NREL's S813 Airfoil (s813-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S813 Airfoil (s813-nr) Reynolds number: 200,000 Max Cl/Cd: 64.85 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s813-nr-200000.txt Download as CSV file: xf-s813-nr-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3107 0.07952 0.07635 -0.0952 0.9561 0.0430
-12.250 -0.3477 0.06749 0.06425 -0.1018 0.9519 0.0405
-12.000 -0.3933 0.05651 0.05308 -0.1086 0.9463 0.0394
-11.750 -0.4839 0.04564 0.04157 -0.1133 0.9352 0.0364
-11.500 -0.4894 0.04462 0.04029 -0.1130 0.9246 0.0356
-11.250 -0.5503 0.05041 0.04585 -0.1141 0.9356 0.0345
-11.000 -0.5613 0.04656 0.04171 -0.1135 0.9230 0.0339
-10.750 -0.5716 0.04339 0.03826 -0.1112 0.9122 0.0331
-10.500 -0.5821 0.04095 0.03551 -0.1077 0.9019 0.0326
-10.250 -0.5863 0.03816 0.03236 -0.1048 0.8946 0.0320
-10.000 -0.5840 0.03556 0.02938 -0.1024 0.8881 0.0318
-9.750 -0.5752 0.03359 0.02709 -0.1004 0.8836 0.0325
-9.500 -0.5635 0.03204 0.02526 -0.0988 0.8782 0.0335
-9.250 -0.5487 0.03058 0.02349 -0.0974 0.8736 0.0345
-9.000 -0.5301 0.02904 0.02164 -0.0962 0.8700 0.0352
-8.750 -0.5061 0.02698 0.01933 -0.0960 0.8666 0.0361
-8.500 -0.4774 0.02497 0.01730 -0.0966 0.8633 0.0375
-8.250 -0.4563 0.02412 0.01643 -0.0961 0.8597 0.0400
-8.000 -0.4343 0.02334 0.01556 -0.0955 0.8567 0.0427
-7.750 -0.4113 0.02252 0.01462 -0.0948 0.8542 0.0444
-7.500 -0.3934 0.02140 0.01349 -0.0937 0.8511 0.0468
-7.250 -0.3784 0.02073 0.01285 -0.0923 0.8474 0.0502
-7.000 -0.3616 0.02022 0.01228 -0.0909 0.8441 0.0547
-6.750 -0.3490 0.01942 0.01147 -0.0889 0.8410 0.0599
-6.500 -0.3337 0.01879 0.01080 -0.0872 0.8386 0.0699
-6.250 -0.3278 0.01778 0.01017 -0.0845 0.8349 0.1152
-6.000 -0.3219 0.01674 0.00971 -0.0820 0.8314 0.2185
-5.750 -0.3096 0.01604 0.00939 -0.0802 0.8286 0.3037
-5.500 -0.2944 0.01543 0.00912 -0.0786 0.8262 0.3853
-5.250 -0.2767 0.01495 0.00897 -0.0772 0.8241 0.4677
-5.000 -0.2603 0.01493 0.00934 -0.0753 0.8211 0.5486
-4.750 -0.2400 0.01534 0.00991 -0.0738 0.8183 0.6054
-4.500 -0.2173 0.01585 0.01038 -0.0727 0.8158 0.6422
-4.250 -0.1925 0.01643 0.01092 -0.0717 0.8137 0.6649
-4.000 -0.1667 0.01695 0.01138 -0.0709 0.8119 0.6822
-3.750 -0.1399 0.01737 0.01171 -0.0702 0.8102 0.6953
-3.500 -0.1130 0.01773 0.01198 -0.0697 0.8087 0.7071
-3.250 -0.0975 0.01838 0.01261 -0.0679 0.8052 0.7187
-3.000 -0.0784 0.01904 0.01328 -0.0661 0.8023 0.7260
-2.750 -0.0575 0.01942 0.01359 -0.0650 0.7998 0.7362
-2.500 -0.0329 0.01980 0.01394 -0.0641 0.7978 0.7434
-2.250 -0.0069 0.01998 0.01405 -0.0637 0.7961 0.7521
-2.000 0.0199 0.02025 0.01428 -0.0631 0.7949 0.7588
-1.750 0.0459 0.02043 0.01439 -0.0629 0.7937 0.7668
-1.500 0.0363 0.02166 0.01571 -0.0574 0.7869 0.7735
-1.250 0.0538 0.02199 0.01599 -0.0560 0.7839 0.7814
-1.000 0.0755 0.02230 0.01630 -0.0548 0.7821 0.7869
-0.750 0.1026 0.02240 0.01632 -0.0552 0.7807 0.7949
-0.500 0.1306 0.02249 0.01640 -0.0549 0.7795 0.7991
-0.250 0.0946 0.02431 0.01829 -0.0460 0.7699 0.8074
0.000 0.1186 0.02446 0.01841 -0.0456 0.7677 0.8125
0.250 0.1463 0.02457 0.01851 -0.0455 0.7662 0.8174
0.500 0.1780 0.02460 0.01850 -0.0466 0.7651 0.8230
0.750 0.2112 0.02453 0.01842 -0.0475 0.7641 0.8270
1.000 0.1617 0.02651 0.02046 -0.0364 0.7523 0.8347
1.250 0.1964 0.02651 0.02042 -0.0381 0.7508 0.8394
1.500 0.2314 0.02639 0.02031 -0.0392 0.7498 0.8424
