FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il) Reynolds number: 500,000 Max Cl/Cd: 87.22 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs21158-il-500000-n5.txt Download as CSV file: xf-fxs21158-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX S 02/1-158 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7333 0.05711 0.05431 -0.0588 1.0000 0.0024
-13.000 -0.7567 0.05056 0.04757 -0.0630 1.0000 0.0023
-12.750 -0.7744 0.04520 0.04202 -0.0661 1.0000 0.0023
-12.500 -0.7815 0.04146 0.03814 -0.0681 1.0000 0.0023
-12.250 -0.7323 0.03383 0.02994 -0.0871 0.9083 0.0025
-12.000 -0.7056 0.03104 0.02651 -0.0935 0.7963 0.0025
-11.750 -0.7072 0.02912 0.02428 -0.0928 0.7530 0.0026
-11.500 -0.7095 0.02753 0.02243 -0.0916 0.7220 0.0026
-11.250 -0.7025 0.02619 0.02086 -0.0908 0.6974 0.0026
-11.000 -0.6917 0.02496 0.01937 -0.0900 0.6770 0.0027
-10.750 -0.6776 0.02386 0.01808 -0.0893 0.6610 0.0028
-10.500 -0.6611 0.02289 0.01694 -0.0887 0.6452 0.0028
-10.250 -0.6440 0.02186 0.01573 -0.0881 0.6298 0.0031
-10.000 -0.6259 0.02087 0.01456 -0.0876 0.6163 0.0034
-9.750 -0.6062 0.02003 0.01356 -0.0871 0.6049 0.0036
-9.500 -0.5856 0.01920 0.01260 -0.0867 0.5941 0.0040
-9.250 -0.5638 0.01847 0.01178 -0.0864 0.5837 0.0046
-9.000 -0.5389 0.01821 0.01155 -0.0864 0.5732 0.0066
-8.750 -0.5126 0.01817 0.01148 -0.0864 0.5632 0.0103
-8.500 -0.4869 0.01796 0.01118 -0.0863 0.5549 0.0122
-8.250 -0.4612 0.01775 0.01086 -0.0862 0.5479 0.0137
-8.000 -0.4349 0.01757 0.01060 -0.0862 0.5415 0.0146
-7.750 -0.4070 0.01773 0.01067 -0.0863 0.5355 0.0153
-7.500 -0.3836 0.01695 0.00981 -0.0862 0.5305 0.0165
-7.250 -0.3580 0.01659 0.00938 -0.0862 0.5247 0.0173
-7.000 -0.3324 0.01621 0.00892 -0.0861 0.5190 0.0179
-6.750 -0.3063 0.01582 0.00846 -0.0861 0.5132 0.0184
-6.500 -0.2803 0.01542 0.00798 -0.0861 0.5079 0.0189
-6.250 -0.2539 0.01506 0.00754 -0.0861 0.5036 0.0195
-6.000 -0.2271 0.01475 0.00717 -0.0862 0.4998 0.0204
-5.750 -0.1997 0.01460 0.00695 -0.0863 0.4962 0.0216
-5.500 -0.1725 0.01439 0.00667 -0.0863 0.4931 0.0223
-5.250 -0.1456 0.01403 0.00623 -0.0864 0.4903 0.0224
-5.000 -0.1184 0.01366 0.00580 -0.0865 0.4876 0.0226
-4.750 -0.0913 0.01322 0.00528 -0.0866 0.4848 0.0229
-4.500 -0.0639 0.01283 0.00480 -0.0868 0.4821 0.0234
-4.250 -0.0362 0.01252 0.00439 -0.0870 0.4796 0.0242
-4.000 -0.0084 0.01228 0.00408 -0.0871 0.4774 0.0250
-3.750 0.0199 0.01206 0.00381 -0.0873 0.4753 0.0257
-3.500 0.0482 0.01187 0.00358 -0.0875 0.4724 0.0265
-3.250 0.0765 0.01172 0.00336 -0.0876 0.4692 0.0277
-3.000 0.1048 0.01160 0.00318 -0.0877 0.4658 0.0296
-2.750 0.1329 0.01148 0.00301 -0.0879 0.4630 0.0353
-2.500 0.1614 0.01125 0.00285 -0.0881 0.4603 0.0608
-2.250 0.1900 0.01112 0.00271 -0.0883 0.4575 0.0743
-2.000 0.2184 0.01093 0.00258 -0.0886 0.4551 0.1091
-1.750 0.2465 0.01052 0.00238 -0.0890 0.4526 0.1946
-1.500 0.2733 0.00966 0.00220 -0.0897 0.4504 0.4068
-1.250 0.3017 0.00969 0.00222 -0.0898 0.4481 0.4288
-1.000 0.3306 0.00971 0.00222 -0.0900 0.4459 0.4383
-0.750 0.3593 0.00973 0.00224 -0.0901 0.4433 0.4486
-0.500 0.3879 0.00979 0.00230 -0.0902 0.4406 0.4626
-0.250 0.4165 0.00984 0.00232 -0.0904 0.4375 0.4707
