FX S 03-182 AIRFOIL (fxs03182-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 03-182 AIRFOIL (fxs03182-il) Reynolds number: 200,000 Max Cl/Cd: 66.69 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs03182-il-200000-n5.txt Download as CSV file: xf-fxs03182-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX S 03-182 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4986 0.08776 0.08394 -0.0800 1.0000 0.0057
-14.000 -0.5255 0.07877 0.07478 -0.0848 1.0000 0.0057
-13.750 -0.5435 0.07046 0.06626 -0.0903 0.9902 0.0056
-13.500 -0.5495 0.06423 0.05980 -0.0957 0.9762 0.0056
-13.250 -0.5540 0.05847 0.05377 -0.1009 0.9615 0.0056
-13.000 -0.5505 0.05367 0.04868 -0.1060 0.9491 0.0055
-12.750 -0.5464 0.04885 0.04353 -0.1109 0.9358 0.0056
-12.500 -0.5380 0.04455 0.03889 -0.1154 0.9222 0.0056
-12.250 -0.5279 0.04070 0.03466 -0.1190 0.9078 0.0058
-12.000 -0.5081 0.03861 0.03232 -0.1218 0.8937 0.0057
-11.750 -0.4950 0.03636 0.02981 -0.1232 0.8794 0.0058
-11.500 -0.4813 0.03458 0.02780 -0.1239 0.8662 0.0058
-11.250 -0.4722 0.03272 0.02574 -0.1238 0.8542 0.0061
-11.000 -0.4589 0.03156 0.02440 -0.1235 0.8431 0.0060
-10.750 -0.4484 0.03023 0.02290 -0.1228 0.8332 0.0062
-10.500 -0.4369 0.02903 0.02153 -0.1220 0.8244 0.0064
-10.250 -0.4255 0.02800 0.02036 -0.1210 0.8152 0.0065
-10.000 -0.4137 0.02697 0.01919 -0.1199 0.8076 0.0068
-9.750 -0.4009 0.02612 0.01817 -0.1188 0.7998 0.0068
-9.500 -0.3877 0.02529 0.01721 -0.1177 0.7933 0.0069
-9.250 -0.3758 0.02440 0.01620 -0.1164 0.7868 0.0074
-8.750 -0.3490 0.02292 0.01452 -0.1140 0.7756 0.0082
-8.500 -0.3356 0.02223 0.01381 -0.1128 0.7703 0.0091
-8.250 -0.3215 0.02160 0.01318 -0.1116 0.7658 0.0105
-8.000 -0.3075 0.02103 0.01255 -0.1103 0.7606 0.0132
-7.750 -0.2938 0.02046 0.01185 -0.1088 0.7559 0.0156
-7.500 -0.2815 0.01991 0.01120 -0.1071 0.7518 0.0177
-7.250 -0.2698 0.01949 0.01070 -0.1052 0.7470 0.0195
-7.000 -0.2558 0.01910 0.01021 -0.1037 0.7428 0.0214
-6.750 -0.2417 0.01857 0.00970 -0.1024 0.7394 0.0266
-6.500 -0.2242 0.01820 0.00927 -0.1014 0.7360 0.0298
-6.250 -0.2052 0.01789 0.00890 -0.1005 0.7323 0.0350
-6.000 -0.1858 0.01755 0.00850 -0.0997 0.7290 0.0418
-5.750 -0.1668 0.01713 0.00810 -0.0990 0.7262 0.0509
-5.500 -0.1462 0.01673 0.00770 -0.0985 0.7237 0.0679
-5.250 -0.1280 0.01622 0.00732 -0.0978 0.7205 0.0998
-5.000 -0.1110 0.01548 0.00686 -0.0971 0.7172 0.1598
-4.750 -0.0973 0.01417 0.00616 -0.0965 0.7142 0.2990
-4.500 -0.0791 0.01312 0.00592 -0.0963 0.7116 0.4702
