NREL's S813 Airfoil (s813-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S813 Airfoil (s813-nr) Reynolds number: 50,000 Max Cl/Cd: 20.37 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s813-nr-50000-n5.txt Download as CSV file: xf-s813-nr-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4197 0.10910 0.10234 -0.0677 1.0000 0.0494
-12.250 -0.4378 0.10226 0.09562 -0.0702 1.0000 0.0486
-12.000 -0.4885 0.09075 0.08420 -0.0760 1.0000 0.0465
-11.750 -0.5499 0.08443 0.07781 -0.0771 1.0000 0.0450
-11.500 -0.5783 0.08225 0.07567 -0.0747 0.9993 0.0448
-11.250 -0.5928 0.07635 0.06956 -0.0794 0.9899 0.0447
-11.000 -0.6080 0.07130 0.06425 -0.0828 0.9810 0.0446
-10.750 -0.6208 0.06707 0.05973 -0.0848 0.9719 0.0446
-10.500 -0.6326 0.06376 0.05614 -0.0850 0.9622 0.0446
-10.250 -0.6420 0.06068 0.05271 -0.0843 0.9535 0.0448
-10.000 -0.6456 0.05751 0.04912 -0.0835 0.9455 0.0451
-9.750 -0.6392 0.05451 0.04591 -0.0831 0.9396 0.0458
-9.500 -0.6320 0.05229 0.04352 -0.0822 0.9335 0.0470
-9.250 -0.6173 0.05013 0.04113 -0.0824 0.9292 0.0493
-9.000 -0.6102 0.04833 0.03905 -0.0807 0.9233 0.0515
-8.750 -0.5958 0.04624 0.03656 -0.0797 0.9184 0.0538
-8.500 -0.5682 0.04398 0.03383 -0.0803 0.9155 0.0559
-8.250 -0.5341 0.04195 0.03174 -0.0818 0.9136 0.0594
-8.000 -0.5221 0.04103 0.03070 -0.0797 0.9084 0.0634
-7.750 -0.4961 0.03990 0.02929 -0.0793 0.9052 0.0689
-7.500 -0.4708 0.03867 0.02808 -0.0793 0.9024 0.0751
-7.250 -0.4465 0.03748 0.02677 -0.0793 0.8997 0.0840
-7.000 -0.4412 0.03678 0.02600 -0.0763 0.8945 0.0939
-6.750 -0.4368 0.03591 0.02518 -0.0734 0.8895 0.1080
-6.500 -0.4279 0.03469 0.02417 -0.0715 0.8859 0.1319
-6.250 -0.4244 0.03357 0.02334 -0.0689 0.8822 0.1722
-6.000 -0.4334 0.03291 0.02295 -0.0638 0.8764 0.2122
-5.750 -0.4326 0.03174 0.02233 -0.0607 0.8722 0.2922
-5.500 -0.4248 0.03079 0.02209 -0.0579 0.8693 0.4034
-5.250 -0.4218 0.03099 0.02273 -0.0529 0.8655 0.4821
-5.000 -0.4106 0.03192 0.02386 -0.0482 0.8620 0.5485
-4.750 -0.3961 0.03269 0.02450 -0.0449 0.8586 0.5989
-4.500 -0.3763 0.03349 0.02508 -0.0425 0.8559 0.6353
-4.250 -0.3532 0.03422 0.02554 -0.0408 0.8537 0.6647
-4.000 -0.3551 0.03470 0.02590 -0.0356 0.8494 0.6852
-3.750 -0.3446 0.03518 0.02618 -0.0322 0.8460 0.7057
-3.500 -0.3252 0.03576 0.02656 -0.0300 0.8432 0.7238
-3.250 -0.3026 0.03621 0.02681 -0.0285 0.8408 0.7411
-3.000 -0.2776 0.03657 0.02696 -0.0275 0.8388 0.7572
-2.750 -0.2740 0.03684 0.02710 -0.0235 0.8353 0.7714
-2.500 -0.2629 0.03706 0.02719 -0.0206 0.8319 0.7853
-2.250 -0.2456 0.03724 0.02721 -0.0189 0.8289 0.7988
-2.000 -0.2252 0.03738 0.02718 -0.0178 0.8264 0.8117
-1.750 -0.2021 0.03752 0.02715 -0.0173 0.8244 0.8237
-1.500 -0.1855 0.03774 0.02725 -0.0157 0.8215 0.8338
-1.250 -0.1752 0.03784 0.02726 -0.0133 0.8177 0.8444
-1.000 -0.1600 0.03790 0.02721 -0.0118 0.8146 0.8553
-0.750 -0.1341 0.03810 0.02728 -0.0120 0.8121 0.8637
-0.500 -0.1083 0.03823 0.02728 -0.0123 0.8097 0.8724
-0.250 -0.0921 0.03838 0.02735 -0.0111 0.8065 0.8814
0.000 -0.0776 0.03856 0.02747 -0.0099 0.8027 0.8895
0.250 -0.0607 0.03868 0.02751 -0.0089 0.7992 0.8983
0.500 -0.0291 0.03897 0.02772 -0.0105 0.7965 0.9041
