NREL's S813 Airfoil (s813-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S813 Airfoil (s813-nr) Reynolds number: 200,000 Max Cl/Cd: 65.35 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s813-nr-200000-n5.txt Download as CSV file: xf-s813-nr-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4389 0.11704 0.11347 -0.0614 1.0000 0.0149
-14.000 -0.5332 0.08747 0.08380 -0.0755 1.0000 0.0138
-13.750 -0.5800 0.07432 0.07041 -0.0840 1.0000 0.0135
-13.250 -0.6249 0.05874 0.05429 -0.0960 0.9678 0.0133
-13.000 -0.6324 0.05317 0.04842 -0.1010 0.9441 0.0134
-12.750 -0.6351 0.04877 0.04369 -0.1046 0.9199 0.0135
-12.500 -0.6361 0.04542 0.04004 -0.1064 0.8982 0.0139
-12.250 -0.6396 0.04247 0.03676 -0.1064 0.8804 0.0140
-12.000 -0.6409 0.04007 0.03406 -0.1058 0.8670 0.0142
-11.750 -0.6403 0.03786 0.03157 -0.1049 0.8565 0.0145
-11.500 -0.6371 0.03588 0.02932 -0.1037 0.8480 0.0148
-11.250 -0.6310 0.03414 0.02730 -0.1025 0.8410 0.0152
-11.000 -0.6252 0.03288 0.02574 -0.1011 0.8346 0.0161
-10.750 -0.6139 0.03115 0.02383 -0.1000 0.8292 0.0166
-10.500 -0.6020 0.02991 0.02250 -0.0990 0.8247 0.0172
-10.250 -0.5887 0.02879 0.02127 -0.0980 0.8201 0.0179
-10.000 -0.5740 0.02766 0.02001 -0.0970 0.8155 0.0185
-9.750 -0.5585 0.02660 0.01881 -0.0960 0.8115 0.0192
-9.500 -0.5424 0.02559 0.01764 -0.0949 0.8081 0.0199
-9.250 -0.5265 0.02466 0.01661 -0.0938 0.8042 0.0206
-9.000 -0.5107 0.02387 0.01569 -0.0926 0.8007 0.0215
-8.750 -0.4997 0.02283 0.01463 -0.0910 0.7975 0.0229
-8.500 -0.4868 0.02215 0.01386 -0.0893 0.7947 0.0239
-8.250 -0.4734 0.02152 0.01315 -0.0876 0.7918 0.0250
-8.000 -0.4586 0.02086 0.01242 -0.0861 0.7886 0.0261
-7.750 -0.4424 0.02027 0.01172 -0.0848 0.7856 0.0272
-7.500 -0.4273 0.01959 0.01099 -0.0833 0.7827 0.0292
-7.250 -0.4097 0.01904 0.01036 -0.0822 0.7803 0.0315
-7.000 -0.3906 0.01856 0.00977 -0.0812 0.7782 0.0341
-6.750 -0.3720 0.01803 0.00921 -0.0801 0.7757 0.0377
-6.500 -0.3524 0.01755 0.00872 -0.0792 0.7732 0.0442
-6.250 -0.3339 0.01697 0.00822 -0.0782 0.7708 0.0609
-6.000 -0.3154 0.01636 0.00774 -0.0772 0.7686 0.0929
-5.750 -0.2962 0.01580 0.00733 -0.0764 0.7665 0.1312
-5.500 -0.2762 0.01527 0.00695 -0.0756 0.7646 0.1744
-5.250 -0.2569 0.01470 0.00660 -0.0748 0.7626 0.2304
-5.000 -0.2392 0.01406 0.00630 -0.0738 0.7602 0.3027
-4.750 -0.2214 0.01342 0.00602 -0.0727 0.7580 0.3856
-4.500 -0.2028 0.01287 0.00588 -0.0715 0.7559 0.4747
-4.250 -0.1809 0.01267 0.00601 -0.0705 0.7541 0.5496
