NREL's S813 Airfoil (s813-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S813 Airfoil (s813-nr) Reynolds number: 500,000 Max Cl/Cd: 96.31 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s813-nr-500000-n5.txt Download as CSV file: xf-s813-nr-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6992 0.09605 0.09316 -0.0667 1.0000 0.0066
-16.500 -0.7367 0.08476 0.08164 -0.0729 1.0000 0.0065
-16.250 -0.7538 0.07772 0.07448 -0.0769 1.0000 0.0066
-16.000 -0.7668 0.07167 0.06832 -0.0804 1.0000 0.0066
-15.750 -0.7850 0.06518 0.06165 -0.0839 1.0000 0.0066
-15.500 -0.7964 0.06011 0.05645 -0.0865 1.0000 0.0066
-15.250 -0.8075 0.05546 0.05166 -0.0886 1.0000 0.0067
-15.000 -0.7987 0.05086 0.04690 -0.0942 0.9677 0.0068
-14.750 -0.7785 0.04704 0.04291 -0.1010 0.9401 0.0070
-14.500 -0.7628 0.04372 0.03929 -0.1059 0.8932 0.0071
-14.250 -0.7636 0.04145 0.03673 -0.1059 0.8599 0.0072
-14.000 -0.7675 0.03904 0.03408 -0.1053 0.8416 0.0073
-13.750 -0.7646 0.03731 0.03219 -0.1049 0.8289 0.0075
-13.500 -0.7635 0.03541 0.03011 -0.1042 0.8193 0.0076
-13.250 -0.7598 0.03377 0.02831 -0.1035 0.8112 0.0078
-13.000 -0.7551 0.03221 0.02661 -0.1026 0.8047 0.0080
-12.750 -0.7481 0.03087 0.02512 -0.1018 0.7986 0.0082
-12.250 -0.7309 0.02846 0.02241 -0.1000 0.7888 0.0087
-12.000 -0.7235 0.02718 0.02103 -0.0989 0.7842 0.0090
-11.750 -0.7149 0.02605 0.01979 -0.0978 0.7802 0.0093
-11.500 -0.7050 0.02500 0.01866 -0.0966 0.7764 0.0094
-11.250 -0.6928 0.02413 0.01772 -0.0956 0.7726 0.0097
-11.000 -0.6786 0.02346 0.01698 -0.0948 0.7690 0.0101
-10.750 -0.6671 0.02254 0.01597 -0.0935 0.7656 0.0104
-10.500 -0.6535 0.02180 0.01513 -0.0923 0.7628 0.0108
-10.250 -0.6402 0.02102 0.01427 -0.0911 0.7601 0.0112
-10.000 -0.6266 0.02027 0.01344 -0.0898 0.7572 0.0115
-9.750 -0.6115 0.01967 0.01273 -0.0886 0.7545 0.0119
-9.500 -0.5994 0.01893 0.01192 -0.0869 0.7520 0.0123
-9.250 -0.5893 0.01819 0.01112 -0.0848 0.7496 0.0128
-9.000 -0.5759 0.01773 0.01061 -0.0830 0.7474 0.0134
-8.750 -0.5592 0.01730 0.01015 -0.0817 0.7450 0.0142
-8.500 -0.5416 0.01680 0.00959 -0.0806 0.7426 0.0147
-8.250 -0.5229 0.01633 0.00905 -0.0795 0.7403 0.0153
-8.000 -0.5029 0.01593 0.00857 -0.0787 0.7382 0.0159
-7.750 -0.4826 0.01551 0.00809 -0.0778 0.7364 0.0164
-7.500 -0.4640 0.01495 0.00747 -0.0768 0.7346 0.0176
-7.250 -0.4423 0.01457 0.00705 -0.0762 0.7330 0.0187
-7.000 -0.4198 0.01421 0.00665 -0.0757 0.7313 0.0197
-6.750 -0.3966 0.01388 0.00627 -0.0752 0.7295 0.0207
-6.500 -0.3730 0.01357 0.00592 -0.0749 0.7277 0.0218
-6.250 -0.3498 0.01321 0.00555 -0.0744 0.7258 0.0246
-6.000 -0.3257 0.01292 0.00522 -0.0741 0.7240 0.0275
