NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S801 Airfoil (s801-nr) Reynolds number: 1,000,000 Max Cl/Cd: 133.2 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s801-nr-1000000-n5.txt Download as CSV file: xf-s801-nr-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S801 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7810 0.05334 0.05090 -0.0959 0.9962 0.0076
-14.250 -0.8072 0.04249 0.03974 -0.1075 0.9942 0.0076
-14.000 -0.8107 0.03821 0.03531 -0.1112 0.9917 0.0076
-13.750 -0.8118 0.03440 0.03133 -0.1145 0.9885 0.0077
-13.500 -0.8014 0.03186 0.02865 -0.1172 0.9857 0.0078
-13.250 -0.7981 0.02938 0.02602 -0.1184 0.9811 0.0079
-12.750 -0.7887 0.02631 0.02273 -0.1170 0.9594 0.0081
-12.500 -0.7709 0.02466 0.02093 -0.1187 0.9462 0.0083
-12.250 -0.7331 0.02280 0.01888 -0.1241 0.9369 0.0084
-12.000 -0.6837 0.02123 0.01711 -0.1312 0.9289 0.0086
-11.750 -0.6396 0.01973 0.01538 -0.1371 0.9101 0.0088
-11.500 -0.6148 0.01886 0.01430 -0.1383 0.8827 0.0091
-11.250 -0.5969 0.01834 0.01362 -0.1374 0.8601 0.0092
-10.750 -0.5604 0.01742 0.01245 -0.1355 0.8286 0.0095
-10.500 -0.5405 0.01699 0.01192 -0.1347 0.8166 0.0097
-10.250 -0.5197 0.01658 0.01141 -0.1340 0.8061 0.0099
-10.000 -0.4982 0.01621 0.01095 -0.1334 0.7963 0.0102
-9.750 -0.4763 0.01576 0.01041 -0.1329 0.7878 0.0104
-9.500 -0.4539 0.01540 0.00994 -0.1323 0.7796 0.0107
-9.250 -0.4309 0.01495 0.00940 -0.1319 0.7720 0.0110
-8.750 -0.3841 0.01412 0.00838 -0.1312 0.7584 0.0113
-8.500 -0.3596 0.01379 0.00797 -0.1309 0.7522 0.0115
-8.250 -0.3367 0.01318 0.00728 -0.1306 0.7470 0.0118
-8.000 -0.3122 0.01272 0.00677 -0.1304 0.7419 0.0121
-7.750 -0.2869 0.01238 0.00638 -0.1303 0.7369 0.0124
-7.500 -0.2612 0.01213 0.00608 -0.1302 0.7325 0.0128
-7.250 -0.2348 0.01184 0.00575 -0.1302 0.7285 0.0132
-7.000 -0.2086 0.01156 0.00543 -0.1302 0.7242 0.0136
-6.750 -0.1824 0.01127 0.00508 -0.1302 0.7201 0.0139
-6.500 -0.1559 0.01101 0.00476 -0.1302 0.7164 0.0143
-6.250 -0.1288 0.01075 0.00446 -0.1303 0.7127 0.0146
-6.000 -0.1017 0.01052 0.00419 -0.1304 0.7089 0.0148
-5.750 -0.0747 0.01027 0.00389 -0.1304 0.7054 0.0152
-5.250 -0.0200 0.00976 0.00333 -0.1307 0.6997 0.0166
-5.000 0.0080 0.00957 0.00312 -0.1309 0.6969 0.0173
-4.750 0.0359 0.00940 0.00292 -0.1311 0.6941 0.0178
-4.500 0.0639 0.00925 0.00274 -0.1313 0.6913 0.0185
-4.250 0.0919 0.00912 0.00258 -0.1315 0.6887 0.0190
-4.000 0.1199 0.00897 0.00241 -0.1317 0.6861 0.0204
