NREL's S825 Airfoil (s825-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S825 Airfoil (s825-nr) Reynolds number: 200,000 Max Cl/Cd: 70.51 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s825-nr-200000-n5.txt Download as CSV file: xf-s825-nr-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5576 0.10977 0.10582 -0.0489 1.0000 0.0081
-14.000 -0.5843 0.10049 0.09641 -0.0532 1.0000 0.0081
-13.750 -0.5994 0.09443 0.09025 -0.0557 1.0000 0.0080
-13.500 -0.6220 0.08735 0.08300 -0.0585 1.0000 0.0080
-13.250 -0.6386 0.08177 0.07726 -0.0605 1.0000 0.0079
-13.000 -0.6549 0.07654 0.07186 -0.0620 1.0000 0.0079
-12.750 -0.6669 0.07224 0.06740 -0.0630 1.0000 0.0079
-12.500 -0.6768 0.06843 0.06343 -0.0635 1.0000 0.0079
-12.250 -0.6894 0.06432 0.05907 -0.0637 1.0000 0.0081
-12.000 -0.6937 0.06158 0.05619 -0.0633 1.0000 0.0081
-11.750 -0.6982 0.05888 0.05331 -0.0626 1.0000 0.0081
-11.500 -0.6994 0.05673 0.05103 -0.0616 1.0000 0.0082
-11.250 -0.7002 0.05477 0.04899 -0.0603 1.0000 0.0084
-11.000 -0.6991 0.05312 0.04729 -0.0589 1.0000 0.0084
-10.750 -0.6984 0.05159 0.04572 -0.0574 1.0000 0.0087
-10.500 -0.6967 0.05024 0.04431 -0.0557 1.0000 0.0088
-10.250 -0.6951 0.04899 0.04302 -0.0538 1.0000 0.0090
-10.000 -0.6807 0.04771 0.04165 -0.0540 0.9984 0.0092
-9.750 -0.6587 0.04644 0.04029 -0.0555 0.9954 0.0098
-9.500 -0.6359 0.04538 0.03910 -0.0567 0.9925 0.0105
-9.250 -0.6144 0.04441 0.03803 -0.0574 0.9886 0.0110
-9.000 -0.5928 0.04328 0.03690 -0.0591 0.9849 0.0116
-8.750 -0.5727 0.04213 0.03575 -0.0607 0.9808 0.0128
-8.500 -0.5550 0.04110 0.03466 -0.0614 0.9752 0.0141
-8.250 -0.5344 0.03992 0.03346 -0.0631 0.9710 0.0152
-8.000 -0.5267 0.03861 0.03214 -0.0627 0.9627 0.0162
-7.750 -0.5023 0.03716 0.03066 -0.0655 0.9582 0.0180
-7.500 -0.4893 0.03567 0.02917 -0.0661 0.9498 0.0202
-7.250 -0.4618 0.03407 0.02756 -0.0696 0.9450 0.0237
-7.000 -0.4463 0.03210 0.02561 -0.0716 0.9358 0.0273
-6.750 -0.4137 0.03006 0.02359 -0.0770 0.9314 0.0346
-6.500 -0.3897 0.02807 0.02158 -0.0808 0.9226 0.0423
-6.250 -0.3457 0.02492 0.01846 -0.0906 0.9187 0.0613
-6.000 -0.2816 0.01978 0.01324 -0.1081 0.9173 0.1053
-5.750 -0.2213 0.01600 0.01001 -0.1221 0.9136 0.3192
-5.500 -0.1875 0.01583 0.00962 -0.1235 0.9069 0.3451
-5.250 -0.1535 0.01592 0.00957 -0.1246 0.9011 0.3586
-5.000 -0.1269 0.01642 0.01013 -0.1235 0.8924 0.3667
-4.750 -0.0935 0.01631 0.00981 -0.1248 0.8853 0.3743