-4.000 -0.1554 0.01275 0.00618 -0.0699 0.7524 0.5947
-3.750 -0.1285 0.01285 0.00623 -0.0697 0.7508 0.6202
-3.500 -0.1010 0.01296 0.00626 -0.0697 0.7493 0.6387
-3.250 -0.0738 0.01309 0.00631 -0.0696 0.7477 0.6542
-3.000 -0.0475 0.01323 0.00641 -0.0694 0.7455 0.6660
-2.750 -0.0209 0.01335 0.00646 -0.0694 0.7436 0.6764
-2.500 0.0059 0.01347 0.00654 -0.0693 0.7418 0.6855
-2.250 0.0330 0.01359 0.00662 -0.0692 0.7401 0.6930
-2.000 0.0602 0.01369 0.00666 -0.0693 0.7385 0.7007
-1.750 0.0878 0.01378 0.00669 -0.0693 0.7369 0.7071
-1.500 0.1156 0.01387 0.00674 -0.0694 0.7354 0.7130
-1.250 0.1438 0.01392 0.00670 -0.0697 0.7341 0.7197
-1.000 0.1707 0.01404 0.00683 -0.0696 0.7326 0.7238
-0.750 0.1963 0.01418 0.00698 -0.0695 0.7306 0.7289
-0.500 0.2226 0.01427 0.00704 -0.0696 0.7286 0.7346
-0.250 0.2487 0.01438 0.00718 -0.0694 0.7266 0.7380
0.000 0.2755 0.01447 0.00727 -0.0694 0.7247 0.7420
0.250 0.3029 0.01454 0.00732 -0.0696 0.7230 0.7464
0.500 0.3307 0.01460 0.00736 -0.0699 0.7216 0.7504
0.750 0.3583 0.01467 0.00745 -0.0701 0.7203 0.7531
1.000 0.3867 0.01473 0.00751 -0.0703 0.7191 0.7561
1.250 0.4124 0.01486 0.00767 -0.0703 0.7170 0.7595
1.500 0.4368 0.01504 0.00790 -0.0702 0.7145 0.7632
1.750 0.4619 0.01519 0.00809 -0.0700 0.7122 0.7660
2.000 0.4878 0.01530 0.00826 -0.0699 0.7101 0.7684
2.250 0.5147 0.01539 0.00840 -0.0700 0.7082 0.7711
2.500 0.5425 0.01547 0.00851 -0.0703 0.7066 0.7739
2.750 0.5714 0.01552 0.00858 -0.0708 0.7051 0.7770
3.000 0.6011 0.01557 0.00864 -0.0714 0.7037 0.7799
3.250 0.6196 0.01588 0.00911 -0.0701 0.6995 0.7822
3.500 0.6432 0.01604 0.00935 -0.0697 0.6961 0.7847
3.750 0.6704 0.01607 0.00945 -0.0697 0.6933 0.7875
4.000 0.7009 0.01597 0.00940 -0.0703 0.6907 0.7903
4.250 0.7260 0.01598 0.00948 -0.0700 0.6859 0.7932
4.500 0.7507 0.01583 0.00941 -0.0695 0.6789 0.7959
4.750 0.7802 0.01543 0.00906 -0.0695 0.6719 0.7983
5.000 0.8042 0.01516 0.00888 -0.0686 0.6624 0.8012
5.250 0.8259 0.01502 0.00884 -0.0675 0.6527 0.8042
5.500 0.8524 0.01476 0.00863 -0.0671 0.6434 0.8073
5.750 0.8741 0.01462 0.00858 -0.0660 0.6316 0.8106
6.000 0.8925 0.01455 0.00864 -0.0642 0.6173 0.8138
6.250 0.9079 0.01456 0.00874 -0.0619 0.5991 0.8175
6.500 0.9248 0.01448 0.00869 -0.0598 0.5714 0.8214
6.750 0.9397 0.01438 0.00834 -0.0571 0.5129 0.8253
7.000 0.9323 0.01498 0.00853 -0.0507 0.4449 0.8300
7.250 0.9210 0.01611 0.00936 -0.0444 0.3881 0.8364
7.500 0.9118 0.01738 0.01039 -0.0391 0.3398 0.8428
