NREL's S825 Airfoil (s825-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S825 Airfoil (s825-nr) Reynolds number: 500,000 Max Cl/Cd: 97.39 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s825-nr-500000.txt Download as CSV file: xf-s825-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S825 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6641 0.06834 0.06522 -0.0618 1.0000 0.0108
-11.750 -0.6829 0.06399 0.06077 -0.0622 1.0000 0.0105
-11.500 -0.6983 0.06036 0.05704 -0.0623 1.0000 0.0103
-11.250 -0.7587 0.05047 0.04641 -0.0608 1.0000 0.0086
-11.000 -0.7662 0.04818 0.04395 -0.0593 1.0000 0.0084
-10.750 -0.7724 0.04622 0.04186 -0.0574 1.0000 0.0084
-10.500 -0.7619 0.04426 0.03976 -0.0585 0.9983 0.0083
-10.250 -0.7401 0.04226 0.03760 -0.0608 0.9953 0.0083
-10.000 -0.7163 0.04070 0.03591 -0.0626 0.9924 0.0082
-9.750 -0.6942 0.03966 0.03472 -0.0612 0.9891 0.0084
-9.500 -0.6684 0.03891 0.03391 -0.0617 0.9860 0.0085
-9.250 -0.6398 0.03826 0.03319 -0.0632 0.9837 0.0085
-9.000 -0.6256 0.03735 0.03226 -0.0628 0.9774 0.0086
-8.750 -0.6042 0.03633 0.03124 -0.0643 0.9730 0.0090
-8.500 -0.5728 0.03518 0.03007 -0.0679 0.9709 0.0096
-8.250 -0.5603 0.03374 0.02861 -0.0681 0.9627 0.0101
-8.000 -0.5289 0.03223 0.02704 -0.0720 0.9595 0.0109
-7.750 -0.4936 0.02975 0.02454 -0.0791 0.9574 0.0121
-7.500 -0.4764 0.02780 0.02258 -0.0812 0.9488 0.0134
-7.250 -0.4345 0.02474 0.01946 -0.0905 0.9463 0.0159
-7.000 -0.3842 0.02132 0.01598 -0.1019 0.9451 0.0220
-6.750 -0.3279 0.01775 0.01233 -0.1144 0.9445 0.0339
-6.500 -0.2760 0.01568 0.01028 -0.1230 0.9440 0.0565
-6.250 -0.2437 0.01426 0.00895 -0.1262 0.9375 0.0928
-6.000 -0.1856 0.01119 0.00649 -0.1372 0.9381 0.3070
-5.750 -0.1498 0.01113 0.00641 -0.1388 0.9347 0.3423
-5.500 -0.1119 0.01121 0.00644 -0.1406 0.9324 0.3557
-5.250 -0.0731 0.01123 0.00642 -0.1426 0.9308 0.3632
-5.000 -0.0502 0.01130 0.00647 -0.1413 0.9221 0.3682
-4.750 -0.0133 0.01133 0.00640 -0.1429 0.9190 0.3743
-4.500 0.0137 0.01132 0.00646 -0.1424 0.9118 0.3780
-4.250 0.0449 0.01129 0.00643 -0.1426 0.9059 0.3812
-4.000 0.0747 0.01119 0.00627 -0.1428 0.8980 0.3839
-3.750 0.1101 0.01108 0.00609 -0.1442 0.8914 0.3869
-3.500 0.1465 0.01083 0.00577 -0.1458 0.8831 0.3891
-3.250 0.1905 0.01053 0.00545 -0.1491 0.8758 0.3908
-3.000 0.2377 0.01035 0.00523 -0.1530 0.8642 0.3922
-2.750 0.2885 0.01021 0.00499 -0.1578 0.8488 0.3934
-2.500 0.3307 0.01009 0.00472 -0.1608 0.8271 0.3940
-2.250 0.3644 0.01007 0.00454 -0.1620 0.8026 0.3947
-2.000 0.3939 0.01008 0.00441 -0.1624 0.7786 0.3953
-1.750 0.4215 0.01013 0.00430 -0.1624 0.7559 0.3961
-1.500 0.4482 0.01018 0.00422 -0.1622 0.7347 0.3969
-1.250 0.4746 0.01023 0.00415 -0.1619 0.7144 0.3977
-1.000 0.5009 0.01029 0.00409 -0.1617 0.6953 0.3986
-0.750 0.5271 0.01036 0.00404 -0.1614 0.6777 0.3995
-0.500 0.5536 0.01043 0.00401 -0.1612 0.6613 0.4004
0.000 0.6069 0.01058 0.00398 -0.1608 0.6319 0.4021
0.250 0.6338 0.01067 0.00399 -0.1607 0.6186 0.4028
0.500 0.6609 0.01064 0.00393 -0.1607 0.6061 0.4043
0.750 0.6877 0.01070 0.00395 -0.1605 0.5945 0.4055
1.000 0.7144 0.01080 0.00401 -0.1603 0.5835 0.4067
1.250 0.7414 0.01087 0.00408 -0.1602 0.5731 0.4078
1.500 0.7686 0.01096 0.00415 -0.1602 0.5640 0.4090
1.750 0.7957 0.01107 0.00423 -0.1601 0.5553 0.4102