-4.500 -0.0647 0.01665 0.01021 -0.1241 0.8774 0.3780
-4.250 -0.0338 0.01679 0.01030 -0.1243 0.8689 0.3823
-4.000 0.0059 0.01639 0.00964 -0.1272 0.8621 0.3880
-3.750 0.0381 0.01639 0.00965 -0.1276 0.8528 0.3899
-3.500 0.0778 0.01616 0.00936 -0.1297 0.8452 0.3912
-3.250 0.1165 0.01582 0.00891 -0.1319 0.8344 0.3920
-3.000 0.1606 0.01541 0.00837 -0.1354 0.8238 0.3926
-2.750 0.2094 0.01505 0.00787 -0.1398 0.8117 0.3933
-2.500 0.2559 0.01477 0.00744 -0.1438 0.7965 0.3940
-2.250 0.2970 0.01456 0.00708 -0.1466 0.7791 0.3949
-2.000 0.3341 0.01441 0.00678 -0.1487 0.7612 0.3958
-1.750 0.3680 0.01432 0.00654 -0.1501 0.7434 0.3968
-1.500 0.3999 0.01426 0.00633 -0.1510 0.7259 0.3980
-1.250 0.4304 0.01423 0.00614 -0.1517 0.7089 0.3993
-1.000 0.4599 0.01421 0.00597 -0.1522 0.6924 0.4007
-0.500 0.5174 0.01419 0.00568 -0.1530 0.6624 0.4029
-0.250 0.5448 0.01421 0.00566 -0.1530 0.6491 0.4037
0.000 0.5721 0.01426 0.00566 -0.1529 0.6366 0.4045
0.250 0.5993 0.01432 0.00569 -0.1529 0.6247 0.4054
0.500 0.6265 0.01440 0.00572 -0.1528 0.6134 0.4064
0.750 0.6536 0.01447 0.00576 -0.1528 0.6022 0.4075
1.000 0.6810 0.01455 0.00581 -0.1528 0.5919 0.4086
1.250 0.7084 0.01464 0.00586 -0.1528 0.5830 0.4099
1.500 0.7359 0.01472 0.00594 -0.1529 0.5739 0.4113
1.750 0.7635 0.01481 0.00600 -0.1529 0.5658 0.4128
2.000 0.7911 0.01490 0.00607 -0.1530 0.5574 0.4144
2.250 0.8188 0.01501 0.00616 -0.1531 0.5497 0.4161
2.500 0.8465 0.01511 0.00624 -0.1532 0.5423 0.4177
2.750 0.8739 0.01524 0.00639 -0.1532 0.5361 0.4191
3.000 0.9010 0.01535 0.00659 -0.1531 0.5294 0.4206
3.250 0.9280 0.01552 0.00678 -0.1531 0.5233 0.4223
3.500 0.9552 0.01565 0.00699 -0.1530 0.5170 0.4241
3.750 0.9824 0.01581 0.00720 -0.1530 0.5113 0.4261
4.000 1.0098 0.01599 0.00739 -0.1530 0.5060 0.4282
4.250 1.0364 0.01612 0.00760 -0.1529 0.4987 0.4302
4.500 1.0624 0.01631 0.00777 -0.1526 0.4909 0.4323
4.750 1.0870 0.01645 0.00798 -0.1521 0.4803 0.4341
5.000 1.1114 0.01661 0.00822 -0.1515 0.4704 0.4358
5.250 1.1358 0.01681 0.00846 -0.1509 0.4614 0.4377
5.500 1.1602 0.01698 0.00874 -0.1503 0.4519 0.4398
5.750 1.1841 0.01719 0.00900 -0.1496 0.4427 0.4421
6.000 1.2077 0.01739 0.00927 -0.1488 0.4328 0.4446
6.250 1.2312 0.01760 0.00955 -0.1481 0.4225 0.4472
6.500 1.2535 0.01783 0.00987 -0.1471 0.4114 0.4496
6.750 1.2745 0.01808 0.01020 -0.1459 0.3988 0.4519
7.000 1.2946 0.01836 0.01055 -0.1445 0.3840 0.4546