-3.750 0.1485 0.00882 0.00226 -0.1320 0.6839 0.0222
-3.500 0.1770 0.00868 0.00213 -0.1323 0.6814 0.0262
-3.250 0.2054 0.00847 0.00200 -0.1326 0.6789 0.0441
-3.000 0.2339 0.00829 0.00190 -0.1330 0.6767 0.0654
-2.750 0.2624 0.00811 0.00180 -0.1334 0.6745 0.0929
-2.500 0.2910 0.00792 0.00172 -0.1338 0.6725 0.1280
-2.250 0.3198 0.00771 0.00164 -0.1343 0.6705 0.1761
-2.000 0.3491 0.00749 0.00158 -0.1349 0.6688 0.2247
-1.750 0.3785 0.00722 0.00153 -0.1356 0.6668 0.2944
-1.500 0.4080 0.00696 0.00148 -0.1363 0.6647 0.3662
-1.250 0.4379 0.00661 0.00142 -0.1372 0.6626 0.4702
-1.000 0.4681 0.00618 0.00143 -0.1382 0.6608 0.6137
-0.750 0.4969 0.00617 0.00149 -0.1384 0.6589 0.6520
-0.500 0.5256 0.00621 0.00154 -0.1386 0.6569 0.6715
-0.250 0.5543 0.00626 0.00159 -0.1389 0.6549 0.6836
0.000 0.5833 0.00629 0.00161 -0.1391 0.6529 0.6912
0.250 0.6120 0.00632 0.00166 -0.1393 0.6501 0.6978
0.500 0.6405 0.00637 0.00169 -0.1395 0.6466 0.7046
0.750 0.6686 0.00643 0.00174 -0.1396 0.6430 0.7093
1.000 0.6966 0.00649 0.00179 -0.1397 0.6390 0.7141
1.250 0.7250 0.00653 0.00183 -0.1398 0.6341 0.7190
1.500 0.7528 0.00659 0.00188 -0.1399 0.6288 0.7233
1.750 0.7802 0.00665 0.00194 -0.1398 0.6234 0.7273
2.000 0.8081 0.00670 0.00200 -0.1398 0.6169 0.7311
2.250 0.8352 0.00678 0.00205 -0.1397 0.6100 0.7342
2.500 0.8630 0.00683 0.00211 -0.1398 0.6020 0.7364
2.750 0.8898 0.00692 0.00216 -0.1396 0.5922 0.7378
3.000 0.9164 0.00699 0.00222 -0.1395 0.5805 0.7393
3.250 0.9425 0.00709 0.00230 -0.1392 0.5662 0.7407
3.500 0.9670 0.00726 0.00239 -0.1386 0.5425 0.7420
3.750 0.9867 0.00767 0.00259 -0.1371 0.4948 0.7435
4.000 1.0040 0.00827 0.00292 -0.1352 0.4402 0.7450
4.250 1.0225 0.00881 0.00325 -0.1336 0.3944 0.7464
4.500 1.0406 0.00935 0.00358 -0.1319 0.3500 0.7477
4.750 1.0584 0.00989 0.00392 -0.1302 0.3084 0.7492
5.000 1.0763 0.01040 0.00425 -0.1285 0.2716 0.7507
5.250 1.0945 0.01087 0.00458 -0.1269 0.2408 0.7521
5.500 1.1120 0.01134 0.00491 -0.1251 0.2119 0.7533
5.750 1.1290 0.01175 0.00522 -0.1232 0.1888 0.7547
6.000 1.1450 0.01214 0.00553 -0.1211 0.1697 0.7560
6.250 1.1604 0.01257 0.00588 -0.1189 0.1497 0.7575
6.500 1.1758 0.01302 0.00626 -0.1168 0.1319 0.7589
6.750 1.1919 0.01346 0.00664 -0.1148 0.1177 0.7606
7.000 1.2089 0.01386 0.00700 -0.1130 0.1071 0.7624
7.250 1.2258 0.01428 0.00739 -0.1112 0.0974 0.7641
7.500 1.2416 0.01474 0.00782 -0.1093 0.0878 0.7657