-5.750 -0.3019 0.01259 0.00491 -0.0738 0.7222 0.0357
-5.500 -0.2787 0.01220 0.00459 -0.0734 0.7207 0.0563
-5.250 -0.2553 0.01181 0.00430 -0.0731 0.7193 0.0824
-5.000 -0.2319 0.01140 0.00403 -0.0728 0.7179 0.1172
-4.750 -0.2085 0.01097 0.00378 -0.0725 0.7164 0.1600
-4.500 -0.1848 0.01053 0.00354 -0.0723 0.7149 0.2087
-4.250 -0.1607 0.01012 0.00332 -0.0721 0.7134 0.2593
-4.000 -0.1362 0.00973 0.00312 -0.0720 0.7118 0.3104
-3.750 -0.1115 0.00934 0.00291 -0.0719 0.7101 0.3665
-3.500 -0.0888 0.00874 0.00268 -0.0716 0.7085 0.4594
-3.250 -0.0653 0.00828 0.00258 -0.0712 0.7071 0.5514
-3.000 -0.0380 0.00819 0.00258 -0.0713 0.7058 0.5900
-2.750 -0.0097 0.00819 0.00258 -0.0716 0.7046 0.6132
-2.500 0.0190 0.00822 0.00259 -0.0719 0.7034 0.6303
-2.250 0.0476 0.00824 0.00260 -0.0722 0.7022 0.6425
-2.000 0.0763 0.00826 0.00263 -0.0725 0.7008 0.6512
-1.750 0.1052 0.00829 0.00263 -0.0729 0.6993 0.6596
-1.500 0.1339 0.00832 0.00266 -0.0732 0.6978 0.6662
-1.250 0.1629 0.00835 0.00265 -0.0736 0.6962 0.6729
-1.000 0.1916 0.00838 0.00269 -0.0740 0.6949 0.6779
-0.750 0.2206 0.00842 0.00271 -0.0744 0.6936 0.6833
-0.500 0.2497 0.00847 0.00271 -0.0748 0.6924 0.6885
-0.250 0.2785 0.00850 0.00275 -0.0752 0.6912 0.6922
0.000 0.3075 0.00854 0.00279 -0.0756 0.6900 0.6961
0.250 0.3366 0.00860 0.00282 -0.0760 0.6887 0.7003
0.500 0.3653 0.00864 0.00287 -0.0764 0.6873 0.7042
0.750 0.3938 0.00867 0.00295 -0.0768 0.6859 0.7072
1.000 0.4224 0.00871 0.00302 -0.0771 0.6845 0.7103
1.250 0.4511 0.00875 0.00308 -0.0775 0.6829 0.7133
1.500 0.4798 0.00879 0.00314 -0.0779 0.6813 0.7162
1.750 0.5087 0.00883 0.00318 -0.0783 0.6798 0.7188
2.000 0.5374 0.00886 0.00325 -0.0787 0.6784 0.7209
2.250 0.5661 0.00890 0.00332 -0.0791 0.6770 0.7230
2.500 0.5950 0.00895 0.00339 -0.0795 0.6756 0.7251
2.750 0.6241 0.00901 0.00347 -0.0800 0.6743 0.7273
3.000 0.6517 0.00904 0.00358 -0.0802 0.6717 0.7296
3.250 0.6790 0.00902 0.00361 -0.0802 0.6667 0.7319
3.500 0.7071 0.00895 0.00350 -0.0803 0.6598 0.7339
3.750 0.7325 0.00888 0.00351 -0.0800 0.6501 0.7358
4.000 0.7590 0.00884 0.00351 -0.0798 0.6416 0.7377
4.250 0.7854 0.00883 0.00354 -0.0797 0.6325 0.7398
4.500 0.8114 0.00884 0.00360 -0.0795 0.6222 0.7418
4.750 0.8369 0.00887 0.00366 -0.0792 0.6094 0.7439
5.000 0.8610 0.00894 0.00371 -0.0786 0.5903 0.7464
5.250 0.8800 0.00914 0.00378 -0.0770 0.5496 0.7488
5.500 0.8830 0.00989 0.00415 -0.0725 0.4721 0.7511
5.750 0.8798 0.01086 0.00478 -0.0670 0.4002 0.7536
6.000 0.8771 0.01161 0.00532 -0.0616 0.3505 0.7563
6.250 0.8765 0.01241 0.00593 -0.0568 0.3072 0.7596
6.500 0.8789 0.01324 0.00659 -0.0529 0.2683 0.7629