0.000 0.4448 0.00990 0.00233 -0.0904 0.4337 0.4748
0.250 0.4734 0.00992 0.00234 -0.0906 0.4300 0.4780
0.500 0.5019 0.00996 0.00235 -0.0907 0.4258 0.4809
0.750 0.5302 0.01002 0.00236 -0.0908 0.4224 0.4834
1.000 0.5584 0.01007 0.00240 -0.0909 0.4191 0.4861
1.250 0.5869 0.01011 0.00245 -0.0910 0.4165 0.4890
1.500 0.6152 0.01016 0.00249 -0.0912 0.4135 0.4917
1.750 0.6435 0.01022 0.00255 -0.0913 0.4107 0.4943
2.000 0.6716 0.01029 0.00260 -0.0914 0.4083 0.4965
2.250 0.6995 0.01037 0.00266 -0.0915 0.4058 0.4984
2.500 0.7278 0.01041 0.00274 -0.0916 0.4018 0.5007
2.750 0.7557 0.01047 0.00281 -0.0917 0.3948 0.5044
3.000 0.7835 0.01055 0.00288 -0.0917 0.3874 0.5084
3.250 0.8113 0.01063 0.00296 -0.0918 0.3793 0.5119
3.500 0.8390 0.01071 0.00306 -0.0919 0.3739 0.5146
3.750 0.8665 0.01080 0.00316 -0.0919 0.3665 0.5168
4.000 0.8938 0.01091 0.00327 -0.0919 0.3602 0.5195
4.250 0.9209 0.01103 0.00341 -0.0919 0.3534 0.5224
4.500 0.9478 0.01118 0.00355 -0.0918 0.3474 0.5262
4.750 0.9749 0.01130 0.00371 -0.0918 0.3410 0.5296
5.000 1.0013 0.01148 0.00389 -0.0917 0.3332 0.5330
5.250 1.0263 0.01177 0.00413 -0.0914 0.3065 0.5362
5.500 1.0341 0.01367 0.00539 -0.0890 0.1874 0.5386
5.750 1.0483 0.01489 0.00630 -0.0873 0.1261 0.5410
6.000 1.0667 0.01566 0.00695 -0.0862 0.0902 0.5435
6.250 1.0886 0.01610 0.00738 -0.0855 0.0788 0.5465
6.500 1.1078 0.01673 0.00795 -0.0844 0.0556 0.5498
6.750 1.1296 0.01713 0.00837 -0.0837 0.0485 0.5534
7.000 1.1473 0.01778 0.00901 -0.0825 0.0304 0.5567
7.250 1.1670 0.01823 0.00951 -0.0815 0.0274 0.5606
7.500 1.1856 0.01873 0.01005 -0.0803 0.0232 0.5649
7.750 1.2048 0.01915 0.01053 -0.0792 0.0211 0.5698
8.000 1.2130 0.02007 0.01142 -0.0767 0.0047 0.5744
8.250 1.2221 0.02070 0.01212 -0.0740 0.0040 0.5800
8.750 1.2373 0.02225 0.01385 -0.0689 0.0030 0.5924
9.000 1.2424 0.02327 0.01496 -0.0665 0.0027 0.5996
9.250 1.2462 0.02450 0.01631 -0.0644 0.0026 0.6077
9.500 1.2486 0.02603 0.01795 -0.0627 0.0024 0.6171
9.750 1.2508 0.02781 0.01986 -0.0614 0.0024 0.6280
10.000 1.2532 0.02979 0.02197 -0.0605 0.0023 0.6414
10.250 1.2533 0.03215 0.02448 -0.0597 0.0022 0.6584
10.500 1.2543 0.03452 0.02701 -0.0592 0.0022 0.6833
10.750 1.2541 0.03696 0.02967 -0.0586 0.0021 0.7282
11.250 1.2585 0.04260 0.03592 -0.0599 0.0019 1.0000
11.500 1.2601 0.04522 0.03863 -0.0597 0.0020 1.0000
11.750 1.2563 0.04843 0.04193 -0.0596 0.0019 1.0000
12.000 1.2521 0.05171 0.04531 -0.0595 0.0018 1.0000
12.250 1.2485 0.05498 0.04865 -0.0595 0.0018 1.0000
12.500 1.2489 0.05789 0.05164 -0.0596 0.0018 1.0000
12.750 1.2492 0.06092 0.05474 -0.0598 0.0017 1.0000
13.000 1.2505 0.06388 0.05777 -0.0601 0.0017 1.0000
13.250 1.2506 0.06706 0.06102 -0.0605 0.0017 1.0000
13.500 1.2523 0.07008 0.06411 -0.0608 0.0017 1.0000
13.750 1.2524 0.07340 0.06751 -0.0613 0.0016 1.0000
14.000 1.2536 0.07659 0.07077 -0.0618 0.0016 1.0000
14.250 1.2541 0.07996 0.07422 -0.0625 0.0016 1.0000
14.500 1.2556 0.08323 0.07756 -0.0631 0.0016 1.0000
14.750 1.2554 0.08680 0.08121 -0.0639 0.0015 1.0000
15.000 1.2572 0.09011 0.08459 -0.0646 0.0015 1.0000
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