FX S 03-182 AIRFOIL (fxs03182-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: FX S 03-182 AIRFOIL (fxs03182-il) Reynolds number: 200,000 Max Cl/Cd: 64.54 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxs03182-il-200000.txt Download as CSV file: xf-fxs03182-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3798 0.08724 0.08400 -0.0896 0.9842 0.0201
-12.250 -0.4017 0.07662 0.07323 -0.0989 0.9761 0.0196
-12.000 -0.4131 0.06907 0.06550 -0.1065 0.9691 0.0192
-11.750 -0.4281 0.06174 0.05793 -0.1131 0.9598 0.0186
-11.500 -0.4428 0.05423 0.05006 -0.1196 0.9518 0.0176
-11.250 -0.4756 0.04411 0.03901 -0.1248 0.9399 0.0158
-11.000 -0.4657 0.04077 0.03517 -0.1274 0.9272 0.0152
-10.750 -0.4542 0.03795 0.03198 -0.1286 0.9145 0.0151
-10.500 -0.4429 0.03523 0.02891 -0.1287 0.9025 0.0151
-10.250 -0.4270 0.03291 0.02626 -0.1284 0.8924 0.0151
-10.000 -0.4035 0.03026 0.02331 -0.1283 0.8847 0.0154
-9.750 -0.3803 0.02875 0.02162 -0.1278 0.8765 0.0156
-9.500 -0.3572 0.02750 0.02025 -0.1274 0.8694 0.0161
-9.250 -0.3407 0.02658 0.01926 -0.1263 0.8610 0.0172
-9.000 -0.3208 0.02571 0.01827 -0.1255 0.8545 0.0180
-8.750 -0.3056 0.02489 0.01737 -0.1240 0.8470 0.0192
-8.500 -0.2881 0.02427 0.01660 -0.1230 0.8407 0.0208
-8.250 -0.2804 0.02324 0.01560 -0.1209 0.8337 0.0238
-8.000 -0.2671 0.02256 0.01484 -0.1194 0.8276 0.0275
-7.750 -0.2612 0.02158 0.01383 -0.1170 0.8219 0.0318
-7.500 -0.2497 0.02104 0.01319 -0.1151 0.8160 0.0381
-7.250 -0.2468 0.02020 0.01231 -0.1124 0.8113 0.0428
-7.000 -0.2404 0.01980 0.01187 -0.1097 0.8061 0.0473
-6.750 -0.2297 0.01932 0.01140 -0.1079 0.8013 0.0554
-6.500 -0.2145 0.01886 0.01086 -0.1066 0.7977 0.0641
-6.250 -0.1998 0.01843 0.01041 -0.1053 0.7938 0.0759
-6.000 -0.1885 0.01789 0.01000 -0.1035 0.7891 0.1028
-5.750 -0.1796 0.01685 0.00937 -0.1019 0.7852 0.1789
-5.500 -0.1726 0.01520 0.00851 -0.1008 0.7823 0.3505
-5.250 -0.1568 0.01496 0.00915 -0.0991 0.7790 0.5278
-5.000 -0.1313 0.01541 0.00954 -0.0987 0.7755 0.5712
-4.750 -0.1043 0.01597 0.00999 -0.0984 0.7726 0.5963
-4.500 -0.0767 0.01663 0.01057 -0.0977 0.7703 0.6125
-4.250 -0.0483 0.01705 0.01087 -0.0976 0.7682 0.6246
-4.000 -0.0218 0.01778 0.01156 -0.0967 0.7660 0.6364
-3.750 -0.0004 0.01892 0.01279 -0.0941 0.7625 0.6474
-3.500 0.0227 0.02021 0.01412 -0.0913 0.7597 0.6596
-3.250 0.0471 0.02155 0.01548 -0.0885 0.7575 0.6719
