NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S826 Airfoil (s826-nr) Reynolds number: 100,000 Max Cl/Cd: 60.01 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s826-nr-100000-n5.txt Download as CSV file: xf-s826-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S826 Airfoil
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3565 0.12094 0.11593 -0.0443 1.0000 0.0242
-10.500 -0.3543 0.11810 0.11313 -0.0437 1.0000 0.0232
-10.250 -0.3553 0.11470 0.10978 -0.0439 1.0000 0.0224
-9.750 -0.3753 0.10228 0.09750 -0.0480 1.0000 0.0188
-9.500 -0.3773 0.09946 0.09474 -0.0477 1.0000 0.0186
-9.250 -0.3821 0.09612 0.09147 -0.0476 1.0000 0.0184
-9.000 -0.3882 0.09271 0.08812 -0.0477 1.0000 0.0181
-8.750 -0.3973 0.08883 0.08431 -0.0480 1.0000 0.0179
-8.500 -0.4099 0.08469 0.08024 -0.0485 1.0000 0.0176
-8.250 -0.4095 0.07757 0.07309 -0.0562 0.9947 0.0172
-8.000 -0.4133 0.07075 0.06620 -0.0644 0.9864 0.0168
-7.750 -0.4183 0.06396 0.05926 -0.0736 0.9753 0.0166
-7.500 -0.4104 0.05652 0.05150 -0.0849 0.9638 0.0162
-7.250 -0.3945 0.05026 0.04481 -0.0927 0.9550 0.0159
-7.000 -0.3723 0.04490 0.03895 -0.0985 0.9470 0.0158
-6.750 -0.3487 0.04048 0.03404 -0.1020 0.9389 0.0157
-6.500 -0.3164 0.03658 0.02963 -0.1059 0.9336 0.0159
-6.250 -0.2888 0.03387 0.02651 -0.1077 0.9258 0.0170
-6.000 -0.2541 0.03116 0.02325 -0.1099 0.9208 0.0191
-5.750 -0.2263 0.02943 0.02140 -0.1110 0.9132 0.0205
-5.500 -0.1940 0.02765 0.01945 -0.1121 0.9077 0.0218
-5.250 -0.1661 0.02613 0.01776 -0.1120 0.9003 0.0235
-5.000 -0.1351 0.02480 0.01643 -0.1127 0.8943 0.0268
-4.750 -0.1052 0.02390 0.01545 -0.1131 0.8870 0.0322
-4.500 -0.0715 0.02285 0.01445 -0.1147 0.8807 0.0401
-4.250 -0.0332 0.02172 0.01322 -0.1176 0.8746 0.0532
-4.000 0.0092 0.02028 0.01176 -0.1222 0.8679 0.0811
-3.750 0.0647 0.01785 0.01054 -0.1310 0.8648 0.3893
-3.500 0.0961 0.01836 0.01089 -0.1311 0.8554 0.4476
-3.250 0.1315 0.01880 0.01117 -0.1316 0.8494 0.4754
-3.000 0.1606 0.01911 0.01135 -0.1312 0.8394 0.4908
-2.750 0.1971 0.01926 0.01135 -0.1322 0.8330 0.5049
-2.500 0.2279 0.01934 0.01136 -0.1322 0.8233 0.5121
-2.250 0.2689 0.01900 0.01075 -0.1352 0.8159 0.5171
-2.000 0.3079 0.01866 0.01021 -0.1377 0.8077 0.5195
-1.750 0.3436 0.01845 0.00986 -0.1393 0.7989 0.5213
-1.500 0.3821 0.01823 0.00949 -0.1415 0.7910 0.5237
-1.250 0.4156 0.01810 0.00924 -0.1428 0.7809 0.5266
-1.000 0.4531 0.01793 0.00891 -0.1449 0.7725 0.5301
-0.750 0.4888 0.01778 0.00859 -0.1469 0.7633 0.5337
-0.500 0.5210 0.01774 0.00849 -0.1479 0.7547 0.5358
-0.250 0.5546 0.01770 0.00838 -0.1491 0.7469 0.5385
0.000 0.5849 0.01772 0.00836 -0.1498 0.7381 0.5418
0.250 0.6192 0.01770 0.00823 -0.1513 0.7310 0.5458
0.500 0.6488 0.01774 0.00822 -0.1519 0.7224 0.5494
0.750 0.6804 0.01778 0.00824 -0.1527 0.7162 0.5520
1.000 0.7079 0.01789 0.00836 -0.1529 0.7087 0.5551
1.250 0.7389 0.01796 0.00840 -0.1537 0.7024 0.5592
1.500 0.7682 0.01808 0.00851 -0.1543 0.6955 0.5639
1.750 0.7966 0.01820 0.00867 -0.1545 0.6893 0.5669
2.000 0.8261 0.01833 0.00882 -0.1550 0.6840 0.5705
2.250 0.8532 0.01850 0.00904 -0.1552 0.6776 0.5746
2.500 0.8839 0.01864 0.00920 -0.1559 0.6724 0.5793
2.750 0.9101 0.01883 0.00950 -0.1558 0.6667 0.5829
3.000 0.9373 0.01903 0.00978 -0.1559 0.6610 0.5876
