NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S826 Airfoil (s826-nr) Reynolds number: 200,000 Max Cl/Cd: 81.38 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s826-nr-200000-n5.txt Download as CSV file: xf-s826-nr-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2412 0.10627 0.10293 -0.0549 0.9898 0.0129
-10.500 -0.3664 0.11419 0.11070 -0.0416 1.0000 0.0136
-10.250 -0.3637 0.11095 0.10749 -0.0424 0.9995 0.0132
-10.000 -0.3540 0.10611 0.10265 -0.0464 0.9974 0.0126
-9.500 -0.3537 0.08944 0.08602 -0.0583 0.9922 0.0102
-9.250 -0.3495 0.08332 0.07991 -0.0636 0.9888 0.0101
-9.000 -0.3471 0.07588 0.07246 -0.0709 0.9854 0.0099
-8.750 -0.3528 0.06830 0.06483 -0.0785 0.9802 0.0096
-8.250 -0.3719 0.05585 0.05215 -0.0918 0.9628 0.0094
-8.000 -0.3705 0.04936 0.04541 -0.1005 0.9519 0.0091
-7.750 -0.3560 0.04245 0.03806 -0.1090 0.9453 0.0089
-7.500 -0.3464 0.03759 0.03280 -0.1115 0.9350 0.0087
-7.250 -0.3262 0.03277 0.02747 -0.1144 0.9279 0.0085
-7.000 -0.3004 0.02891 0.02311 -0.1167 0.9219 0.0085
-6.750 -0.2680 0.02595 0.01973 -0.1191 0.9188 0.0086
-6.500 -0.2466 0.02409 0.01762 -0.1186 0.9098 0.0088
-6.250 -0.2146 0.02231 0.01560 -0.1200 0.9060 0.0091
-6.000 -0.1903 0.02096 0.01408 -0.1198 0.8972 0.0096
-5.500 -0.1276 0.01849 0.01139 -0.1225 0.8843 0.0109
-5.250 -0.0908 0.01753 0.01035 -0.1250 0.8794 0.0128
-5.000 -0.0562 0.01671 0.00948 -0.1271 0.8722 0.0163
-4.750 -0.0158 0.01569 0.00837 -0.1305 0.8662 0.0220
-4.500 0.0250 0.01486 0.00748 -0.1338 0.8592 0.0328
-4.250 0.0691 0.01397 0.00657 -0.1379 0.8518 0.0536
-4.000 0.1154 0.01308 0.00578 -0.1426 0.8437 0.1079
-3.750 0.1700 0.01157 0.00509 -0.1502 0.8361 0.3866
-3.500 0.2109 0.01166 0.00503 -0.1527 0.8247 0.4276
-3.250 0.2505 0.01175 0.00497 -0.1549 0.8124 0.4453
-3.000 0.2875 0.01184 0.00490 -0.1567 0.7992 0.4566
-2.750 0.3214 0.01197 0.00491 -0.1577 0.7853 0.4656
-2.500 0.3546 0.01206 0.00478 -0.1588 0.7714 0.4738
-2.250 0.3849 0.01213 0.00476 -0.1592 0.7581 0.4778
-1.750 0.4442 0.01218 0.00453 -0.1601 0.7338 0.4827
-1.500 0.4733 0.01220 0.00442 -0.1604 0.7231 0.4853
-1.250 0.5027 0.01225 0.00431 -0.1608 0.7133 0.4883
-1.000 0.5307 0.01229 0.00430 -0.1609 0.7035 0.4903
-0.750 0.5586 0.01235 0.00430 -0.1610 0.6943 0.4924
-0.250 0.6148 0.01248 0.00430 -0.1613 0.6776 0.4973
0.000 0.6434 0.01257 0.00431 -0.1615 0.6708 0.5003
0.250 0.6715 0.01264 0.00433 -0.1617 0.6637 0.5036
0.500 0.6993 0.01273 0.00441 -0.1618 0.6573 0.5059
0.750 0.7269 0.01281 0.00450 -0.1619 0.6508 0.5085
1.000 0.7548 0.01291 0.00458 -0.1620 0.6447 0.5113
1.250 0.7829 0.01301 0.00466 -0.1622 0.6395 0.5144
1.500 0.8108 0.01311 0.00477 -0.1623 0.6339 0.5179
1.750 0.8386 0.01322 0.00490 -0.1624 0.6289 0.5208
2.000 0.8664 0.01334 0.00504 -0.1625 0.6241 0.5238
2.250 0.8938 0.01345 0.00523 -0.1626 0.6188 0.5273
2.500 0.9218 0.01358 0.00538 -0.1627 0.6144 0.5310
2.750 0.9499 0.01373 0.00553 -0.1629 0.6101 0.5345
3.000 0.9766 0.01384 0.00575 -0.1628 0.6045 0.5375
3.250 1.0037 0.01398 0.00595 -0.1627 0.5988 0.5411
3.500 1.0304 0.01412 0.00614 -0.1626 0.5925 0.5455
