NREL's S813 Airfoil (s813-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S813 Airfoil (s813-nr) Reynolds number: 1,000,000 Max Cl/Cd: 115.28 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s813-nr-1000000-n5.txt Download as CSV file: xf-s813-nr-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S813 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.250 -0.7212 0.13383 0.13169 -0.0458 1.0000 0.0046
-19.000 -0.7655 0.12060 0.11832 -0.0524 1.0000 0.0046
-18.750 -0.8028 0.10948 0.10703 -0.0579 1.0000 0.0044
-18.500 -0.8364 0.09930 0.09673 -0.0631 1.0000 0.0044
-18.250 -0.8657 0.09028 0.08756 -0.0678 1.0000 0.0043
-18.000 -0.8909 0.08212 0.07926 -0.0721 1.0000 0.0043
-17.750 -0.9068 0.07576 0.07278 -0.0755 1.0000 0.0042
-17.500 -0.9351 0.06760 0.06446 -0.0799 1.0000 0.0043
-17.250 -0.9536 0.06136 0.05807 -0.0831 1.0000 0.0043
-17.000 -0.9634 0.05668 0.05327 -0.0854 1.0000 0.0044
-16.750 -0.9731 0.05225 0.04873 -0.0873 1.0000 0.0044
-16.500 -0.9702 0.04799 0.04434 -0.0912 0.9780 0.0044
-16.250 -0.9411 0.04330 0.03946 -0.1011 0.9500 0.0047
-16.000 -0.9245 0.04078 0.03654 -0.1048 0.8666 0.0048
-15.500 -0.9286 0.03648 0.03186 -0.1038 0.8233 0.0049
-15.250 -0.9275 0.03459 0.02984 -0.1033 0.8112 0.0050
-15.000 -0.9239 0.03294 0.02807 -0.1028 0.8023 0.0051
-14.750 -0.9164 0.03165 0.02669 -0.1022 0.7945 0.0052
-14.500 -0.9103 0.03024 0.02518 -0.1015 0.7882 0.0053
-14.250 -0.9036 0.02892 0.02376 -0.1008 0.7824 0.0054
-14.000 -0.8985 0.02753 0.02226 -0.0998 0.7774 0.0054
-13.750 -0.8883 0.02650 0.02116 -0.0990 0.7729 0.0057
-13.500 -0.8803 0.02535 0.01992 -0.0980 0.7684 0.0058
-13.000 -0.8605 0.02338 0.01776 -0.0959 0.7610 0.0060
-12.750 -0.8494 0.02248 0.01679 -0.0948 0.7574 0.0061
-12.500 -0.8358 0.02176 0.01600 -0.0939 0.7538 0.0062
-12.250 -0.8267 0.02079 0.01494 -0.0925 0.7503 0.0064
-12.000 -0.8150 0.02000 0.01409 -0.0912 0.7473 0.0067
-11.750 -0.8008 0.01934 0.01340 -0.0901 0.7446 0.0069
-11.500 -0.7875 0.01866 0.01266 -0.0889 0.7418 0.0070
-11.250 -0.7723 0.01811 0.01206 -0.0878 0.7392 0.0073
-11.000 -0.7553 0.01768 0.01159 -0.0868 0.7367 0.0077
-10.750 -0.7410 0.01714 0.01099 -0.0854 0.7342 0.0080
-10.500 -0.7273 0.01659 0.01038 -0.0838 0.7322 0.0082
-10.250 -0.7117 0.01617 0.00993 -0.0824 0.7302 0.0085
-10.000 -0.6956 0.01586 0.00957 -0.0809 0.7279 0.0088
-9.750 -0.6811 0.01540 0.00906 -0.0791 0.7256 0.0091
-9.500 -0.6630 0.01496 0.00858 -0.0780 0.7233 0.0096
-9.250 -0.6428 0.01460 0.00818 -0.0772 0.7213 0.0099
-9.000 -0.6216 0.01429 0.00782 -0.0765 0.7193 0.0104
-8.750 -0.5996 0.01398 0.00748 -0.0759 0.7177 0.0109
-8.500 -0.5774 0.01364 0.00711 -0.0754 0.7162 0.0113
-8.250 -0.5544 0.01334 0.00678 -0.0750 0.7146 0.0117
-8.000 -0.5304 0.01310 0.00650 -0.0747 0.7130 0.0121
-7.750 -0.5084 0.01269 0.00606 -0.0741 0.7113 0.0129