6.750 0.8824 0.01410 0.00730 -0.0493 0.2321 0.7657
7.000 0.8867 0.01498 0.00806 -0.0460 0.1982 0.7685
7.250 0.8931 0.01587 0.00883 -0.0432 0.1689 0.7716
7.500 0.9013 0.01674 0.00962 -0.0408 0.1438 0.7749
7.750 0.9102 0.01764 0.01042 -0.0386 0.1219 0.7784
8.000 0.9208 0.01848 0.01121 -0.0368 0.1030 0.7818
8.250 0.9325 0.01929 0.01199 -0.0350 0.0883 0.7854
8.500 0.9448 0.02010 0.01277 -0.0335 0.0760 0.7893
8.750 0.9576 0.02092 0.01357 -0.0320 0.0659 0.7933
9.000 0.9701 0.02175 0.01440 -0.0306 0.0571 0.7972
9.250 0.9828 0.02258 0.01523 -0.0292 0.0486 0.8016
9.500 0.9967 0.02338 0.01605 -0.0280 0.0429 0.8065
9.750 1.0091 0.02428 0.01693 -0.0267 0.0369 0.8116
10.000 1.0236 0.02503 0.01775 -0.0256 0.0338 0.8175
10.250 1.0371 0.02588 0.01863 -0.0245 0.0306 0.8244
10.500 1.0504 0.02671 0.01954 -0.0233 0.0278 0.8320
11.000 1.0765 0.02845 0.02139 -0.0210 0.0227 0.8510
11.250 1.0893 0.02931 0.02235 -0.0198 0.0208 0.8642
11.750 1.1171 0.03114 0.02442 -0.0182 0.0168 0.9315
12.000 1.1340 0.03217 0.02553 -0.0183 0.0145 1.0000
12.250 1.1457 0.03335 0.02672 -0.0175 0.0129 1.0000
12.500 1.1585 0.03448 0.02790 -0.0167 0.0118 1.0000
12.750 1.1697 0.03575 0.02920 -0.0159 0.0104 1.0000
13.000 1.1803 0.03709 0.03057 -0.0151 0.0093 1.0000
13.250 1.1914 0.03842 0.03196 -0.0143 0.0087 1.0000
13.500 1.2019 0.03981 0.03340 -0.0136 0.0079 1.0000
13.750 1.2119 0.04128 0.03493 -0.0129 0.0074 1.0000
14.000 1.2194 0.04301 0.03672 -0.0121 0.0069 1.0000
14.250 1.2287 0.04460 0.03839 -0.0115 0.0067 1.0000
14.500 1.2370 0.04632 0.04020 -0.0109 0.0065 1.0000
14.750 1.2447 0.04814 0.04211 -0.0104 0.0062 1.0000
15.000 1.2516 0.05007 0.04413 -0.0099 0.0060 1.0000
15.250 1.2586 0.05204 0.04618 -0.0095 0.0057 1.0000
15.500 1.2637 0.05423 0.04847 -0.0091 0.0056 1.0000
15.750 1.2691 0.05645 0.05078 -0.0089 0.0054 1.0000
16.000 1.2726 0.05894 0.05337 -0.0087 0.0054 1.0000
16.250 1.2758 0.06153 0.05605 -0.0086 0.0052 1.0000
16.500 1.2764 0.06448 0.05912 -0.0087 0.0050 1.0000
16.750 1.2774 0.06747 0.06222 -0.0089 0.0050 1.0000
17.000 1.2744 0.07108 0.06594 -0.0092 0.0049 1.0000
17.250 1.2701 0.07498 0.06997 -0.0098 0.0048 1.0000
17.500 1.2638 0.07929 0.07440 -0.0107 0.0046 1.0000
17.750 1.2609 0.08325 0.07849 -0.0117 0.0046 1.0000
18.000 1.2569 0.08747 0.08285 -0.0130 0.0045 1.0000
18.250 1.2518 0.09201 0.08752 -0.0145 0.0045 1.0000
18.500 1.2451 0.09694 0.09260 -0.0164 0.0045 1.0000
18.750 1.2388 0.10193 0.09772 -0.0184 0.0044 1.0000
19.000 1.2315 0.10720 0.10314 -0.0208 0.0044 1.0000
19.250 1.2222 0.11300 0.10908 -0.0236 0.0043 1.0000
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