3.750 1.0563 0.01426 0.00633 -0.1623 0.5847 0.5498
4.000 1.0814 0.01438 0.00655 -0.1618 0.5758 0.5535
4.250 1.1066 0.01454 0.00672 -0.1613 0.5665 0.5578
4.500 1.1310 0.01466 0.00694 -0.1607 0.5565 0.5624
4.750 1.1558 0.01481 0.00718 -0.1602 0.5474 0.5664
5.000 1.1801 0.01497 0.00741 -0.1595 0.5375 0.5708
5.250 1.2039 0.01512 0.00767 -0.1588 0.5267 0.5759
5.500 1.2275 0.01529 0.00793 -0.1581 0.5158 0.5810
5.750 1.2504 0.01547 0.00823 -0.1571 0.5036 0.5862
6.000 1.2723 0.01568 0.00851 -0.1560 0.4888 0.5924
6.250 1.2931 0.01589 0.00882 -0.1547 0.4704 0.5978
6.500 1.3120 0.01615 0.00913 -0.1531 0.4457 0.6038
6.750 1.3278 0.01654 0.00947 -0.1509 0.4076 0.6098
7.000 1.3351 0.01728 0.00999 -0.1472 0.3528 0.6153
7.250 1.3386 0.01826 0.01073 -0.1430 0.3042 0.6217
7.500 1.3428 0.01936 0.01163 -0.1392 0.2600 0.6279
7.750 1.3492 0.02045 0.01258 -0.1359 0.2223 0.6354
8.000 1.3565 0.02154 0.01357 -0.1328 0.1911 0.6432
8.250 1.3644 0.02263 0.01460 -0.1299 0.1646 0.6522
8.500 1.3723 0.02373 0.01569 -0.1271 0.1429 0.6613
8.750 1.3804 0.02485 0.01680 -0.1245 0.1232 0.6716
9.250 1.3952 0.02726 0.01923 -0.1193 0.0927 0.6959
9.500 1.4024 0.02852 0.02055 -0.1168 0.0807 0.7111
9.750 1.4093 0.02984 0.02195 -0.1145 0.0701 0.7293
10.000 1.4154 0.03123 0.02343 -0.1121 0.0608 0.7523
10.250 1.4201 0.03273 0.02502 -0.1098 0.0528 0.7840
10.500 1.4229 0.03408 0.02657 -0.1070 0.0459 0.8491
10.750 1.4243 0.03556 0.02817 -0.1043 0.0406 1.0000
11.000 1.4288 0.03753 0.03016 -0.1027 0.0350 1.0000
11.250 1.4350 0.03941 0.03214 -0.1013 0.0303 1.0000
11.500 1.4376 0.04173 0.03447 -0.0999 0.0261 1.0000
11.750 1.4428 0.04385 0.03670 -0.0987 0.0223 1.0000
12.000 1.4446 0.04641 0.03930 -0.0976 0.0191 1.0000
12.250 1.4480 0.04888 0.04188 -0.0966 0.0163 1.0000
12.500 1.4484 0.05177 0.04484 -0.0958 0.0143 1.0000
12.750 1.4511 0.05447 0.04767 -0.0951 0.0123 1.0000
13.000 1.4509 0.05760 0.05089 -0.0946 0.0109 1.0000
13.250 1.4519 0.06070 0.05413 -0.0942 0.0097 1.0000
13.500 1.4523 0.06393 0.05750 -0.0939 0.0087 1.0000
13.750 1.4509 0.06748 0.06116 -0.0939 0.0079 1.0000
14.000 1.4495 0.07115 0.06498 -0.0940 0.0073 1.0000
14.250 1.4490 0.07477 0.06876 -0.0942 0.0066 1.0000
14.500 1.4481 0.07851 0.07263 -0.0946 0.0060 1.0000
14.750 1.4449 0.08270 0.07695 -0.0953 0.0056 1.0000
15.000 1.4390 0.08740 0.08180 -0.0963 0.0054 1.0000
15.250 1.4351 0.09192 0.08652 -0.0972 0.0050 1.0000
15.500 1.4294 0.09683 0.09161 -0.0985 0.0048 1.0000
15.750 1.4234 0.10191 0.09687 -0.1001 0.0046 1.0000
16.000 1.4170 0.10718 0.10231 -0.1019 0.0045 1.0000
16.250 1.4101 0.11264 0.10794 -0.1040 0.0043 1.0000
16.500 1.4030 0.11825 0.11372 -0.1063 0.0042 1.0000
16.750 1.3954 0.12411 0.11974 -0.1090 0.0041 1.0000
17.000 1.3877 0.13014 0.12596 -0.1120 0.0040 1.0000
17.250 1.3796 0.13639 0.13237 -0.1153 0.0040 1.0000
17.500 1.3709 0.14296 0.13910 -0.1191 0.0039 1.0000
17.750 1.3630 0.14952 0.14581 -0.1229 0.0039 1.0000
18.000 1.3538 0.15650 0.15295 -0.1273 0.0038 1.0000
18.250 1.3454 0.16348 0.16008 -0.1318 0.0038 1.0000
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