3.250 0.9683 0.01920 0.00997 -0.1567 0.6562 0.5931
3.500 0.9922 0.01944 0.01038 -0.1561 0.6496 0.5970
3.750 1.0200 0.01963 0.01064 -0.1563 0.6437 0.6017
4.000 1.0470 0.01986 0.01096 -0.1563 0.6373 0.6072
4.250 1.0726 0.02006 0.01132 -0.1560 0.6301 0.6120
4.500 1.0988 0.02025 0.01162 -0.1557 0.6225 0.6177
4.750 1.1250 0.02042 0.01186 -0.1554 0.6133 0.6242
5.000 1.1476 0.02060 0.01221 -0.1544 0.6029 0.6296
5.250 1.1727 0.02074 0.01244 -0.1538 0.5924 0.6364
5.500 1.1978 0.02085 0.01265 -0.1532 0.5817 0.6424
5.750 1.2189 0.02105 0.01302 -0.1519 0.5698 0.6494
6.000 1.2404 0.02122 0.01337 -0.1507 0.5573 0.6567
6.250 1.2616 0.02139 0.01370 -0.1494 0.5440 0.6648
6.500 1.2819 0.02157 0.01404 -0.1479 0.5297 0.6729
6.750 1.3011 0.02177 0.01439 -0.1462 0.5135 0.6823
7.000 1.3184 0.02197 0.01476 -0.1441 0.4949 0.6912
7.250 1.3335 0.02223 0.01518 -0.1417 0.4727 0.7015
7.500 1.3461 0.02256 0.01564 -0.1389 0.4439 0.7131
7.750 1.3554 0.02298 0.01608 -0.1355 0.4028 0.7253
8.000 1.3574 0.02369 0.01659 -0.1310 0.3526 0.7386
8.250 1.3556 0.02487 0.01752 -0.1262 0.3056 0.7539
8.500 1.3536 0.02625 0.01875 -0.1218 0.2651 0.7728
8.750 1.3512 0.02769 0.02014 -0.1175 0.2315 0.7980
9.000 1.3478 0.02906 0.02151 -0.1132 0.2035 0.8414
9.250 1.3433 0.03039 0.02286 -0.1089 0.1809 1.0000
9.500 1.3446 0.03228 0.02464 -0.1062 0.1590 1.0000
9.750 1.3472 0.03416 0.02648 -0.1039 0.1393 1.0000
10.000 1.3495 0.03615 0.02844 -0.1017 0.1230 1.0000
10.250 1.3518 0.03824 0.03052 -0.0998 0.1089 1.0000
10.500 1.3542 0.04042 0.03271 -0.0980 0.0965 1.0000
10.750 1.3564 0.04272 0.03503 -0.0964 0.0861 1.0000
11.000 1.3576 0.04520 0.03750 -0.0950 0.0770 1.0000
11.250 1.3604 0.04763 0.04004 -0.0938 0.0684 1.0000
11.500 1.3627 0.05018 0.04267 -0.0927 0.0607 1.0000
11.750 1.3617 0.05315 0.04563 -0.0917 0.0546 1.0000
12.000 1.3656 0.05572 0.04835 -0.0909 0.0477 1.0000
12.250 1.3641 0.05894 0.05159 -0.0903 0.0430 1.0000
12.500 1.3665 0.06183 0.05465 -0.0897 0.0377 1.0000
12.750 1.3630 0.06549 0.05832 -0.0894 0.0343 1.0000
13.000 1.3654 0.06858 0.06162 -0.0891 0.0303 1.0000
13.250 1.3640 0.07217 0.06531 -0.0891 0.0275 1.0000
13.500 1.3610 0.07609 0.06932 -0.0890 0.0254 1.0000
13.750 1.3611 0.07970 0.07315 -0.0890 0.0230 1.0000
14.000 1.3592 0.08361 0.07718 -0.0895 0.0212 1.0000
14.250 1.3544 0.08799 0.08167 -0.0903 0.0198 1.0000
14.500 1.3537 0.09200 0.08592 -0.0908 0.0182 1.0000
14.750 1.3516 0.09625 0.09038 -0.0915 0.0171 1.0000
15.000 1.3487 0.10067 0.09497 -0.0925 0.0163 1.0000
15.250 1.3444 0.10536 0.09979 -0.0940 0.0155 1.0000
15.500 1.3391 0.11025 0.10475 -0.0958 0.0148 1.0000
15.750 1.3339 0.11543 0.11018 -0.0976 0.0141 1.0000
16.000 1.3274 0.12103 0.11606 -0.1000 0.0135 1.0000
16.250 1.3198 0.12696 0.12223 -0.1029 0.0129 1.0000
16.500 1.3117 0.13313 0.12861 -0.1062 0.0124 1.0000
16.750 1.3030 0.13963 0.13531 -0.1100 0.0121 1.0000
17.000 1.2938 0.14650 0.14238 -0.1142 0.0119 1.0000
17.250 1.2833 0.15398 0.15005 -0.1190 0.0118 1.0000
17.500 1.2715 0.16221 0.15847 -0.1245 0.0117 1.0000
17.750 1.2552 0.17237 0.16887 -0.1314 0.0119 1.0000
18.000 1.2323 0.18566 0.18238 -0.1405 0.0124 1.0000
18.250 1.2032 0.20304 0.19990 -0.1517 0.0136 1.0000
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