-3.000 0.0724 0.02216 0.01603 -0.0873 0.7555 0.6834
-2.750 0.1001 0.02290 0.01673 -0.0857 0.7539 0.6873
-2.500 0.1258 0.02263 0.01631 -0.0868 0.7523 0.6969
-2.250 0.1418 0.02299 0.01673 -0.0846 0.7491 0.6989
-2.000 0.1621 0.02314 0.01686 -0.0834 0.7461 0.7012
-1.750 0.1857 0.02316 0.01683 -0.0831 0.7437 0.7043
-1.500 0.2122 0.02283 0.01639 -0.0847 0.7417 0.7106
-1.250 0.2376 0.02285 0.01637 -0.0845 0.7402 0.7132
-1.000 0.2640 0.02293 0.01641 -0.0843 0.7388 0.7154
-0.750 0.2818 0.02315 0.01665 -0.0833 0.7361 0.7179
-0.500 0.2965 0.02339 0.01691 -0.0822 0.7323 0.7211
-0.250 0.3218 0.02335 0.01681 -0.0835 0.7299 0.7249
0.000 0.3478 0.02335 0.01678 -0.0841 0.7280 0.7271
0.250 0.3743 0.02339 0.01681 -0.0841 0.7264 0.7288
0.500 0.4030 0.02339 0.01679 -0.0846 0.7249 0.7306
0.750 0.4330 0.02341 0.01679 -0.0855 0.7237 0.7328
1.000 0.4197 0.02486 0.01837 -0.0806 0.7168 0.7357
1.250 0.4457 0.02502 0.01851 -0.0815 0.7143 0.7385
1.500 0.4782 0.02503 0.01848 -0.0836 0.7126 0.7409
1.750 0.5080 0.02501 0.01847 -0.0843 0.7113 0.7421
2.000 0.5414 0.02490 0.01837 -0.0856 0.7102 0.7434
2.250 0.5082 0.02726 0.02086 -0.0775 0.6999 0.7458
2.500 0.5402 0.02721 0.02083 -0.0787 0.6982 0.7477
2.750 0.5767 0.02703 0.02066 -0.0806 0.6971 0.7496
3.000 0.6159 0.02678 0.02041 -0.0830 0.6962 0.7514
3.250 0.6564 0.02653 0.02017 -0.0856 0.6954 0.7533
3.500 0.5654 0.03165 0.02538 -0.0710 0.6770 0.7563
3.750 0.6180 0.03051 0.02429 -0.0742 0.6779 0.7578
4.000 0.6742 0.02949 0.02332 -0.0783 0.6787 0.7595
4.250 0.7319 0.02836 0.02225 -0.0827 0.6795 0.7612
4.500 0.6691 0.03230 0.02625 -0.0716 0.6635 0.7642
4.750 0.7258 0.03079 0.02480 -0.0754 0.6636 0.7661
5.000 0.8057 0.02790 0.02195 -0.0820 0.6611 0.7680
5.250 0.9517 0.02095 0.01477 -0.0969 0.6528 0.7692
5.500 0.9709 0.02072 0.01464 -0.0954 0.6440 0.7714
5.750 1.0113 0.01988 0.01381 -0.0972 0.6384 0.7735
6.000 1.0281 0.01985 0.01392 -0.0954 0.6305 0.7761
6.250 1.0683 0.01902 0.01309 -0.0973 0.6233 0.7788
6.500 1.0877 0.01862 0.01277 -0.0958 0.6112 0.7818
6.750 1.1103 0.01804 0.01221 -0.0947 0.5963 0.7848
7.000 1.1232 0.01784 0.01213 -0.0920 0.5831 0.7873
7.250 1.1361 0.01782 0.01223 -0.0894 0.5712 0.7902
7.500 1.1458 0.01780 0.01233 -0.0863 0.5571 0.7939
7.750 1.1527 0.01786 0.01240 -0.0829 0.5347 0.7984
8.000 1.1540 0.01807 0.01253 -0.0784 0.4924 0.8020
8.250 1.1471 0.01883 0.01292 -0.0730 0.4330 0.8061