-7.500 -0.4851 0.01237 0.00571 -0.0737 0.7096 0.0136
-7.250 -0.4610 0.01210 0.00541 -0.0734 0.7080 0.0143
-7.000 -0.4364 0.01185 0.00512 -0.0731 0.7063 0.0149
-6.750 -0.4115 0.01162 0.00485 -0.0729 0.7046 0.0156
-6.500 -0.3860 0.01142 0.00462 -0.0729 0.7031 0.0161
-6.250 -0.3609 0.01114 0.00433 -0.0727 0.7018 0.0173
-6.000 -0.3353 0.01089 0.00408 -0.0726 0.7005 0.0185
-5.750 -0.3093 0.01067 0.00385 -0.0726 0.6991 0.0201
-5.500 -0.2831 0.01047 0.00363 -0.0726 0.6977 0.0225
-5.250 -0.2574 0.01021 0.00341 -0.0725 0.6963 0.0297
-5.000 -0.2324 0.00988 0.00317 -0.0724 0.6949 0.0499
-4.750 -0.2068 0.00961 0.00297 -0.0724 0.6935 0.0698
-4.500 -0.1816 0.00929 0.00276 -0.0723 0.6920 0.0996
-4.250 -0.1562 0.00897 0.00257 -0.0723 0.6905 0.1344
-3.750 -0.1052 0.00829 0.00221 -0.0723 0.6879 0.2237
-3.500 -0.0786 0.00802 0.00207 -0.0724 0.6868 0.2600
-3.250 -0.0517 0.00777 0.00195 -0.0726 0.6856 0.2987
-3.000 -0.0264 0.00732 0.00177 -0.0727 0.6843 0.3743
-2.750 -0.0017 0.00677 0.00159 -0.0727 0.6830 0.4710
-2.500 0.0252 0.00649 0.00149 -0.0729 0.6818 0.5277
-2.250 0.0530 0.00632 0.00144 -0.0732 0.6804 0.5691
-2.000 0.0813 0.00624 0.00143 -0.0735 0.6790 0.5996
-1.750 0.1102 0.00622 0.00143 -0.0739 0.6777 0.6167
-1.500 0.1393 0.00622 0.00143 -0.0743 0.6764 0.6285
-1.250 0.1683 0.00623 0.00144 -0.0747 0.6752 0.6378
-1.000 0.1976 0.00625 0.00145 -0.0752 0.6740 0.6453
-0.750 0.2268 0.00626 0.00147 -0.0756 0.6730 0.6520
-0.500 0.2562 0.00627 0.00148 -0.0761 0.6719 0.6578
-0.250 0.2854 0.00628 0.00150 -0.0766 0.6705 0.6626
0.000 0.3147 0.00629 0.00153 -0.0770 0.6691 0.6675
0.250 0.3440 0.00632 0.00155 -0.0775 0.6678 0.6719
0.500 0.3732 0.00633 0.00157 -0.0780 0.6666 0.6754
0.750 0.4023 0.00635 0.00161 -0.0784 0.6653 0.6790
1.000 0.4315 0.00638 0.00164 -0.0789 0.6639 0.6827
1.250 0.4606 0.00641 0.00168 -0.0793 0.6625 0.6862
1.500 0.4898 0.00646 0.00171 -0.0798 0.6612 0.6892
1.750 0.5188 0.00649 0.00177 -0.0802 0.6599 0.6919
2.000 0.5478 0.00651 0.00183 -0.0807 0.6586 0.6945
2.250 0.5769 0.00653 0.00188 -0.0811 0.6569 0.6969
2.500 0.6055 0.00653 0.00191 -0.0814 0.6528 0.6992
2.750 0.6333 0.00655 0.00190 -0.0816 0.6456 0.7014
3.000 0.6614 0.00654 0.00192 -0.0818 0.6362 0.7033
3.250 0.6890 0.00656 0.00194 -0.0819 0.6278 0.7051
3.500 0.7163 0.00659 0.00198 -0.0820 0.6180 0.7070
3.750 0.7439 0.00663 0.00205 -0.0821 0.6079 0.7088
4.000 0.7700 0.00672 0.00211 -0.0820 0.5913 0.7106
4.250 0.7943 0.00689 0.00221 -0.0815 0.5650 0.7126
4.500 0.8104 0.00741 0.00246 -0.0795 0.5042 0.7147
4.750 0.8163 0.00838 0.00301 -0.0757 0.4150 0.7168
5.000 0.8236 0.00923 0.00351 -0.0722 0.3430 0.7186
5.250 0.8331 0.00988 0.00393 -0.0691 0.2910 0.7206
5.500 0.8445 0.01035 0.00428 -0.0663 0.2560 0.7228
5.750 0.8519 0.01082 0.00462 -0.0627 0.2250 0.7251