-4.250 -0.0515 0.01326 0.00617 -0.0962 0.7096 0.5358
-4.000 -0.0235 0.01341 0.00624 -0.0965 0.7072 0.5661
-3.750 0.0040 0.01372 0.00653 -0.0964 0.7046 0.5912
-3.500 0.0314 0.01414 0.00690 -0.0961 0.7023 0.6108
-3.250 0.0586 0.01457 0.00731 -0.0957 0.7001 0.6254
-3.000 0.0860 0.01488 0.00758 -0.0954 0.6982 0.6335
-2.750 0.1146 0.01495 0.00754 -0.0958 0.6964 0.6397
-2.250 0.1697 0.01512 0.00761 -0.0960 0.6924 0.6460
-2.000 0.1974 0.01509 0.00751 -0.0964 0.6900 0.6487
-1.750 0.2261 0.01502 0.00736 -0.0971 0.6878 0.6515
-1.500 0.2546 0.01500 0.00727 -0.0976 0.6860 0.6536
-1.250 0.2826 0.01504 0.00727 -0.0979 0.6843 0.6552
-1.000 0.3111 0.01506 0.00726 -0.0983 0.6827 0.6569
-0.750 0.3401 0.01508 0.00723 -0.0989 0.6813 0.6587
-0.500 0.3688 0.01511 0.00722 -0.0994 0.6799 0.6605
-0.250 0.3956 0.01514 0.00726 -0.0997 0.6776 0.6623
0.000 0.4232 0.01517 0.00727 -0.1002 0.6754 0.6642
0.250 0.4517 0.01520 0.00727 -0.1008 0.6735 0.6665
0.500 0.4800 0.01524 0.00731 -0.1013 0.6718 0.6682
0.750 0.5079 0.01530 0.00738 -0.1017 0.6702 0.6694
1.000 0.5364 0.01536 0.00745 -0.1021 0.6687 0.6706
1.250 0.5655 0.01541 0.00750 -0.1027 0.6672 0.6720
1.500 0.5951 0.01548 0.00755 -0.1034 0.6659 0.6735
1.750 0.6203 0.01562 0.00777 -0.1034 0.6638 0.6752
2.000 0.6464 0.01575 0.00796 -0.1035 0.6617 0.6773
2.250 0.6734 0.01587 0.00812 -0.1038 0.6595 0.6794
2.500 0.7013 0.01598 0.00826 -0.1043 0.6575 0.6814
2.750 0.7291 0.01609 0.00841 -0.1047 0.6559 0.6829
3.000 0.7571 0.01619 0.00857 -0.1051 0.6543 0.6842
3.250 0.7861 0.01628 0.00871 -0.1057 0.6527 0.6856
3.500 0.8150 0.01639 0.00887 -0.1062 0.6511 0.6872
3.750 0.8360 0.01660 0.00922 -0.1054 0.6471 0.6892
4.000 0.8616 0.01664 0.00934 -0.1053 0.6428 0.6914
4.250 0.8934 0.01633 0.00899 -0.1060 0.6361 0.6937
4.500 0.9152 0.01621 0.00894 -0.1050 0.6267 0.6960
4.750 0.9378 0.01595 0.00871 -0.1040 0.6149 0.6978
5.000 0.9599 0.01575 0.00857 -0.1029 0.6029 0.6995
5.250 0.9827 0.01564 0.00849 -0.1020 0.5921 0.7013
5.500 1.0029 0.01565 0.00858 -0.1007 0.5809 0.7035
5.750 1.0218 0.01574 0.00878 -0.0993 0.5700 0.7058
6.000 1.0403 0.01582 0.00893 -0.0979 0.5567 0.7085
6.500 1.0671 0.01600 0.00914 -0.0929 0.5068 0.7137
6.750 1.0603 0.01653 0.00931 -0.0867 0.4439 0.7163
7.000 1.0424 0.01791 0.01032 -0.0797 0.3849 0.7193
7.250 1.0250 0.01966 0.01177 -0.0736 0.3329 0.7225
7.500 1.0114 0.02160 0.01345 -0.0687 0.2852 0.7258
7.750 0.9992 0.02369 0.01532 -0.0645 0.2371 0.7283