8.500 1.1288 0.02058 0.01430 -0.0671 0.3775 0.8110
8.750 1.1141 0.02254 0.01601 -0.0623 0.3338 0.8154
9.000 1.0988 0.02473 0.01800 -0.0579 0.2911 0.8198
9.250 1.0912 0.02683 0.01994 -0.0549 0.2533 0.8250
9.500 1.0784 0.02942 0.02226 -0.0517 0.2093 0.8300
9.750 1.0765 0.03130 0.02405 -0.0494 0.1821 0.8352
10.000 1.0778 0.03320 0.02585 -0.0478 0.1552 0.8416
10.250 1.0788 0.03499 0.02756 -0.0460 0.1331 0.8476
10.500 1.0838 0.03664 0.02920 -0.0447 0.1137 0.8549
10.750 1.0884 0.03829 0.03082 -0.0434 0.0973 0.8620
11.000 1.0944 0.03995 0.03247 -0.0423 0.0844 0.8706
11.500 1.1064 0.04298 0.03555 -0.0397 0.0620 0.8915
11.750 1.1111 0.04447 0.03708 -0.0382 0.0539 0.9070
12.000 1.1127 0.04580 0.03849 -0.0360 0.0472 0.9381
12.250 1.1233 0.04721 0.03998 -0.0360 0.0416 1.0000
12.500 1.1359 0.04917 0.04195 -0.0367 0.0363 1.0000
12.750 1.1481 0.05110 0.04392 -0.0372 0.0335 1.0000
13.000 1.1582 0.05316 0.04602 -0.0374 0.0308 1.0000
13.250 1.1648 0.05554 0.04842 -0.0374 0.0276 1.0000
13.500 1.1754 0.05749 0.05049 -0.0376 0.0256 1.0000
13.750 1.1849 0.05957 0.05270 -0.0377 0.0232 1.0000
14.000 1.1927 0.06184 0.05506 -0.0377 0.0206 1.0000
14.250 1.1984 0.06434 0.05761 -0.0377 0.0185 1.0000
14.500 1.2040 0.06690 0.06026 -0.0378 0.0166 1.0000
14.750 1.2071 0.06978 0.06319 -0.0379 0.0153 1.0000
15.000 1.2031 0.07361 0.06711 -0.0380 0.0139 1.0000
15.250 1.2038 0.07694 0.07057 -0.0382 0.0132 1.0000
15.500 1.2041 0.08036 0.07413 -0.0385 0.0125 1.0000
15.750 1.2048 0.08378 0.07768 -0.0389 0.0120 1.0000
16.000 1.2054 0.08727 0.08132 -0.0394 0.0115 1.0000
16.250 1.2062 0.09077 0.08493 -0.0400 0.0111 1.0000
16.500 1.2068 0.09431 0.08858 -0.0407 0.0108 1.0000
16.750 1.2071 0.09794 0.09233 -0.0414 0.0105 1.0000
17.000 1.2070 0.10168 0.09617 -0.0423 0.0101 1.0000
17.250 1.2060 0.10553 0.10014 -0.0432 0.0098 1.0000
17.500 1.2047 0.10942 0.10417 -0.0440 0.0095 1.0000
17.750 1.2029 0.11366 0.10859 -0.0455 0.0093 1.0000
18.000 1.2008 0.11809 0.11321 -0.0474 0.0091 1.0000
18.250 1.1978 0.12273 0.11805 -0.0495 0.0089 1.0000
18.500 1.1934 0.12770 0.12322 -0.0519 0.0087 1.0000
18.750 1.1874 0.13306 0.12877 -0.0547 0.0085 1.0000
19.000 1.1805 0.13872 0.13462 -0.0578 0.0084 1.0000
19.250 1.1718 0.14484 0.14093 -0.0613 0.0084 1.0000
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Polar data table (+)
Polar graphs
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