2.000 0.8232 0.01115 0.00432 -0.1601 0.5471 0.4116
2.250 0.8503 0.01128 0.00440 -0.1600 0.5393 0.4130
2.500 0.8779 0.01136 0.00450 -0.1600 0.5319 0.4145
2.750 0.9052 0.01149 0.00460 -0.1600 0.5252 0.4159
3.000 0.9328 0.01161 0.00472 -0.1600 0.5190 0.4172
3.250 0.9601 0.01168 0.00480 -0.1600 0.5120 0.4187
3.500 0.9868 0.01177 0.00491 -0.1598 0.5042 0.4204
3.750 1.0127 0.01186 0.00502 -0.1595 0.4948 0.4220
4.000 1.0388 0.01197 0.00516 -0.1592 0.4864 0.4237
4.250 1.0649 0.01210 0.00531 -0.1589 0.4790 0.4255
4.500 1.0912 0.01222 0.00547 -0.1586 0.4718 0.4274
4.750 1.1171 0.01236 0.00562 -0.1583 0.4642 0.4295
5.000 1.1431 0.01251 0.00579 -0.1580 0.4574 0.4316
5.250 1.1688 0.01264 0.00595 -0.1576 0.4500 0.4335
5.500 1.1944 0.01274 0.00612 -0.1572 0.4426 0.4360
5.750 1.2192 0.01287 0.00630 -0.1567 0.4338 0.4382
6.000 1.2440 0.01302 0.00650 -0.1561 0.4251 0.4404
6.250 1.2676 0.01321 0.00672 -0.1554 0.4156 0.4428
6.500 1.2920 0.01335 0.00692 -0.1547 0.4053 0.4453
6.750 1.3152 0.01355 0.00714 -0.1539 0.3937 0.4476
7.000 1.3371 0.01373 0.00735 -0.1528 0.3796 0.4501
7.250 1.3579 0.01395 0.00761 -0.1515 0.3624 0.4527
7.500 1.3761 0.01429 0.00791 -0.1498 0.3388 0.4552
7.750 1.3904 0.01489 0.00834 -0.1474 0.2955 0.4577
8.000 1.3991 0.01596 0.00909 -0.1443 0.2411 0.4602
8.250 1.4090 0.01701 0.00990 -0.1415 0.1995 0.4627
8.500 1.4205 0.01795 0.01068 -0.1389 0.1674 0.4652
8.750 1.4325 0.01882 0.01148 -0.1365 0.1424 0.4679
9.250 1.4560 0.02058 0.01310 -0.1317 0.1043 0.4740
9.500 1.4671 0.02149 0.01396 -0.1292 0.0896 0.4771
9.750 1.4779 0.02242 0.01486 -0.1268 0.0769 0.4801
10.000 1.4879 0.02340 0.01584 -0.1244 0.0662 0.4833
10.250 1.4964 0.02450 0.01692 -0.1219 0.0570 0.4864
10.500 1.5067 0.02551 0.01796 -0.1197 0.0503 0.4899
10.750 1.5153 0.02665 0.01914 -0.1173 0.0445 0.4932
11.000 1.5228 0.02790 0.02042 -0.1150 0.0394 0.4965
11.250 1.5308 0.02917 0.02178 -0.1129 0.0351 0.5000
11.500 1.5371 0.03060 0.02325 -0.1107 0.0311 0.5037
11.750 1.5423 0.03219 0.02489 -0.1086 0.0278 0.5075
12.000 1.5489 0.03375 0.02652 -0.1069 0.0249 0.5114
12.250 1.5495 0.03589 0.02872 -0.1048 0.0222 0.5150
12.500 1.5568 0.03755 0.03049 -0.1035 0.0201 0.5196
12.750 1.5589 0.03978 0.03276 -0.1020 0.0181 0.5242
13.000 1.5602 0.04221 0.03532 -0.1008 0.0163 0.5286
13.250 1.5635 0.04455 0.03777 -0.0998 0.0147 0.5338
13.500 1.5610 0.04764 0.04093 -0.0989 0.0132 0.5388
13.750 1.5612 0.05059 0.04403 -0.0983 0.0120 0.5439
14.000 1.5619 0.05360 0.04715 -0.0980 0.0109 0.5499
14.250 1.5572 0.05738 0.05102 -0.0978 0.0100 0.5555
14.500 1.5518 0.06145 0.05524 -0.0979 0.0092 0.5610
14.750 1.5507 0.06504 0.05898 -0.0981 0.0085 0.5684
15.000 1.5487 0.06887 0.06294 -0.0986 0.0079 0.5758
15.250 1.5434 0.07327 0.06746 -0.0993 0.0075 0.5840
15.500 1.5318 0.07878 0.07312 -0.1004 0.0071 0.5910
16.000 1.5223 0.08809 0.08276 -0.1028 0.0064 0.6135
16.250 1.5175 0.09293 0.08777 -0.1042 0.0062 0.6281
16.750 1.5083 0.10287 0.09808 -0.1077 0.0057 0.6709
17.000 1.5034 0.10810 0.10350 -0.1099 0.0055 0.7059
17.250 1.4978 0.11362 0.10929 -0.1123 0.0054 0.7678
17.500 1.4860 0.11837 0.11435 -0.1132 0.0052 1.0000
17.750 1.4766 0.12437 0.12045 -0.1159 0.0051 1.0000
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