NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S830 Airfoil (s830-nr) Reynolds number: 200,000 Max Cl/Cd: 61.14 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s830-nr-200000.txt Download as CSV file: xf-s830-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S830 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2659 0.11006 0.10666 -0.1009 0.9652 0.0424
-11.500 -0.2863 0.10283 0.09933 -0.1087 0.9617 0.0426
-11.250 -0.3046 0.09770 0.09410 -0.1126 0.9552 0.0426
-11.000 -0.3141 0.09291 0.08922 -0.1165 0.9499 0.0426
-10.750 -0.2655 0.08771 0.08422 -0.1158 0.9500 0.0448
-10.500 -0.2642 0.08261 0.07905 -0.1206 0.9475 0.0456
-10.250 -0.2793 0.07841 0.07479 -0.1220 0.9384 0.0459
-10.000 -0.2843 0.07356 0.06982 -0.1262 0.9345 0.0468
-9.750 -0.3002 0.07022 0.06639 -0.1265 0.9247 0.0472
-9.500 -0.3050 0.06620 0.06221 -0.1298 0.9202 0.0483
-9.250 -0.3237 0.06396 0.05986 -0.1279 0.9087 0.0487
-9.000 -0.3375 0.06149 0.05723 -0.1271 0.8981 0.0498
-8.750 -0.3434 0.06175 0.05678 -0.1295 0.8918 0.0529
-8.250 -0.3294 0.05140 0.04638 -0.1292 0.8796 0.0557
-8.000 -0.3024 0.04805 0.04293 -0.1318 0.8781 0.0583
-7.750 -0.2997 0.04653 0.04124 -0.1293 0.8681 0.0610
-7.500 -0.2789 0.04352 0.03775 -0.1314 0.8651 0.0677
-7.250 -0.2446 0.04011 0.03433 -0.1343 0.8639 0.0713
-7.000 -0.1933 0.03391 0.02715 -0.1323 0.8635 0.0332
-6.750 -0.1459 0.03055 0.02332 -0.1323 0.8632 0.0275
-6.500 -0.0932 0.02894 0.02166 -0.1316 0.8635 0.0273
-6.250 -0.0184 0.02849 0.02125 -0.1335 0.8652 0.0293
-6.000 0.0300 0.02799 0.02074 -0.1359 0.8637 0.0328
-5.500 0.0691 0.02690 0.01971 -0.1336 0.8501 0.0443
-5.250 0.0805 0.02623 0.01905 -0.1320 0.8422 0.0533
-5.000 0.0793 0.02518 0.01803 -0.1291 0.8337 0.0616
-4.750 0.0710 0.02426 0.01710 -0.1250 0.8231 0.0681
-4.500 0.3060 0.04136 0.03585 -0.1330 0.8341 0.5957
-4.250 0.3794 0.03972 0.03398 -0.1397 0.8319 0.6023
-4.000 0.3902 0.03980 0.03399 -0.1375 0.8213 0.6093
-3.750 0.3706 0.04012 0.03425 -0.1321 0.8104 0.6134
-3.500 0.4064 0.03903 0.03303 -0.1342 0.8038 0.6141
-3.250 0.4292 0.03833 0.03222 -0.1343 0.7965 0.6146
-3.000 0.4504 0.03769 0.03149 -0.1341 0.7888 0.6151
-2.750 0.4741 0.03705 0.03075 -0.1344 0.7823 0.6157
-2.500 0.4908 0.03658 0.03022 -0.1333 0.7743 0.6166
-2.250 0.5168 0.03596 0.02949 -0.1341 0.7684 0.6174
-2.000 0.4638 0.03752 0.03111 -0.1222 0.7575 0.6279
-1.750 0.4783 0.03680 0.03030 -0.1215 0.7513 0.6288
-1.500 0.4948 0.03610 0.02958 -0.1199 0.7440 0.6292
-1.250 0.5252 0.03531 0.02867 -0.1213 0.7390 0.6296
-1.000 0.5387 0.03482 0.02819 -0.1192 0.7322 0.6303
-0.750 0.5609 0.03426 0.02757 -0.1189 0.7263 0.6310
-0.500 0.5901 0.03368 0.02690 -0.1202 0.7218 0.6318
-0.250 0.5953 0.03346 0.02672 -0.1165 0.7146 0.6332
0.000 0.6171 0.03303 0.02623 -0.1165 0.7094 0.6347
0.250 0.6327 0.03274 0.02591 -0.1153 0.7041 0.6369
0.500 0.6088 0.02886 0.02191 -0.1203 0.6962 0.5942
0.750 0.6407 0.02827 0.02123 -0.1223 0.6921 0.5928
1.000 0.6566 0.02767 0.02064 -0.1220 0.6864 0.5910
1.250 0.6806 0.02696 0.01990 -0.1235 0.6811 0.5900
