NREL's S813 Airfoil (s813-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S813 Airfoil (s813-nr) Reynolds number: 500,000 Max Cl/Cd: 104.58 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s813-nr-500000.txt Download as CSV file: xf-s813-nr-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3487 0.10221 0.09978 -0.0724 0.8792 0.0161
-14.250 -0.4002 0.08536 0.08293 -0.0813 0.8890 0.0150
-14.000 -0.6334 0.06629 0.06335 -0.0893 1.0000 0.0123
-13.750 -0.6571 0.06057 0.05749 -0.0919 1.0000 0.0123
-13.500 -0.6626 0.05428 0.05094 -0.0987 0.9767 0.0123
-13.250 -0.6679 0.04770 0.04402 -0.1059 0.9521 0.0123
-13.000 -0.6676 0.04304 0.03899 -0.1103 0.9135 0.0123
-12.750 -0.6786 0.03981 0.03540 -0.1094 0.8807 0.0125
-12.500 -0.6843 0.03745 0.03281 -0.1080 0.8634 0.0127
-12.250 -0.6868 0.03546 0.03057 -0.1065 0.8517 0.0128
-12.000 -0.6864 0.03372 0.02865 -0.1050 0.8424 0.0130
-11.750 -0.6829 0.03242 0.02722 -0.1035 0.8350 0.0133
-11.500 -0.6793 0.03060 0.02519 -0.1018 0.8284 0.0134
-11.250 -0.6707 0.02979 0.02428 -0.1005 0.8230 0.0139
-11.000 -0.6632 0.02869 0.02307 -0.0989 0.8179 0.0146
-10.750 -0.6541 0.02744 0.02165 -0.0972 0.8133 0.0149
-10.500 -0.6428 0.02617 0.02017 -0.0957 0.8095 0.0153
-10.250 -0.6325 0.02545 0.01930 -0.0938 0.8057 0.0158
-10.000 -0.6224 0.02487 0.01857 -0.0917 0.8018 0.0161
-9.750 -0.5954 0.02215 0.01570 -0.0925 0.7994 0.0171
-9.500 -0.5785 0.02116 0.01464 -0.0915 0.7963 0.0177
-9.250 -0.5624 0.02041 0.01380 -0.0903 0.7933 0.0183
-9.000 -0.5469 0.01971 0.01306 -0.0889 0.7903 0.0191
-8.750 -0.5311 0.01918 0.01248 -0.0874 0.7874 0.0202
-8.500 -0.5138 0.01859 0.01179 -0.0861 0.7847 0.0209
-8.250 -0.4962 0.01792 0.01104 -0.0849 0.7822 0.0217
-8.000 -0.4846 0.01685 0.00990 -0.0829 0.7799 0.0230
-7.750 -0.4673 0.01628 0.00928 -0.0817 0.7777 0.0240
-7.500 -0.4485 0.01575 0.00873 -0.0806 0.7755 0.0253
-7.250 -0.4279 0.01532 0.00825 -0.0798 0.7731 0.0267
-7.000 -0.4061 0.01496 0.00783 -0.0792 0.7708 0.0278
-6.750 -0.3887 0.01425 0.00706 -0.0779 0.7685 0.0302
-6.500 -0.3666 0.01385 0.00662 -0.0772 0.7665 0.0326
-6.250 -0.3431 0.01356 0.00626 -0.0768 0.7647 0.0356
-6.000 -0.3213 0.01312 0.00583 -0.0761 0.7629 0.0447
-5.750 -0.3036 0.01230 0.00533 -0.0750 0.7611 0.0977
-5.500 -0.2839 0.01163 0.00497 -0.0743 0.7592 0.1627
-5.250 -0.2625 0.01108 0.00468 -0.0738 0.7573 0.2236
-5.000 -0.2409 0.01052 0.00440 -0.0733 0.7554 0.2916
-4.750 -0.2188 0.00997 0.00412 -0.0729 0.7535 0.3657
-4.500 -0.1964 0.00943 0.00388 -0.0725 0.7518 0.4446
