NREL's S825 Airfoil (s825-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S825 Airfoil (s825-nr) Reynolds number: 200,000 Max Cl/Cd: 70.13 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s825-nr-200000.txt Download as CSV file: xf-s825-nr-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4982 0.07420 0.07066 -0.0603 1.0000 0.0302
-11.000 -0.5177 0.06905 0.06546 -0.0610 1.0000 0.0296
-10.750 -0.5417 0.06364 0.05996 -0.0616 1.0000 0.0289
-10.500 -0.6214 0.05345 0.04923 -0.0634 1.0000 0.0251
-10.250 -0.6173 0.05053 0.04628 -0.0617 1.0000 0.0240
-10.000 -0.6332 0.04717 0.04285 -0.0604 1.0000 0.0237
-9.750 -0.7490 0.05656 0.05189 -0.0602 1.0000 0.0255
-9.500 -0.7411 0.05429 0.04957 -0.0582 1.0000 0.0238
-9.250 -0.7460 0.05103 0.04619 -0.0580 1.0000 0.0231
-9.000 -0.7473 0.04749 0.04244 -0.0581 1.0000 0.0223
-8.750 -0.7448 0.04363 0.03826 -0.0575 1.0000 0.0214
-8.500 -0.7380 0.04053 0.03484 -0.0558 1.0000 0.0208
-8.250 -0.7266 0.03852 0.03263 -0.0538 0.9997 0.0208
-8.000 -0.6952 0.03714 0.03109 -0.0539 0.9954 0.0213
-7.750 -0.6646 0.03629 0.03012 -0.0533 0.9904 0.0221
-7.500 -0.6292 0.03543 0.02909 -0.0552 0.9852 0.0241
-7.250 -0.6020 0.03528 0.02894 -0.0530 0.9795 0.0258
-7.000 -0.5686 0.03462 0.02834 -0.0548 0.9734 0.0289
-6.750 -0.5355 0.03428 0.02797 -0.0554 0.9677 0.0323
-6.500 -0.5017 0.03303 0.02681 -0.0590 0.9607 0.0383
-6.250 -0.4555 0.03136 0.02518 -0.0660 0.9572 0.0500
-6.000 -0.4104 0.02775 0.02170 -0.0768 0.9497 0.0703
-5.750 -0.2928 0.01989 0.01443 -0.1112 0.9568 0.3615
-5.500 -0.2676 0.02221 0.01690 -0.1078 0.9462 0.3785
-5.250 -0.2393 0.02410 0.01881 -0.1055 0.9373 0.3901
-5.000 -0.2227 0.02994 0.02508 -0.0934 0.9306 0.3942
-4.750 -0.1958 0.03103 0.02609 -0.0918 0.9209 0.4046
-4.500 -0.1846 0.04703 0.04254 -0.0548 0.9190 0.4377
-4.250 -0.1565 0.04261 0.03795 -0.0657 0.9080 0.4348
-4.000 -0.1161 0.04874 0.04414 -0.0496 0.9087 0.4701
-3.750 -0.0793 0.04688 0.04215 -0.0584 0.9034 0.4804
-3.500 0.0213 0.02870 0.02413 -0.0605 0.8768 0.4808
-3.250 0.0495 0.02735 0.02273 -0.0607 0.8695 0.4817
-3.000 0.0840 0.02598 0.02130 -0.0622 0.8638 0.4831
-2.750 0.1262 0.02441 0.01964 -0.0661 0.8601 0.4846
-2.500 0.1552 0.02320 0.01837 -0.0679 0.8486 0.4862
-2.250 0.1946 0.02184 0.01693 -0.0723 0.8391 0.4883
-2.000 0.2311 0.02011 0.01506 -0.0817 0.8261 0.4956
-1.750 0.2548 0.02595 0.02013 -0.1147 0.8461 0.4482
-1.500 0.2959 0.02518 0.01932 -0.1175 0.8344 0.4475
-1.250 0.3449 0.02418 0.01824 -0.1225 0.8222 0.4466
-1.000 0.3957 0.02288 0.01678 -0.1288 0.8073 0.4461
-0.750 0.4458 0.02140 0.01507 -0.1357 0.7902 0.4464
-0.500 0.4898 0.02026 0.01371 -0.1407 0.7724 0.4466
-0.250 0.5309 0.01929 0.01249 -0.1451 0.7548 0.4473
0.000 0.5677 0.01862 0.01158 -0.1482 0.7375 0.4482
0.250 0.5982 0.01826 0.01109 -0.1493 0.7206 0.4490
0.500 0.6268 0.01808 0.01083 -0.1498 0.7049 0.4498
0.750 0.6551 0.01798 0.01065 -0.1501 0.6906 0.4506
1.000 0.6833 0.01793 0.01053 -0.1504 0.6774 0.4514
1.250 0.7107 0.01788 0.01045 -0.1506 0.6646 0.4524
1.500 0.7384 0.01787 0.01041 -0.1508 0.6528 0.4537
1.750 0.7673 0.01788 0.01036 -0.1513 0.6422 0.4553
2.000 0.7966 0.01786 0.01029 -0.1519 0.6320 0.4573
