AG37 (ag37-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG37 (ag37-il) Reynolds number: 50,000 Max Cl/Cd: 36.42 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag37-il-50000-n5.txt Download as CSV file: xf-ag37-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4005 0.09283 0.08633 -0.0117 1.0000 0.1264
-9.250 -0.4003 0.08899 0.08254 -0.0126 1.0000 0.1270
-9.000 -0.5053 0.09046 0.08363 -0.0188 1.0000 0.0657
-8.750 -0.4959 0.08665 0.07982 -0.0175 1.0000 0.0637
-8.250 -0.4842 0.07394 0.06694 -0.0307 1.0000 0.0529
-7.750 -0.4639 0.06560 0.05851 -0.0326 1.0000 0.0513
-7.500 -0.4521 0.06117 0.05397 -0.0343 1.0000 0.0502
-7.250 -0.4386 0.05661 0.04922 -0.0361 1.0000 0.0491
-7.000 -0.4232 0.05205 0.04440 -0.0376 1.0000 0.0482
-6.750 -0.4058 0.04765 0.03965 -0.0388 1.0000 0.0475
-6.500 -0.3866 0.04352 0.03510 -0.0395 1.0000 0.0472
-6.250 -0.3657 0.03999 0.03111 -0.0398 1.0000 0.0482
-6.000 -0.3433 0.03682 0.02741 -0.0398 1.0000 0.0504
-5.750 -0.3195 0.03394 0.02393 -0.0395 1.0000 0.0521
-5.500 -0.2950 0.03138 0.02079 -0.0389 1.0000 0.0529
-5.250 -0.2711 0.02899 0.01813 -0.0382 1.0000 0.0544
-5.000 -0.2474 0.02729 0.01629 -0.0376 1.0000 0.0582
-4.750 -0.2225 0.02581 0.01453 -0.0367 1.0000 0.0637
-4.500 -0.1974 0.02426 0.01274 -0.0357 1.0000 0.0675
-4.250 -0.1730 0.02302 0.01143 -0.0349 1.0000 0.0742
-4.000 -0.1482 0.02196 0.01027 -0.0341 1.0000 0.0847
-3.750 -0.1230 0.02096 0.00919 -0.0334 1.0000 0.0982
-3.500 -0.0978 0.01997 0.00828 -0.0329 1.0000 0.1263
-3.250 -0.0723 0.01852 0.00748 -0.0329 1.0000 0.2273
-3.000 -0.0566 0.01627 0.00722 -0.0304 1.0000 0.6315
-2.750 -0.0217 0.01554 0.00681 -0.0302 1.0000 1.0000
-2.500 0.0007 0.01563 0.00655 -0.0295 1.0000 1.0000
-2.250 0.0231 0.01575 0.00638 -0.0288 1.0000 1.0000
-2.000 0.0453 0.01591 0.00631 -0.0282 1.0000 1.0000
-1.750 0.0672 0.01612 0.00632 -0.0276 1.0000 1.0000
-1.500 0.0920 0.01637 0.00641 -0.0278 0.9979 1.0000
-1.250 0.1410 0.01660 0.00642 -0.0325 0.9799 1.0000
-1.000 0.1886 0.01677 0.00645 -0.0368 0.9601 1.0000
-0.750 0.2363 0.01689 0.00645 -0.0409 0.9402 1.0000
-0.500 0.2782 0.01694 0.00644 -0.0436 0.9158 1.0000
-0.250 0.3163 0.01697 0.00642 -0.0454 0.8885 1.0000
0.000 0.3554 0.01696 0.00637 -0.0472 0.8625 1.0000
0.250 0.3927 0.01698 0.00632 -0.0484 0.8359 1.0000
0.500 0.4265 0.01705 0.00632 -0.0489 0.8079 1.0000
0.750 0.4570 0.01719 0.00640 -0.0488 0.7792 1.0000
1.000 0.4852 0.01738 0.00651 -0.0482 0.7506 1.0000
1.250 0.5119 0.01762 0.00668 -0.0475 0.7225 1.0000
1.500 0.5379 0.01789 0.00688 -0.0466 0.6949 1.0000
1.750 0.5633 0.01817 0.00715 -0.0458 0.6674 1.0000
2.000 0.5885 0.01847 0.00739 -0.0449 0.6412 1.0000
2.250 0.6138 0.01881 0.00766 -0.0440 0.6165 1.0000
2.500 0.6391 0.01920 0.00798 -0.0431 0.5929 1.0000
2.750 0.6642 0.01964 0.00844 -0.0423 0.5689 1.0000
3.000 0.6896 0.02012 0.00893 -0.0417 0.5445 1.0000
3.250 0.7149 0.02061 0.00942 -0.0410 0.5209 1.0000
3.500 0.7398 0.02110 0.00997 -0.0404 0.4960 1.0000
3.750 0.7642 0.02159 0.01058 -0.0397 0.4704 1.0000
4.000 0.7882 0.02205 0.01113 -0.0389 0.4439 1.0000
4.250 0.8117 0.02251 0.01165 -0.0380 0.4166 1.0000
4.500 0.8346 0.02299 0.01218 -0.0371 0.3875 1.0000
4.750 0.8569 0.02353 0.01278 -0.0361 0.3564 1.0000
5.000 0.8784 0.02414 0.01338 -0.0351 0.3236 1.0000
5.250 0.8993 0.02487 0.01411 -0.0342 0.2885 1.0000
5.500 0.9193 0.02572 0.01493 -0.0332 0.2520 1.0000
5.750 0.9387 0.02675 0.01593 -0.0322 0.2146 1.0000
6.000 0.9568 0.02800 0.01711 -0.0313 0.1811 1.0000
6.500 0.9920 0.03105 0.02009 -0.0292 0.1295 1.0000
6.750 1.0086 0.03276 0.02176 -0.0281 0.1136 1.0000
7.000 1.0255 0.03452 0.02360 -0.0270 0.1009 1.0000
7.250 1.0423 0.03633 0.02561 -0.0259 0.0900 1.0000
7.500 1.0597 0.03840 0.02782 -0.0247 0.0832 1.0000
7.750 1.0761 0.04041 0.03000 -0.0236 0.0763 1.0000
8.000 1.0915 0.04270 0.03252 -0.0225 0.0703 1.0000
8.250 1.1067 0.04525 0.03540 -0.0214 0.0661 1.0000
8.500 1.1210 0.04772 0.03796 -0.0204 0.0626 1.0000
8.750 1.1293 0.05090 0.04160 -0.0191 0.0594 1.0000
9.000 1.1330 0.05416 0.04533 -0.0176 0.0563 1.0000
9.250 1.1345 0.05753 0.04905 -0.0162 0.0543 1.0000
9.500 1.1325 0.06113 0.05295 -0.0149 0.0530 1.0000
9.750 1.1253 0.06473 0.05681 -0.0134 0.0522 1.0000
10.000 1.1147 0.06854 0.06082 -0.0124 0.0515 1.0000
10.250 1.1013 0.07284 0.06533 -0.0123 0.0510 1.0000
10.500 1.0786 0.07861 0.07135 -0.0142 0.0511 1.0000
10.750 1.0358 0.08883 0.08190 -0.0211 0.0527 1.0000
11.000 0.9844 0.10403 0.09723 -0.0325 0.0550 1.0000
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Polar data table (+)
Polar graphs
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