.0258
-6.500 -0.3828 0.03448 0.02766 -0.0401 1.0000 0.0263
-6.250 -0.3614 0.03153 0.02425 -0.0398 1.0000 0.0279
-6.000 -0.3387 0.02872 0.02089 -0.0392 1.0000 0.0292
-5.750 -0.3151 0.02619 0.01787 -0.0384 1.0000 0.0297
-5.500 -0.2909 0.02413 0.01536 -0.0376 1.0000 0.0304
-5.250 -0.2666 0.02220 0.01311 -0.0368 1.0000 0.0313
-5.000 -0.2431 0.02088 0.01173 -0.0362 1.0000 0.0338
-4.750 -0.2189 0.01989 0.01061 -0.0354 1.0000 0.0373
-4.500 -0.1942 0.01876 0.00932 -0.0346 1.0000 0.0395
-4.250 -0.1697 0.01769 0.00815 -0.0338 1.0000 0.0420
-4.000 -0.1457 0.01695 0.00746 -0.0332 1.0000 0.0480
-3.750 -0.1210 0.01627 0.00670 -0.0326 1.0000 0.0540
-3.500 -0.0963 0.01565 0.00609 -0.0321 1.0000 0.0644
-3.250 -0.0711 0.01503 0.00558 -0.0317 1.0000 0.0851
-3.000 -0.0385 0.01411 0.00514 -0.0331 0.9962 0.1827
-2.500 0.0398 0.01139 0.00493 -0.0367 0.9819 1.0000
-2.250 0.0832 0.01140 0.00466 -0.0399 0.9700 1.0000
-2.000 0.1238 0.01137 0.00444 -0.0425 0.9552 1.0000
-1.750 0.1601 0.01134 0.00424 -0.0441 0.9359 1.0000
-1.500 0.1959 0.01131 0.00407 -0.0455 0.9143 1.0000
-1.250 0.2284 0.01127 0.00391 -0.0461 0.8867 1.0000
-1.000 0.2642 0.01122 0.00371 -0.0473 0.8606 1.0000
-0.750 0.2973 0.01122 0.00354 -0.0478 0.8322 1.0000
-0.500 0.3271 0.01128 0.00344 -0.0477 0.8018 1.0000
-0.250 0.3547 0.01139 0.00339 -0.0472 0.7707 1.0000
0.000 0.3817 0.01155 0.00339 -0.0466 0.7395 1.0000
0.250 0.4082 0.01172 0.00343 -0.0461 0.7079 1.0000
0.500 0.4345 0.01190 0.00348 -0.0455 0.6757 1.0000
0.750 0.4606 0.01210 0.00355 -0.0449 0.6451 1.0000
1.000 0.4866 0.01235 0.00362 -0.0443 0.6193 1.0000
1.250 0.5127 0.01262 0.00374 -0.0438 0.5966 1.0000
1.500 0.5389 0.01290 0.00393 -0.0433 0.5748 1.0000
1.750 0.5650 0.01321 0.00416 -0.0429 0.5544 1.0000
2.000 0.5912 0.01350 0.00440 -0.0426 0.5346 1.0000
2.250 0.6174 0.01379 0.00466 -0.0422 0.5144 1.0000
2.500 0.6434 0.01410 0.00492 -0.0418 0.4945 1.0000
2.750 0.6695 0.01438 0.00524 -0.0415 0.4731 1.0000
3.000 0.6953 0.01466 0.00552 -0.0411 0.4508 1.0000
3.250 0.7210 0.01495 0.00581 -0.0408 0.4268 1.0000
3.500 0.7464 0.01526 0.00611 -0.0403 0.4016 1.0000
3.750 0.7715 0.01563 0.00646 -0.0399 0.3752 1.0000
4.000 0.7962 0.01603 0.00682 -0.0395 0.3475 1.0000
4.250 0.8208 0.01649 0.00723 -0.0390 0.3187 1.0000
4.500 0.8451 0.01698 0.00768 -0.0386 0.2885 1.0000
4.750 0.8691 0.01752 0.00821 -0.0382 0.2570 1.0000
5.000 0.8925 0.01814 0.00877 -0.0377 0.2242 1.0000
5.250 0.9156 0.01884 0.00940 -0.0373 0.1897 1.0000
5.500 0.9380 0.01966 0.01012 -0.0368 0.1559 1.0000
5.750 0.9595 0.02063 0.01100 -0.0362 0.1255 1.0000
6.000 0.9807 0.02166 0.01199 -0.0355 0.1021 1.0000
6.250 1.0009 0.02280 0.01307 -0.0348 0.0853 1.0000
6.500 1.0205 0.02400 0.01430 -0.0339 0.0741 1.0000
6.750 1.0406 0.02511 0.01556 -0.0331 0.0649 1.0000
7.000 1.0591 0.02640 0.01693 -0.0321 0.0581 1.0000
7.250 1.0775 0.02769 0.01834 -0.0310 0.0531 1.0000
7.500 1.0939 0.02923 0.01994 -0.0299 0.0489 1.0000
7.750 1.1122 0.03056 0.02149 -0.0288 0.0446 1.0000
8.000 1.1287 0.03209 0.02313 -0.0277 0.0416 1.0000
8.250 1.1428 0.03414 0.02522 -0.0264 0.0393 1.0000
8.500 1.1593 0.03583 0.02726 -0.0252 0.0367 1.0000
8.750 1.1737 0.03760 0.02929 -0.0240 0.0341 1.0000
9.000 1.1865 0.03959 0.03146 -0.0227 0.0324 1.0000
9.250 1.1974 0.04177 0.03379 -0.0214 0.0311 1.0000
9.500 1.2050 0.04467 0.03682 -0.0200 0.0298 1.0000
9.750 1.2087 0.04723 0.03983 -0.0181 0.0286 1.0000
10.000 1.2071 0.04995 0.04291 -0.0160 0.0275 1.0000
10.250 1.2011 0.05281 0.04608 -0.0138 0.0266 1.0000
10.500 1.1921 0.05614 0.04970 -0.0124 0.0260 1.0000
10.750 1.1802 0.06005 0.05388 -0.0119 0.0257 1.0000
11.000 1.1656 0.06465 0.05874 -0.0126 0.0254 1.0000
11.250 1.1483 0.07013 0.06448 -0.0148 0.0254 1.0000
11.500 1.1281 0.07677 0.07137 -0.0184 0.0254 1.0000
11.750 1.1039 0.08493 0.07977 -0.0237 0.0256 1.0000
12.000 1.0740 0.09510 0.09015 -0.0306 0.0261 1.0000
12.250 1.0375 0.10798 0.10318 -0.0391 0.0270 1.0000
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Polar data table (+)
Polar graphs
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