7.750 1.2579 0.01519 0.00825 -0.1076 0.0796 0.7672
8.000 1.2743 0.01565 0.00869 -0.1058 0.0730 0.7686
8.250 1.2898 0.01615 0.00918 -0.1040 0.0670 0.7701
8.500 1.3058 0.01663 0.00967 -0.1023 0.0620 0.7718
8.750 1.3208 0.01718 0.01022 -0.1005 0.0569 0.7735
9.000 1.3358 0.01774 0.01079 -0.0987 0.0526 0.7754
9.250 1.3513 0.01830 0.01137 -0.0971 0.0493 0.7773
9.500 1.3652 0.01896 0.01204 -0.0953 0.0458 0.7793
9.750 1.3799 0.01959 0.01270 -0.0937 0.0430 0.7814
10.000 1.3944 0.02027 0.01339 -0.0921 0.0403 0.7835
10.250 1.4076 0.02104 0.01418 -0.0905 0.0376 0.7856
10.500 1.4212 0.02180 0.01498 -0.0889 0.0356 0.7879
10.750 1.4353 0.02256 0.01579 -0.0875 0.0338 0.7902
11.000 1.4479 0.02344 0.01669 -0.0859 0.0312 0.7927
11.250 1.4598 0.02440 0.01767 -0.0844 0.0289 0.7953
11.500 1.4733 0.02528 0.01859 -0.0831 0.0275 0.7978
12.000 1.4973 0.02731 0.02068 -0.0803 0.0241 0.8032
12.250 1.5091 0.02837 0.02181 -0.0790 0.0228 0.8063
12.500 1.5215 0.02941 0.02290 -0.0779 0.0219 0.8097
12.750 1.5333 0.03053 0.02407 -0.0767 0.0210 0.8131
13.000 1.5441 0.03175 0.02533 -0.0755 0.0199 0.8165
13.250 1.5543 0.03305 0.02667 -0.0743 0.0187 0.8206
13.500 1.5649 0.03432 0.02802 -0.0732 0.0179 0.8253
14.000 1.5855 0.03701 0.03084 -0.0712 0.0161 0.8358
14.250 1.5943 0.03854 0.03242 -0.0702 0.0151 0.8421
14.500 1.6031 0.04009 0.03404 -0.0693 0.0143 0.8487
14.750 1.6122 0.04163 0.03566 -0.0684 0.0136 0.8568
15.000 1.6204 0.04327 0.03739 -0.0676 0.0127 0.8669
15.250 1.6276 0.04501 0.03921 -0.0667 0.0119 0.8812
15.500 1.6318 0.04669 0.04109 -0.0653 0.0112 0.9509
15.750 1.6388 0.04855 0.04302 -0.0647 0.0105 1.0000
16.000 1.6450 0.05061 0.04513 -0.0641 0.0097 1.0000
16.250 1.6495 0.05288 0.04745 -0.0636 0.0089 1.0000
16.500 1.6550 0.05512 0.04975 -0.0632 0.0083 1.0000
16.750 1.6591 0.05755 0.05226 -0.0628 0.0076 1.0000
17.000 1.6626 0.06011 0.05488 -0.0626 0.0071 1.0000
17.250 1.6646 0.06290 0.05774 -0.0624 0.0065 1.0000
17.500 1.6668 0.06573 0.06064 -0.0623 0.0060 1.0000
17.750 1.6681 0.06874 0.06374 -0.0624 0.0056 1.0000
18.000 1.6683 0.07197 0.06706 -0.0626 0.0052 1.0000
18.250 1.6666 0.07554 0.07071 -0.0630 0.0048 1.0000
18.500 1.6656 0.07909 0.07435 -0.0635 0.0046 1.0000
18.750 1.6638 0.08283 0.07820 -0.0642 0.0044 1.0000
19.000 1.6611 0.08680 0.08227 -0.0650 0.0042 1.0000
19.250 1.6571 0.09106 0.08663 -0.0661 0.0040 1.0000
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