S9000 (9%) (s9000-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 200,000 Max Cl/Cd: 66.49 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9000-il-200000-n5.txt Download as CSV file: xf-s9000-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9000 (9%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4391 0.09161 0.08796 -0.0274 1.0000 0.0108
-9.000 -0.4391 0.08821 0.08459 -0.0283 1.0000 0.0106
-8.750 -0.4406 0.08450 0.08093 -0.0296 1.0000 0.0105
-8.500 -0.4437 0.08067 0.07716 -0.0308 1.0000 0.0103
-8.250 -0.4492 0.07674 0.07328 -0.0322 1.0000 0.0101
-8.000 -0.4595 0.07262 0.06925 -0.0334 1.0000 0.0100
-7.750 -0.4704 0.06832 0.06502 -0.0356 1.0000 0.0099
-7.500 -0.4774 0.06249 0.05920 -0.0403 1.0000 0.0096
-7.250 -0.4840 0.05604 0.05267 -0.0436 1.0000 0.0094
-7.000 -0.4886 0.04966 0.04612 -0.0453 1.0000 0.0091
-6.750 -0.4910 0.04303 0.03920 -0.0460 1.0000 0.0088
-6.500 -0.4925 0.03432 0.02979 -0.0461 1.0000 0.0083
-6.250 -0.4753 0.02867 0.02338 -0.0469 0.9986 0.0080
-6.000 -0.4436 0.02500 0.01910 -0.0493 0.9951 0.0081
-5.750 -0.4118 0.02247 0.01612 -0.0509 0.9915 0.0082
-5.500 -0.3791 0.02056 0.01385 -0.0524 0.9877 0.0086
-5.250 -0.3450 0.01895 0.01197 -0.0540 0.9844 0.0089
-5.000 -0.3133 0.01760 0.01038 -0.0549 0.9799 0.0096
-4.750 -0.2807 0.01645 0.00905 -0.0561 0.9751 0.0104
-4.500 -0.2458 0.01555 0.00806 -0.0578 0.9714 0.0124
-4.250 -0.2145 0.01497 0.00739 -0.0585 0.9650 0.0155
-4.000 -0.1804 0.01404 0.00638 -0.0600 0.9597 0.0195
-3.750 -0.1470 0.01336 0.00566 -0.0612 0.9538 0.0300
-3.500 -0.1142 0.01270 0.00507 -0.0623 0.9472 0.0496
-3.250 -0.0790 0.01209 0.00457 -0.0640 0.9423 0.0842
-3.000 -0.0480 0.01153 0.00420 -0.0648 0.9342 0.1388
-2.750 -0.0136 0.01096 0.00389 -0.0664 0.9280 0.2137
-2.500 0.0181 0.01044 0.00365 -0.0674 0.9187 0.3002
-2.250 0.0504 0.00994 0.00345 -0.0684 0.9093 0.3937
-2.000 0.0837 0.00945 0.00325 -0.0696 0.9002 0.4908
-1.750 0.1137 0.00902 0.00315 -0.0698 0.8887 0.5920
-1.500 0.1423 0.00875 0.00312 -0.0694 0.8763 0.6817
-1.250 0.1708 0.00861 0.00305 -0.0690 0.8631 0.7404
-1.000 0.1986 0.00852 0.00298 -0.0684 0.8487 0.7812
-0.750 0.2256 0.00847 0.00290 -0.0677 0.8327 0.8140
-0.500 0.2516 0.00844 0.00283 -0.0667 0.8159 0.8432
-0.250 0.2764 0.00843 0.00277 -0.0655 0.7983 0.8690
0.000 0.3017 0.00842 0.00271 -0.0644 0.7807 0.8934
0.250 0.3284 0.00843 0.00263 -0.0637 0.7625 0.9181
0.500 0.3585 0.00845 0.00256 -0.0638 0.7434 0.9421
0.750 0.3933 0.00848 0.00249 -0.0650 0.7216 0.9655
1.000 0.4302 0.00853 0.00242 -0.0668 0.6987 0.9925
1.250 0.4572 0.00866 0.00242 -0.0666 0.6761 1.0000
1.500 0.4825 0.00880 0.00244 -0.0661 0.6544 1.0000
1.750 0.5080 0.00896 0.00248 -0.0656 0.6322 1.0000
2.000 0.5334 0.00914 0.00254 -0.0651 0.6090 1.0000
2.250 0.5587 0.00934 0.00263 -0.0645 0.5844 1.0000
2.500 0.5839 0.00956 0.00272 -0.0640 0.5583 1.0000
2.750 0.6092 0.00978 0.00283 -0.0634 0.5324 1.0000
3.000 0.6345 0.01002 0.00296 -0.0630 0.5077 1.0000
3.250 0.6597 0.01027 0.00314 -0.0625 0.4836 1.0000