0.750 0.0004 0.03920 0.02787 -0.0117 0.7940 0.9110
1.000 0.0157 0.03950 0.02815 -0.0109 0.7896 0.9182
1.250 0.0358 0.03978 0.02839 -0.0109 0.7854 0.9255
1.500 0.0665 0.04013 0.02872 -0.0126 0.7821 0.9313
1.750 0.1020 0.04052 0.02907 -0.0150 0.7794 0.9365
2.000 0.1199 0.04093 0.02948 -0.0149 0.7744 0.9439
2.250 0.1481 0.04141 0.02997 -0.0165 0.7698 0.9495
2.500 0.1802 0.04183 0.03040 -0.0185 0.7662 0.9558
2.750 0.2215 0.04233 0.03093 -0.0219 0.7634 0.9601
3.000 0.2375 0.04292 0.03157 -0.0221 0.7563 0.9679
3.250 0.2727 0.04345 0.03216 -0.0248 0.7519 0.9736
3.500 0.3136 0.04393 0.03270 -0.0281 0.7486 0.9790
3.750 0.3308 0.04461 0.03346 -0.0286 0.7405 0.9883
4.000 0.3650 0.04509 0.03404 -0.0309 0.7358 0.9980
4.500 0.3741 0.04547 0.03448 -0.0254 0.7215 1.0000
4.750 0.3831 0.04581 0.03485 -0.0236 0.7140 1.0000
5.000 0.4020 0.04619 0.03529 -0.0231 0.7069 1.0000
5.250 0.4195 0.04669 0.03587 -0.0227 0.6992 1.0000
5.500 0.4435 0.04712 0.03639 -0.0230 0.6918 1.0000
6.000 0.4920 0.04800 0.03748 -0.0235 0.6759 1.0000
6.250 0.5076 0.04860 0.03818 -0.0229 0.6650 1.0000
6.500 0.5347 0.04891 0.03862 -0.0233 0.6565 1.0000
6.750 0.5618 0.04912 0.03897 -0.0236 0.6471 1.0000
7.000 0.5803 0.04953 0.03951 -0.0230 0.6349 1.0000
7.250 0.6017 0.04976 0.03991 -0.0226 0.6228 1.0000
7.500 0.6257 0.04978 0.04010 -0.0222 0.6103 1.0000
7.750 0.6498 0.04964 0.04015 -0.0217 0.5969 1.0000
8.000 0.6724 0.04943 0.04014 -0.0210 0.5818 1.0000
8.250 0.6951 0.04902 0.03994 -0.0200 0.5651 1.0000
8.750 0.7427 0.04755 0.03889 -0.0176 0.5274 1.0000
9.000 0.7641 0.04672 0.03831 -0.0160 0.5041 1.0000
9.250 0.7832 0.04605 0.03783 -0.0142 0.4761 1.0000
9.500 0.8090 0.04477 0.03669 -0.0124 0.4391 1.0000
9.750 0.8441 0.04259 0.03437 -0.0104 0.3788 1.0000
10.000 0.8631 0.04238 0.03366 -0.0081 0.3060 1.0000
10.250 0.8658 0.04409 0.03492 -0.0061 0.2523 1.0000
10.500 0.8671 0.04620 0.03671 -0.0045 0.2120 1.0000
10.750 0.8694 0.04839 0.03864 -0.0032 0.1810 1.0000
11.000 0.8746 0.05047 0.04055 -0.0021 0.1571 1.0000
11.250 0.8814 0.05249 0.04244 -0.0011 0.1383 1.0000
11.500 0.8906 0.05438 0.04425 -0.0003 0.1232 1.0000
11.750 0.9034 0.05607 0.04593 0.0005 0.1105 1.0000
12.000 0.9184 0.05766 0.04762 0.0012 0.0993 1.0000
12.250 0.9370 0.05911 0.04913 0.0019 0.0899 1.0000
12.500 0.9562 0.06055 0.05049 0.0024 0.0816 1.0000
12.750 0.9780 0.06216 0.05244 0.0029 0.0737 1.0000
13.000 0.9968 0.06398 0.05429 0.0033 0.0674 1.0000
13.250 1.0131 0.06632 0.05697 0.0038 0.0621 1.0000
13.500 1.0285 0.06842 0.05900 0.0040 0.0575 1.0000
13.750 1.0309 0.07184 0.06289 0.0046 0.0544 1.0000
14.000 1.0322 0.07538 0.06678 0.0049 0.0518 1.0000
14.250 1.0315 0.07886 0.07047 0.0050 0.0495 1.0000
14.500 1.0331 0.08197 0.07366 0.0050 0.0475 1.0000
14.750 1.0265 0.08626 0.07814 0.0047 0.0460 1.0000
15.000 1.0096 0.09166 0.08391 0.0037 0.0453 1.0000
15.250 0.9902 0.09771 0.09028 0.0021 0.0448 1.0000
15.500 0.9698 0.10431 0.09715 -0.0003 0.0446 1.0000
15.750 0.9474 0.11174 0.10482 -0.0037 0.0447 1.0000
16.000 0.9236 0.12020 0.11346 -0.0082 0.0450 1.0000
16.250 0.9000 0.12954 0.12294 -0.0136 0.0455 1.0000
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