1.500 0.7165 0.02628 0.01914 -0.1272 0.6772 0.5899
1.750 0.7453 0.02575 0.01858 -0.1294 0.6727 0.5906
2.000 0.7695 0.02524 0.01807 -0.1309 0.6673 0.5923
2.250 0.8072 0.02459 0.01735 -0.1350 0.6630 0.5935
2.500 0.8660 0.02343 0.01597 -0.1451 0.6596 0.5966
2.750 0.8778 0.02346 0.01612 -0.1425 0.6542 0.5973
3.000 0.9001 0.02347 0.01617 -0.1420 0.6499 0.5981
3.250 0.9300 0.02345 0.01617 -0.1429 0.6465 0.5990
3.500 0.9655 0.02347 0.01616 -0.1449 0.6438 0.6002
3.750 0.9777 0.02362 0.01644 -0.1427 0.6389 0.6014
4.000 1.0009 0.02367 0.01657 -0.1426 0.6347 0.6031
4.250 1.0329 0.02365 0.01655 -0.1442 0.6313 0.6053
4.500 1.0737 0.02355 0.01641 -0.1479 0.6287 0.6079
4.750 1.1005 0.02353 0.01645 -0.1495 0.6247 0.6109
5.000 1.1255 0.02359 0.01657 -0.1503 0.6208 0.6131
5.250 1.1495 0.02373 0.01680 -0.1501 0.6175 0.6142
5.500 1.1798 0.02384 0.01697 -0.1510 0.6147 0.6155
5.750 1.2163 0.02399 0.01715 -0.1532 0.6123 0.6170
6.000 1.2229 0.02445 0.01781 -0.1500 0.6082 0.6187
6.250 1.2425 0.02476 0.01824 -0.1494 0.6044 0.6207
6.500 1.2725 0.02490 0.01844 -0.1506 0.6012 0.6235
6.750 1.3128 0.02495 0.01850 -0.1541 0.5986 0.6273
7.000 1.3432 0.02514 0.01878 -0.1554 0.5955 0.6295
7.250 1.3451 0.02567 0.01951 -0.1512 0.5903 0.6307
7.500 1.3686 0.02581 0.01977 -0.1508 0.5861 0.6324
7.750 1.4186 0.02534 0.01927 -0.1551 0.5811 0.6346
8.000 1.4128 0.02559 0.01971 -0.1493 0.5726 0.6364
8.250 1.4468 0.02484 0.01891 -0.1504 0.5625 0.6392
8.500 1.4588 0.02467 0.01880 -0.1479 0.5538 0.6418
8.750 1.4800 0.02451 0.01867 -0.1471 0.5460 0.6445
9.000 1.4871 0.02451 0.01879 -0.1435 0.5382 0.6462
9.250 1.5009 0.02455 0.01893 -0.1411 0.5304 0.6482
9.500 1.5090 0.02473 0.01923 -0.1379 0.5223 0.6504
9.750 1.5191 0.02495 0.01954 -0.1353 0.5141 0.6528
10.000 1.5308 0.02505 0.01970 -0.1329 0.5044 0.6553
10.250 1.5297 0.02567 0.02045 -0.1287 0.4948 0.6576
10.500 1.5373 0.02605 0.02088 -0.1260 0.4837 0.6598
10.750 1.5420 0.02648 0.02138 -0.1227 0.4716 0.6615
11.000 1.5343 0.02756 0.02262 -0.1180 0.4590 0.6630
11.250 1.5301 0.02866 0.02383 -0.1140 0.4440 0.6648
11.500 1.5247 0.03001 0.02524 -0.1102 0.4264 0.6668
11.750 1.5146 0.03187 0.02718 -0.1062 0.4036 0.6688
12.000 1.5021 0.03414 0.02938 -0.1024 0.3700 0.6709
12.250 1.4813 0.03729 0.03229 -0.0983 0.3277 0.6726
12.500 1.4559 0.04128 0.03601 -0.0944 0.2906 0.6740
12.750 1.4320 0.04563 0.04015 -0.0914 0.2557 0.6753
13.000 1.4092 0.05014 0.04450 -0.0889 0.2237 0.6762
13.250 1.3882 0.05479 0.04901 -0.0869 0.1941 0.6771
13.500 1.3692 0.05953 0.05361 -0.0854 0.1664 0.6782
13.750 1.3523 0.06428 0.05822 -0.0844 0.1417 0.6792
14.000 1.3387 0.06883 0.06267 -0.0837 0.1194 0.6805
14.500 1.3187 0.07754 0.07122 -0.0830 0.0882 0.6833
15.000 1.3092 0.08537 0.07901 -0.0831 0.0678 0.6871
15.250 1.3080 0.08897 0.08264 -0.0833 0.0603 0.6892
15.500 1.3034 0.09298 0.08656 -0.0836 0.0545 0.6910
15.750 1.3069 0.09593 0.08966 -0.0838 0.0490 0.6928
16.000 1.3047 0.09947 0.09316 -0.0840 0.0446 0.6945
16.250 1.3093 0.10235 0.09619 -0.0844 0.0404 0.6966
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