2.250 0.8258 0.01780 0.01019 -0.1526 0.6222 0.4592
2.500 0.8578 0.01776 0.01004 -0.1539 0.6142 0.4611
2.750 0.8874 0.01770 0.00994 -0.1548 0.6050 0.4631
3.000 0.9176 0.01772 0.00991 -0.1556 0.5975 0.4647
3.250 0.9446 0.01777 0.01004 -0.1556 0.5896 0.4661
3.500 0.9740 0.01792 0.01019 -0.1561 0.5833 0.4677
3.750 1.0002 0.01801 0.01038 -0.1559 0.5756 0.4694
4.000 1.0301 0.01817 0.01050 -0.1565 0.5689 0.4715
4.250 1.0556 0.01823 0.01065 -0.1562 0.5602 0.4737
4.500 1.0846 0.01834 0.01072 -0.1566 0.5520 0.4765
4.750 1.1108 0.01840 0.01078 -0.1565 0.5421 0.4794
5.000 1.1361 0.01848 0.01095 -0.1561 0.5335 0.4815
5.250 1.1617 0.01860 0.01114 -0.1557 0.5249 0.4837
5.500 1.1863 0.01873 0.01137 -0.1551 0.5161 0.4863
5.750 1.2134 0.01886 0.01149 -0.1551 0.5076 0.4891
6.000 1.2370 0.01896 0.01170 -0.1544 0.4980 0.4922
6.250 1.2629 0.01908 0.01184 -0.1541 0.4890 0.4951
6.500 1.2854 0.01915 0.01203 -0.1531 0.4787 0.4974
6.750 1.3069 0.01927 0.01228 -0.1519 0.4678 0.5001
7.000 1.3287 0.01940 0.01248 -0.1507 0.4564 0.5033
7.250 1.3502 0.01954 0.01265 -0.1495 0.4443 0.5069
7.500 1.3697 0.01967 0.01285 -0.1480 0.4306 0.5105
7.750 1.3866 0.01980 0.01313 -0.1459 0.4156 0.5134
8.000 1.4019 0.01999 0.01343 -0.1436 0.3979 0.5169
8.250 1.4156 0.02022 0.01375 -0.1410 0.3766 0.5209
8.500 1.4251 0.02056 0.01406 -0.1377 0.3502 0.5248
8.750 1.4298 0.02108 0.01454 -0.1336 0.3118 0.5275
9.000 1.4283 0.02217 0.01541 -0.1289 0.2636 0.5302
9.500 1.4241 0.02524 0.01803 -0.1204 0.1870 0.5367
9.750 1.4238 0.02688 0.01950 -0.1167 0.1600 0.5402
10.000 1.4238 0.02852 0.02109 -0.1133 0.1385 0.5430
10.250 1.4229 0.03032 0.02285 -0.1100 0.1219 0.5462
10.500 1.4226 0.03221 0.02471 -0.1071 0.1081 0.5501
10.750 1.4237 0.03413 0.02663 -0.1046 0.0963 0.5545
11.000 1.4250 0.03611 0.02869 -0.1023 0.0864 0.5581
11.250 1.4228 0.03850 0.03113 -0.1001 0.0789 0.5619
11.500 1.4231 0.04082 0.03354 -0.0983 0.0718 0.5667
11.750 1.4222 0.04344 0.03623 -0.0968 0.0658 0.5712
12.000 1.4226 0.04601 0.03890 -0.0956 0.0603 0.5754
12.250 1.4194 0.04912 0.04208 -0.0944 0.0558 0.5800
12.500 1.4225 0.05172 0.04480 -0.0938 0.0508 0.5858
12.750 1.4170 0.05532 0.04842 -0.0931 0.0471 0.5897
13.000 1.4204 0.05811 0.05140 -0.0928 0.0433 0.5957
13.250 1.4215 0.06123 0.05462 -0.0928 0.0398 0.6019
13.500 1.4168 0.06508 0.05849 -0.0924 0.0368 0.6069
13.750 1.4200 0.06819 0.06181 -0.0926 0.0339 0.6148
14.000 1.4205 0.07164 0.06539 -0.0930 0.0314 0.6218
14.250 1.4176 0.07550 0.06922 -0.0927 0.0289 0.6297
14.500 1.4194 0.07901 0.07303 -0.0933 0.0270 0.6385
14.750 1.4197 0.08272 0.07689 -0.0940 0.0250 0.6489
15.000 1.4190 0.08655 0.08079 -0.0949 0.0234 0.6610
15.250 1.4182 0.09035 0.08473 -0.0951 0.0217 0.6738
15.500 1.4180 0.09428 0.08891 -0.0960 0.0204 0.6909
15.750 1.4178 0.09816 0.09300 -0.0969 0.0193 0.7142
16.000 1.4174 0.10198 0.09703 -0.0978 0.0184 0.7562
16.250 1.4135 0.10471 0.10002 -0.0973 0.0177 1.0000
16.500 1.4138 0.10871 0.10410 -0.0978 0.0169 1.0000
16.750 1.4090 0.11380 0.10941 -0.1000 0.0163 1.0000
17.000 1.4035 0.11906 0.11488 -0.1025 0.0157 1.0000
17.250 1.3990 0.12418 0.12017 -0.1049 0.0153 1.0000
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