3.500 0.6849 0.01054 0.00331 -0.0620 0.4593 1.0000
3.750 0.7100 0.01082 0.00351 -0.0615 0.4340 1.0000
4.000 0.7349 0.01112 0.00374 -0.0610 0.4081 1.0000
4.250 0.7595 0.01146 0.00397 -0.0604 0.3804 1.0000
4.500 0.7840 0.01181 0.00423 -0.0599 0.3535 1.0000
4.750 0.8085 0.01217 0.00451 -0.0594 0.3288 1.0000
5.000 0.8331 0.01253 0.00484 -0.0589 0.3048 1.0000
5.250 0.8574 0.01293 0.00517 -0.0584 0.2815 1.0000
5.500 0.8816 0.01334 0.00552 -0.0579 0.2594 1.0000
5.750 0.9056 0.01377 0.00590 -0.0574 0.2355 1.0000
6.000 0.9292 0.01425 0.00633 -0.0568 0.2116 1.0000
6.250 0.9525 0.01477 0.00677 -0.0562 0.1892 1.0000
6.500 0.9761 0.01525 0.00724 -0.0556 0.1691 1.0000
6.750 0.9992 0.01578 0.00773 -0.0550 0.1509 1.0000
7.000 1.0222 0.01633 0.00829 -0.0544 0.1356 1.0000
7.250 1.0448 0.01690 0.00887 -0.0537 0.1212 1.0000
7.500 1.0670 0.01752 0.00948 -0.0530 0.1068 1.0000
7.750 1.0888 0.01816 0.01013 -0.0522 0.0933 1.0000
8.250 1.1310 0.01957 0.01158 -0.0505 0.0708 1.0000
8.500 1.1517 0.02028 0.01238 -0.0496 0.0616 1.0000
8.750 1.1714 0.02108 0.01322 -0.0486 0.0539 1.0000
9.000 1.1904 0.02192 0.01409 -0.0475 0.0468 1.0000
9.250 1.2096 0.02271 0.01500 -0.0464 0.0410 1.0000
9.500 1.2257 0.02377 0.01607 -0.0450 0.0353 1.0000
9.750 1.2436 0.02462 0.01707 -0.0438 0.0310 1.0000
10.000 1.2577 0.02577 0.01829 -0.0422 0.0271 1.0000
10.250 1.2710 0.02691 0.01961 -0.0404 0.0240 1.0000
10.500 1.2838 0.02798 0.02081 -0.0386 0.0210 1.0000
10.750 1.2900 0.02939 0.02228 -0.0361 0.0189 1.0000
11.000 1.2963 0.03079 0.02385 -0.0335 0.0175 1.0000
11.250 1.3020 0.03226 0.02549 -0.0312 0.0162 1.0000
11.500 1.3075 0.03375 0.02711 -0.0292 0.0149 1.0000
11.750 1.3101 0.03550 0.02897 -0.0272 0.0138 1.0000
12.000 1.3070 0.03786 0.03146 -0.0253 0.0129 1.0000
12.250 1.3076 0.04009 0.03389 -0.0239 0.0122 1.0000
12.500 1.3062 0.04265 0.03665 -0.0228 0.0116 1.0000
12.750 1.3045 0.04539 0.03957 -0.0223 0.0109 1.0000
13.000 1.3023 0.04835 0.04268 -0.0222 0.0102 1.0000
13.250 1.2974 0.05184 0.04633 -0.0227 0.0098 1.0000
13.500 1.2901 0.05590 0.05057 -0.0238 0.0093 1.0000
13.750 1.2783 0.06090 0.05572 -0.0255 0.0090 1.0000
14.000 1.2669 0.06619 0.06117 -0.0276 0.0088 1.0000
14.250 1.2573 0.07159 0.06681 -0.0301 0.0085 1.0000
14.500 1.2452 0.07763 0.07304 -0.0331 0.0084 1.0000
14.750 1.2315 0.08427 0.07988 -0.0366 0.0082 1.0000
15.000 1.2168 0.09138 0.08716 -0.0405 0.0082 1.0000
15.250 1.2012 0.09901 0.09497 -0.0448 0.0081 1.0000
15.500 1.1855 0.10695 0.10308 -0.0493 0.0081 1.0000
15.750 1.1694 0.11530 0.11158 -0.0541 0.0081 1.0000
16.000 1.1527 0.12402 0.12046 -0.0592 0.0082 1.0000
16.250 1.1364 0.13302 0.12959 -0.0645 0.0082 1.0000
16.500 1.1204 0.14224 0.13891 -0.0699 0.0083 1.0000
16.750 1.1041 0.15189 0.14867 -0.0756 0.0084 1.0000
17.000 1.0882 0.16178 0.15865 -0.0814 0.0086 1.0000
17.250 1.0708 0.17275 0.16971 -0.0879 0.0087 1.0000
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Polar data table (+)
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