7.750 0.9056 0.01870 0.01153 -0.0347 0.2957 0.8495
8.000 0.9017 0.02013 0.01276 -0.0309 0.2522 0.8566
8.250 0.9025 0.02144 0.01393 -0.0280 0.2154 0.8643
8.500 0.9055 0.02273 0.01509 -0.0255 0.1818 0.8729
8.750 0.9107 0.02396 0.01621 -0.0233 0.1528 0.8838
9.000 0.9176 0.02510 0.01729 -0.0214 0.1285 0.8980
9.250 0.9268 0.02623 0.01840 -0.0199 0.1083 0.9201
9.750 0.9530 0.02842 0.02056 -0.0187 0.0785 1.0000
10.000 0.9644 0.02964 0.02172 -0.0178 0.0685 1.0000
10.250 0.9771 0.03076 0.02287 -0.0169 0.0610 1.0000
10.500 0.9888 0.03198 0.02408 -0.0160 0.0551 1.0000
10.750 1.0008 0.03318 0.02530 -0.0152 0.0496 1.0000
11.000 1.0116 0.03449 0.02664 -0.0142 0.0453 1.0000
11.250 1.0246 0.03564 0.02784 -0.0135 0.0405 1.0000
11.500 1.0345 0.03706 0.02924 -0.0127 0.0366 1.0000
11.750 1.0475 0.03825 0.03052 -0.0120 0.0332 1.0000
12.000 1.0584 0.03962 0.03191 -0.0113 0.0298 1.0000
12.250 1.0680 0.04115 0.03350 -0.0105 0.0275 1.0000
12.500 1.0787 0.04260 0.03505 -0.0098 0.0252 1.0000
12.750 1.0884 0.04417 0.03669 -0.0092 0.0230 1.0000
13.000 1.0963 0.04593 0.03850 -0.0085 0.0209 1.0000
13.250 1.1056 0.04760 0.04027 -0.0079 0.0192 1.0000
13.500 1.1144 0.04934 0.04208 -0.0074 0.0176 1.0000
13.750 1.1202 0.05143 0.04422 -0.0068 0.0165 1.0000
14.000 1.1270 0.05345 0.04638 -0.0063 0.0154 1.0000
14.250 1.1327 0.05563 0.04868 -0.0058 0.0146 1.0000
14.500 1.1383 0.05787 0.05101 -0.0055 0.0139 1.0000
14.750 1.1422 0.06034 0.05356 -0.0053 0.0133 1.0000
15.000 1.1435 0.06314 0.05646 -0.0051 0.0128 1.0000
15.250 1.1469 0.06584 0.05933 -0.0049 0.0123 1.0000
15.500 1.1493 0.06869 0.06235 -0.0049 0.0120 1.0000
15.750 1.1510 0.07170 0.06551 -0.0051 0.0115 1.0000
16.000 1.1518 0.07490 0.06886 -0.0054 0.0112 1.0000
16.250 1.1519 0.07823 0.07233 -0.0060 0.0108 1.0000
16.500 1.1507 0.08185 0.07607 -0.0068 0.0104 1.0000
16.750 1.1486 0.08570 0.08006 -0.0077 0.0103 1.0000
17.000 1.1449 0.08987 0.08436 -0.0090 0.0100 1.0000
17.250 1.1400 0.09433 0.08894 -0.0106 0.0098 1.0000
17.500 1.1337 0.09918 0.09393 -0.0124 0.0096 1.0000
17.750 1.1258 0.10453 0.09950 -0.0146 0.0094 1.0000
18.000 1.1172 0.11014 0.10531 -0.0171 0.0093 1.0000
18.250 1.1073 0.11613 0.11150 -0.0200 0.0092 1.0000
18.500 1.0949 0.12290 0.11848 -0.0236 0.0091 1.0000
18.750 1.0823 0.12989 0.12565 -0.0275 0.0091 1.0000
19.000 1.0680 0.13756 0.13351 -0.0321 0.0091 1.0000
19.250 1.0514 0.14608 0.14223 -0.0374 0.0091 1.0000
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