-4.250 -0.1728 0.00903 0.00373 -0.0721 0.7502 0.5180
-4.000 -0.1473 0.00888 0.00376 -0.0719 0.7488 0.5773
-3.750 -0.1200 0.00889 0.00382 -0.0720 0.7474 0.6117
-3.500 -0.0923 0.00897 0.00394 -0.0720 0.7458 0.6404
-3.250 -0.0643 0.00912 0.00408 -0.0721 0.7442 0.6609
-3.000 -0.0359 0.00923 0.00415 -0.0723 0.7426 0.6720
-2.750 -0.0074 0.00932 0.00423 -0.0725 0.7409 0.6799
-2.500 0.0213 0.00943 0.00427 -0.0728 0.7393 0.6891
-2.250 0.0499 0.00952 0.00436 -0.0730 0.7378 0.6951
-2.000 0.0788 0.00962 0.00441 -0.0734 0.7365 0.7019
-1.750 0.1077 0.00971 0.00447 -0.0737 0.7353 0.7072
-1.500 0.1366 0.00984 0.00459 -0.0740 0.7340 0.7124
-1.250 0.1651 0.00997 0.00467 -0.0744 0.7327 0.7181
-1.000 0.1931 0.01001 0.00475 -0.0746 0.7311 0.7223
-0.750 0.2212 0.01009 0.00485 -0.0748 0.7294 0.7266
-0.500 0.2496 0.01018 0.00493 -0.0751 0.7278 0.7313
-0.250 0.2781 0.01024 0.00498 -0.0755 0.7263 0.7355
0.000 0.3064 0.01029 0.00507 -0.0757 0.7248 0.7387
0.250 0.3349 0.01036 0.00514 -0.0760 0.7234 0.7423
0.500 0.3639 0.01042 0.00519 -0.0765 0.7219 0.7462
0.750 0.3931 0.01050 0.00524 -0.0770 0.7207 0.7499
1.000 0.4218 0.01057 0.00533 -0.0774 0.7195 0.7526
1.250 0.4502 0.01069 0.00549 -0.0777 0.7181 0.7554
1.500 0.4776 0.01076 0.00560 -0.0779 0.7164 0.7584
1.750 0.5054 0.01084 0.00571 -0.0782 0.7145 0.7614
2.000 0.5336 0.01092 0.00581 -0.0786 0.7126 0.7643
2.250 0.5617 0.01094 0.00588 -0.0789 0.7107 0.7665
2.500 0.5900 0.01097 0.00596 -0.0792 0.7088 0.7687
2.750 0.6190 0.01097 0.00599 -0.0796 0.7068 0.7710
3.000 0.6491 0.01097 0.00598 -0.0802 0.7046 0.7735
3.250 0.6760 0.01094 0.00600 -0.0802 0.7002 0.7761
3.500 0.7043 0.01074 0.00581 -0.0803 0.6944 0.7785
3.750 0.7359 0.01050 0.00552 -0.0810 0.6891 0.7807
4.000 0.7607 0.01034 0.00547 -0.0805 0.6826 0.7828
4.250 0.7896 0.01015 0.00530 -0.0807 0.6771 0.7849
4.500 0.8169 0.01006 0.00525 -0.0807 0.6714 0.7872
4.750 0.8435 0.00993 0.00518 -0.0805 0.6646 0.7899
5.000 0.8713 0.00981 0.00507 -0.0805 0.6579 0.7925
5.250 0.8966 0.00967 0.00499 -0.0802 0.6483 0.7948
5.500 0.9213 0.00957 0.00498 -0.0796 0.6382 0.7970
5.750 0.9462 0.00950 0.00497 -0.0791 0.6275 0.7995
6.000 0.9699 0.00947 0.00500 -0.0784 0.6130 0.8023
6.250 0.9914 0.00948 0.00502 -0.0772 0.5894 0.8053
6.500 1.0061 0.00970 0.00509 -0.0748 0.5414 0.8084
6.750 1.0014 0.01051 0.00551 -0.0688 0.4635 0.8118
7.000 0.9881 0.01142 0.00613 -0.0614 0.4027 0.8160
7.250 0.9756 0.01252 0.00696 -0.0546 0.3473 0.8211