1.750 0.2695 0.02628 0.02021 -0.0409 0.7490 0.8455
2.000 0.3100 0.02614 0.02007 -0.0431 0.7484 0.8489
2.250 0.2717 0.02794 0.02189 -0.0344 0.7357 0.8561
2.500 0.3087 0.02775 0.02173 -0.0357 0.7346 0.8589
2.750 0.3488 0.02752 0.02152 -0.0377 0.7337 0.8617
3.000 0.3294 0.02903 0.02304 -0.0321 0.7218 0.8685
3.250 0.3664 0.02880 0.02285 -0.0334 0.7203 0.8711
3.500 0.3930 0.02892 0.02302 -0.0334 0.7169 0.8745
3.750 0.4489 0.02804 0.02219 -0.0372 0.7184 0.8764
4.000 0.4353 0.02938 0.02355 -0.0324 0.7059 0.8829
4.250 0.4400 0.03010 0.02433 -0.0296 0.6970 0.8877
4.500 0.4724 0.02983 0.02413 -0.0301 0.6933 0.8915
4.750 0.5155 0.02916 0.02353 -0.0321 0.6915 0.8945
5.000 0.5647 0.02815 0.02259 -0.0347 0.6904 0.8970
5.250 0.6050 0.02731 0.02185 -0.0360 0.6873 0.9000
5.500 0.6747 0.02508 0.01973 -0.0409 0.6873 0.9010
5.750 0.7730 0.02173 0.01647 -0.0499 0.6889 0.8999
6.000 0.7724 0.02200 0.01685 -0.0454 0.6775 0.9062
6.250 0.8503 0.01932 0.01424 -0.0517 0.6748 0.9062
6.500 0.8648 0.01897 0.01401 -0.0492 0.6637 0.9123
6.750 0.8943 0.01794 0.01309 -0.0486 0.6536 0.9170
7.000 0.9258 0.01682 0.01205 -0.0482 0.6418 0.9223
7.250 0.9424 0.01622 0.01159 -0.0458 0.6271 0.9296
7.500 0.9477 0.01594 0.01142 -0.0415 0.6100 0.9404
7.750 0.9611 0.01564 0.01122 -0.0388 0.5857 0.9528
8.000 0.9857 0.01520 0.01066 -0.0380 0.5244 0.9669
8.250 0.9910 0.01612 0.01084 -0.0354 0.4148 1.0000
8.500 0.9784 0.01799 0.01224 -0.0312 0.3450 1.0000
8.750 0.9677 0.02013 0.01398 -0.0278 0.2824 1.0000
9.000 0.9601 0.02230 0.01579 -0.0250 0.2250 1.0000
9.250 0.9558 0.02440 0.01754 -0.0225 0.1762 1.0000
9.500 0.9550 0.02637 0.01921 -0.0204 0.1383 1.0000
9.750 0.9581 0.02813 0.02079 -0.0186 0.1137 1.0000
10.000 0.9629 0.02980 0.02233 -0.0170 0.0977 1.0000
10.250 0.9711 0.03129 0.02377 -0.0157 0.0862 1.0000
10.500 0.9796 0.03277 0.02522 -0.0143 0.0779 1.0000
10.750 0.9886 0.03426 0.02665 -0.0131 0.0705 1.0000
11.000 1.0013 0.03550 0.02797 -0.0122 0.0640 1.0000
11.250 1.0107 0.03704 0.02942 -0.0111 0.0578 1.0000
11.500 1.0243 0.03822 0.03072 -0.0104 0.0525 1.0000
11.750 1.0348 0.03972 0.03216 -0.0095 0.0476 1.0000
12.000 1.0479 0.04112 0.03367 -0.0086 0.0429 1.0000
12.250 1.0592 0.04260 0.03515 -0.0078 0.0390 1.0000
12.500 1.0750 0.04417 0.03677 -0.0068 0.0352 1.0000
12.750 1.0856 0.04572 0.03845 -0.0061 0.0319 1.0000
13.000 1.1047 0.04756 0.04021 -0.0055 0.0285 1.0000
13.250 1.1173 0.04924 0.04211 -0.0047 0.0273 1.0000
13.500 1.1308 0.05113 0.04420 -0.0039 0.0257 1.0000
13.750 1.1429 0.05316 0.04638 -0.0032 0.0246 1.0000
14.000 1.1522 0.05531 0.04867 -0.0026 0.0236 1.0000
14.250 1.1613 0.05752 0.05095 -0.0021 0.0227 1.0000
14.750 1.1648 0.06456 0.05846 -0.0007 0.0214 1.0000
15.000 1.1572 0.06796 0.06215 -0.0001 0.0210 1.0000
15.250 1.1473 0.07184 0.06631 0.0003 0.0205 1.0000
15.500 1.1363 0.07636 0.07111 0.0004 0.0205 1.0000
15.750 1.1220 0.08132 0.07633 0.0000 0.0204 1.0000
16.000 1.1054 0.08685 0.08212 -0.0010 0.0205 1.0000
16.250 1.0867 0.09282 0.08834 -0.0025 0.0205 1.0000
16.500 1.0655 0.09957 0.09533 -0.0048 0.0206 1.0000
16.750 1.0446 0.10674 0.10270 -0.0079 0.0207 1.0000
17.000 1.0211 0.11486 0.11103 -0.0120 0.0209 1.0000
17.250 0.9972 0.12372 0.12006 -0.0171 0.0211 1.0000
17.500 0.9722 0.13363 0.13013 -0.0231 0.0213 1.0000
17.750 0.9470 0.14447 0.14109 -0.0299 0.0216 1.0000
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