8.000 0.9955 0.02549 0.01698 -0.0616 0.2010 0.7311
8.250 0.9966 0.02714 0.01852 -0.0593 0.1738 0.7342
8.500 0.9997 0.02876 0.02003 -0.0575 0.1458 0.7377
8.750 1.0032 0.03042 0.02160 -0.0558 0.1231 0.7412
9.000 1.0067 0.03206 0.02317 -0.0540 0.0967 0.7443
9.250 1.0121 0.03366 0.02469 -0.0526 0.0765 0.7481
9.500 1.0115 0.03579 0.02660 -0.0509 0.0468 0.7521
9.750 1.0216 0.03716 0.02798 -0.0500 0.0350 0.7563
10.000 1.0297 0.03866 0.02947 -0.0489 0.0295 0.7600
10.250 1.0416 0.03992 0.03079 -0.0482 0.0263 0.7643
10.500 1.0560 0.04103 0.03200 -0.0478 0.0238 0.7693
10.750 1.0695 0.04217 0.03330 -0.0472 0.0209 0.7737
11.000 1.0807 0.04355 0.03475 -0.0466 0.0176 0.7788
11.250 1.0913 0.04507 0.03630 -0.0461 0.0157 0.7845
11.500 1.1025 0.04648 0.03780 -0.0454 0.0147 0.7898
11.750 1.1131 0.04799 0.03939 -0.0449 0.0132 0.7962
12.000 1.1231 0.04958 0.04106 -0.0444 0.0118 0.8026
12.250 1.1331 0.05117 0.04275 -0.0438 0.0109 0.8100
12.500 1.1430 0.05278 0.04447 -0.0433 0.0104 0.8179
12.750 1.1525 0.05446 0.04627 -0.0428 0.0098 0.8271
13.000 1.1615 0.05613 0.04809 -0.0422 0.0094 0.8374
13.250 1.1714 0.05769 0.04979 -0.0417 0.0090 0.8497
13.500 1.1802 0.05927 0.05154 -0.0410 0.0087 0.8650
14.000 1.1885 0.06201 0.05469 -0.0379 0.0069 0.9892
14.250 1.1989 0.06406 0.05688 -0.0381 0.0056 1.0000
14.500 1.2068 0.06632 0.05921 -0.0383 0.0044 1.0000
14.750 1.2140 0.06867 0.06162 -0.0385 0.0040 1.0000
15.000 1.2200 0.07121 0.06422 -0.0387 0.0038 1.0000
15.250 1.2259 0.07380 0.06690 -0.0390 0.0037 1.0000
15.500 1.2307 0.07656 0.06978 -0.0394 0.0036 1.0000
15.750 1.2355 0.07936 0.07269 -0.0398 0.0035 1.0000
16.000 1.2391 0.08235 0.07580 -0.0403 0.0034 1.0000
16.250 1.2423 0.08547 0.07905 -0.0409 0.0034 1.0000
16.500 1.2445 0.08876 0.08247 -0.0416 0.0033 1.0000
16.750 1.2457 0.09225 0.08610 -0.0424 0.0033 1.0000
17.000 1.2462 0.09590 0.08989 -0.0434 0.0032 1.0000
17.250 1.2452 0.09984 0.09398 -0.0446 0.0032 1.0000
17.500 1.2439 0.10390 0.09819 -0.0460 0.0032 1.0000
17.750 1.2414 0.10825 0.10269 -0.0476 0.0031 1.0000
18.000 1.2376 0.11285 0.10745 -0.0494 0.0031 1.0000
18.250 1.2331 0.11768 0.11244 -0.0515 0.0030 1.0000
18.500 1.2277 0.12274 0.11766 -0.0538 0.0030 1.0000
18.750 1.2207 0.12820 0.12328 -0.0565 0.0030 1.0000
19.000 1.2135 0.13382 0.12906 -0.0595 0.0029 1.0000
19.250 1.2060 0.13964 0.13504 -0.0627 0.0029 1.0000
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Polar data table (+)
Polar graphs
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