7.500 0.9680 0.01367 0.00788 -0.0491 0.2978 0.8258
7.750 0.9618 0.01489 0.00889 -0.0442 0.2512 0.8304
8.000 0.9600 0.01612 0.00993 -0.0404 0.2093 0.8358
8.250 0.9615 0.01731 0.01096 -0.0372 0.1732 0.8412
8.500 0.9646 0.01847 0.01199 -0.0344 0.1412 0.8471
8.750 0.9705 0.01959 0.01301 -0.0320 0.1152 0.8539
9.000 0.9765 0.02067 0.01401 -0.0297 0.0935 0.8608
9.500 0.9942 0.02263 0.01592 -0.0259 0.0648 0.8791
9.750 1.0032 0.02356 0.01687 -0.0240 0.0560 0.8929
10.000 1.0137 0.02435 0.01775 -0.0222 0.0501 0.9182
10.250 1.0354 0.02534 0.01884 -0.0232 0.0445 1.0000
10.500 1.0503 0.02628 0.01978 -0.0226 0.0405 1.0000
10.750 1.0605 0.02754 0.02104 -0.0214 0.0366 1.0000
11.000 1.0773 0.02832 0.02186 -0.0209 0.0335 1.0000
11.250 1.0890 0.02948 0.02300 -0.0199 0.0301 1.0000
11.500 1.1002 0.03068 0.02424 -0.0189 0.0273 1.0000
11.750 1.1142 0.03168 0.02528 -0.0181 0.0245 1.0000
12.000 1.1220 0.03318 0.02678 -0.0169 0.0209 1.0000
12.250 1.1352 0.03429 0.02792 -0.0162 0.0185 1.0000
12.500 1.1389 0.03620 0.02984 -0.0148 0.0167 1.0000
12.750 1.1522 0.03733 0.03105 -0.0141 0.0152 1.0000
13.000 1.1631 0.03869 0.03242 -0.0134 0.0138 1.0000
13.250 1.1673 0.04065 0.03443 -0.0122 0.0131 1.0000
13.500 1.1741 0.04246 0.03632 -0.0113 0.0124 1.0000
13.750 1.1825 0.04414 0.03809 -0.0106 0.0119 1.0000
14.000 1.1903 0.04590 0.03993 -0.0099 0.0113 1.0000
14.250 1.1976 0.04776 0.04187 -0.0093 0.0109 1.0000
14.500 1.2036 0.04979 0.04397 -0.0087 0.0106 1.0000
14.750 1.2078 0.05203 0.04627 -0.0081 0.0102 1.0000
15.000 1.2078 0.05478 0.04910 -0.0074 0.0098 1.0000
15.250 1.2090 0.05750 0.05194 -0.0069 0.0095 1.0000
15.500 1.2130 0.05998 0.05453 -0.0065 0.0094 1.0000
15.750 1.2172 0.06249 0.05717 -0.0064 0.0092 1.0000
16.000 1.2202 0.06520 0.06000 -0.0063 0.0091 1.0000
16.250 1.2220 0.06811 0.06305 -0.0064 0.0089 1.0000
16.500 1.2225 0.07128 0.06636 -0.0065 0.0087 1.0000
16.750 1.2230 0.07453 0.06973 -0.0069 0.0086 1.0000
17.000 1.2211 0.07817 0.07351 -0.0075 0.0084 1.0000
17.250 1.2195 0.08187 0.07736 -0.0084 0.0082 1.0000
17.500 1.2172 0.08580 0.08141 -0.0095 0.0080 1.0000
17.750 1.2115 0.09034 0.08611 -0.0108 0.0079 1.0000
18.000 1.2073 0.09477 0.09065 -0.0124 0.0078 1.0000
18.250 1.2002 0.09978 0.09582 -0.0143 0.0078 1.0000
18.500 1.1911 0.10528 0.10147 -0.0166 0.0077 1.0000
18.750 1.1832 0.11076 0.10709 -0.0192 0.0076 1.0000
19.000 1.1737 0.11664 0.11311 -0.0221 0.0075 1.0000
19.250 1.1617 0.12318 0.11982 -0.0256 0.0075 1.0000
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