7.250 1.3140 0.01865 0.01091 -0.1430 0.3664 0.4575
7.500 1.3309 0.01899 0.01130 -0.1411 0.3443 0.4605
7.750 1.3436 0.01946 0.01171 -0.1385 0.3135 0.4632
8.000 1.3513 0.02024 0.01232 -0.1351 0.2725 0.4654
8.250 1.3566 0.02131 0.01321 -0.1317 0.2333 0.4674
8.500 1.3633 0.02243 0.01419 -0.1285 0.2005 0.4698
8.750 1.3709 0.02355 0.01522 -0.1257 0.1739 0.4724
9.000 1.3784 0.02469 0.01630 -0.1229 0.1514 0.4753
9.250 1.3865 0.02584 0.01741 -0.1203 0.1331 0.4782
9.500 1.3945 0.02700 0.01858 -0.1178 0.1167 0.4808
9.750 1.4018 0.02824 0.01984 -0.1153 0.1028 0.4834
10.000 1.4085 0.02956 0.02118 -0.1129 0.0910 0.4866
10.250 1.4142 0.03100 0.02264 -0.1105 0.0809 0.4900
10.500 1.4209 0.03243 0.02412 -0.1084 0.0722 0.4936
10.750 1.4267 0.03398 0.02576 -0.1063 0.0651 0.4967
11.000 1.4307 0.03575 0.02759 -0.1044 0.0586 0.5000
11.250 1.4360 0.03750 0.02947 -0.1026 0.0533 0.5037
11.500 1.4388 0.03955 0.03158 -0.1010 0.0484 0.5074
11.750 1.4422 0.04166 0.03380 -0.0996 0.0443 0.5109
12.000 1.4453 0.04390 0.03616 -0.0984 0.0403 0.5142
12.250 1.4445 0.04664 0.03895 -0.0973 0.0371 0.5177
12.500 1.4485 0.04900 0.04147 -0.0965 0.0339 0.5220
12.750 1.4497 0.05178 0.04435 -0.0959 0.0310 0.5261
13.000 1.4483 0.05496 0.04763 -0.0955 0.0286 0.5300
13.250 1.4508 0.05780 0.05063 -0.0953 0.0262 0.5349
13.500 1.4509 0.06102 0.05395 -0.0952 0.0240 0.5400
13.750 1.4476 0.06480 0.05782 -0.0954 0.0223 0.5443
14.000 1.4487 0.06808 0.06129 -0.0956 0.0206 0.5499
14.500 1.4459 0.07562 0.06911 -0.0966 0.0178 0.5609
14.750 1.4415 0.07995 0.07356 -0.0975 0.0168 0.5667
15.000 1.4401 0.08393 0.07772 -0.0983 0.0157 0.5732
15.250 1.4379 0.08809 0.08204 -0.0992 0.0146 0.5803
15.500 1.4349 0.09246 0.08655 -0.1005 0.0137 0.5878
15.750 1.4291 0.09737 0.09157 -0.1020 0.0130 0.5957
16.000 1.4259 0.10192 0.09630 -0.1034 0.0122 0.6048
16.250 1.4226 0.10655 0.10110 -0.1051 0.0114 0.6154
16.500 1.4190 0.11131 0.10604 -0.1069 0.0108 0.6270
16.750 1.4148 0.11627 0.11116 -0.1089 0.0103 0.6401
17.000 1.4087 0.12163 0.11667 -0.1113 0.0099 0.6546
17.250 1.4013 0.12729 0.12249 -0.1140 0.0096 0.6711
17.500 1.3963 0.13253 0.12794 -0.1165 0.0092 0.6944
17.750 1.3916 0.13779 0.13344 -0.1191 0.0089 0.7282
18.000 1.3848 0.14278 0.13877 -0.1213 0.0086 0.8284
18.250 1.3777 0.14775 0.14392 -0.1239 0.0083 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S825 Airfoil (s825-nr)