6.000 0.8581 0.01142 0.00509 -0.0590 0.1918 0.7274
6.250 0.8679 0.01197 0.00554 -0.0561 0.1659 0.7296
6.500 0.8788 0.01253 0.00601 -0.0536 0.1434 0.7319
6.750 0.8896 0.01313 0.00651 -0.0511 0.1231 0.7341
7.000 0.9016 0.01369 0.00703 -0.0489 0.1060 0.7365
7.250 0.9138 0.01429 0.00758 -0.0468 0.0902 0.7389
7.500 0.9272 0.01487 0.00814 -0.0449 0.0785 0.7414
7.750 0.9392 0.01556 0.00877 -0.0430 0.0644 0.7440
8.000 0.9530 0.01620 0.00938 -0.0414 0.0555 0.7465
8.250 0.9661 0.01690 0.01003 -0.0397 0.0459 0.7490
8.500 0.9815 0.01749 0.01064 -0.0384 0.0411 0.7517
8.750 0.9952 0.01819 0.01133 -0.0369 0.0345 0.7548
9.000 1.0099 0.01886 0.01200 -0.0356 0.0305 0.7581
9.250 1.0257 0.01949 0.01265 -0.0345 0.0279 0.7613
9.500 1.0416 0.02013 0.01332 -0.0334 0.0258 0.7643
9.750 1.0561 0.02085 0.01404 -0.0322 0.0231 0.7676
10.000 1.0714 0.02153 0.01476 -0.0311 0.0214 0.7712
10.250 1.0870 0.02221 0.01549 -0.0301 0.0198 0.7752
10.500 1.1013 0.02300 0.01628 -0.0290 0.0176 0.7791
10.750 1.1156 0.02377 0.01708 -0.0279 0.0153 0.7833
11.000 1.1292 0.02460 0.01793 -0.0268 0.0134 0.7883
11.250 1.1429 0.02545 0.01881 -0.0257 0.0114 0.7937
11.500 1.1557 0.02635 0.01974 -0.0245 0.0095 0.7996
11.750 1.1692 0.02722 0.02067 -0.0235 0.0084 0.8064
12.000 1.1812 0.02822 0.02171 -0.0224 0.0069 0.8134
12.250 1.1942 0.02915 0.02270 -0.0213 0.0063 0.8218
12.500 1.2073 0.03007 0.02371 -0.0204 0.0061 0.8313
12.750 1.2192 0.03109 0.02480 -0.0193 0.0056 0.8432
13.000 1.2294 0.03220 0.02600 -0.0181 0.0050 0.8598
13.250 1.2396 0.03318 0.02713 -0.0167 0.0048 0.8899
13.750 1.2700 0.03550 0.02973 -0.0166 0.0044 1.0000
14.250 1.2922 0.03808 0.03241 -0.0152 0.0042 1.0000
14.500 1.3029 0.03943 0.03381 -0.0145 0.0040 1.0000
14.750 1.3126 0.04090 0.03534 -0.0138 0.0039 1.0000
15.000 1.3222 0.04241 0.03691 -0.0132 0.0038 1.0000
15.250 1.3309 0.04402 0.03857 -0.0125 0.0035 1.0000
15.500 1.3396 0.04567 0.04027 -0.0120 0.0035 1.0000
15.750 1.3467 0.04750 0.04219 -0.0114 0.0034 1.0000
16.000 1.3533 0.04943 0.04418 -0.0110 0.0033 1.0000
16.250 1.3586 0.05154 0.04637 -0.0105 0.0032 1.0000
16.500 1.3611 0.05398 0.04890 -0.0101 0.0031 1.0000
16.750 1.3653 0.05631 0.05132 -0.0099 0.0030 1.0000
17.000 1.3656 0.05914 0.05425 -0.0096 0.0029 1.0000
17.250 1.3697 0.06161 0.05680 -0.0096 0.0029 1.0000
17.500 1.3747 0.06402 0.05929 -0.0097 0.0029 1.0000
17.750 1.3758 0.06696 0.06233 -0.0099 0.0028 1.0000
18.000 1.3769 0.06997 0.06543 -0.0103 0.0028 1.0000
18.250 1.3750 0.07347 0.06904 -0.0108 0.0028 1.0000
18.500 1.3741 0.07694 0.07261 -0.0115 0.0027 1.0000
18.750 1.3721 0.08065 0.07644 -0.0124 0.0027 1.0000
19.000 1.3697 0.08450 0.08038 -0.0135 0.0027 1.0000
19.250 1.3643 0.08891 0.08491 -0.0149 0.0027 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S813 Airfoil (s813-nr)