FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Reynolds number: 500,000 Max Cl/Cd: 119.66 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74modsm-il-500000-n5.txt Download as CSV file: xf-fx74modsm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-Cl5-140 MOD (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-8.750 0.2458 0.09248 0.08808 -0.1253 0.6000 0.0098
-8.500 0.2555 0.09013 0.08571 -0.1266 0.5950 0.0099
-8.250 0.2650 0.08782 0.08337 -0.1277 0.5903 0.0099
-8.000 0.2746 0.08546 0.08101 -0.1290 0.5862 0.0099
-7.750 0.2842 0.08310 0.07866 -0.1304 0.5821 0.0099
-7.500 0.2935 0.08078 0.07633 -0.1317 0.5780 0.0099
-7.250 0.3042 0.07833 0.07386 -0.1318 0.5740 0.0101
-7.000 0.3152 0.07632 0.07185 -0.1323 0.5701 0.0103
-6.750 0.3259 0.07437 0.06990 -0.1331 0.5658 0.0105
-6.500 0.3361 0.07244 0.06796 -0.1339 0.5617 0.0108
-6.000 0.3543 0.06867 0.06421 -0.1355 0.5547 0.0125
-5.750 0.3682 0.06637 0.06191 -0.1387 0.5514 0.0128
-5.500 0.3833 0.06399 0.05952 -0.1416 0.5479 0.0128
-5.250 0.3999 0.06150 0.05702 -0.1447 0.5445 0.0128
-5.000 0.4186 0.05889 0.05440 -0.1483 0.5413 0.0128
-4.750 0.4401 0.05608 0.05159 -0.1525 0.5379 0.0128
-4.500 0.4635 0.05320 0.04868 -0.1570 0.5342 0.0128
-4.250 0.4892 0.05018 0.04564 -0.1620 0.5306 0.0128
-4.000 0.5151 0.04735 0.04276 -0.1666 0.5273 0.0128
-3.750 0.5352 0.04546 0.04087 -0.1683 0.5243 0.0123
-3.500 0.5747 0.04182 0.03717 -0.1768 0.5209 0.0120
-3.250 0.6304 0.03699 0.03222 -0.1897 0.5171 0.0122
-3.000 0.6776 0.03394 0.02905 -0.1985 0.5133 0.0142
-2.750 0.7451 0.02910 0.02396 -0.2121 0.5098 0.0147
-2.500 0.8302 0.02284 0.01720 -0.2284 0.5064 0.0141
-2.250 0.8889 0.01954 0.01344 -0.2365 0.5028 0.0148
-2.000 0.9440 0.01658 0.00986 -0.2430 0.4992 0.0161
-1.500 1.0178 0.01458 0.00729 -0.2476 0.4926 0.0171
-1.250 1.0493 0.01418 0.00677 -0.2486 0.4893 0.0177
-1.000 1.0798 0.01390 0.00638 -0.2493 0.4861 0.0187
-0.750 1.1098 0.01366 0.00600 -0.2499 0.4828 0.0198
-0.500 1.1400 0.01341 0.00565 -0.2505 0.4797 0.0203
-0.250 1.1709 0.01316 0.00535 -0.2513 0.4766 0.0209
0.000 1.2008 0.01304 0.00521 -0.2520 0.4733 0.0219
0.250 1.2297 0.01300 0.00514 -0.2524 0.4703 0.0230
0.500 1.2578 0.01302 0.00511 -0.2526 0.4673 0.0249
0.750 1.2864 0.01303 0.00507 -0.2530 0.4645 0.0268
1.000 1.3150 0.01302 0.00507 -0.2533 0.4616 0.0294
1.250 1.3428 0.01307 0.00508 -0.2535 0.4583 0.0333
1.500 1.3702 0.01313 0.00512 -0.2535 0.4552 0.0420
1.750 1.4014 0.01296 0.00531 -0.2548 0.4524 0.2526
2.000 1.4320 0.01278 0.00567 -0.2560 0.4496 0.5563
2.250 1.4592 0.01276 0.00590 -0.2560 0.4470 0.6874
2.500 1.4841 0.01280 0.00610 -0.2555 0.4439 0.7818
2.750 1.5074 0.01282 0.00623 -0.2547 0.4409 0.8679
3.000 1.5295 0.01286 0.00629 -0.2536 0.4381 1.0000
3.250 1.5547 0.01308 0.00645 -0.2533 0.4355 1.0000
3.500 1.5804 0.01326 0.00662 -0.2531 0.4330 1.0000
3.750 1.6060 0.01343 0.00678 -0.2529 0.4302 1.0000
4.000 1.6310 0.01363 0.00695 -0.2526 0.4272 1.0000
4.250 1.6554 0.01385 0.00715 -0.2522 0.4242 1.0000
4.500 1.6792 0.01409 0.00736 -0.2516 0.4215 1.0000
4.750 1.7028 0.01433 0.00758 -0.2511 0.4191 1.0000
5.000 1.7272 0.01452 0.00779 -0.2507 0.4165 1.0000
5.250 1.7509 0.01474 0.00803 -0.2502 0.4136 1.0000
5.500 1.7737 0.01498 0.00827 -0.2495 0.4106 1.0000
5.750 1.7954 0.01525 0.00853 -0.2486 0.4079 1.0000
6.000 1.8156 0.01554 0.00882 -0.2474 0.4054 1.0000
6.250 1.8371 0.01579 0.00911 -0.2465 0.4030 1.0000
6.500 1.8585 0.01604 0.00939 -0.2456 0.4003 1.0000
6.750 1.8789 0.01632 0.00970 -0.2445 0.3973 1.0000
7.000 1.8982 0.01663 0.01004 -0.2432 0.3945 1.0000
7.250 1.9170 0.01698 0.01041 -0.2419 0.3920 1.0000
7.500 1.9349 0.01737 0.01081 -0.2404 0.3895 1.0000
7.750 1.9548 0.01767 0.01118 -0.2393 0.3869 1.0000
8.000 1.9738 0.01801 0.01158 -0.2380 0.3841 1.0000
8.250 1.9914 0.01841 0.01203 -0.2366 0.3812 1.0000
8.500 2.0081 0.01885 0.01251 -0.2350 0.3785 1.0000
8.750 2.0236 0.01936 0.01305 -0.2332 0.3759 1.0000
9.000 2.0404 0.01982 0.01357 -0.2317 0.3734 1.0000
9.250 2.0577 0.02027 0.01412 -0.2304 0.3705 1.0000
9.500 2.0722 0.02083 0.01474 -0.2286 0.3660 1.0000
9.750 2.0815 0.02165 0.01555 -0.2260 0.3589 1.0000
10.000 2.0920 0.02245 0.01639 -0.2238 0.3493 1.0000
10.250 2.1012 0.02338 0.01735 -0.2214 0.3418 1.0000
10.500 2.1089 0.02444 0.01844 -0.2190 0.3338 1.0000
10.750 2.1163 0.02559 0.01963 -0.2166 0.3255 1.0000
11.000 2.1192 0.02711 0.02116 -0.2138 0.3168 1.0000
11.250 2.1251 0.02850 0.02261 -0.2116 0.3077 1.0000
11.500 2.1250 0.03044 0.02456 -0.2089 0.2975 1.0000
11.750 2.1191 0.03299 0.02712 -0.2059 0.2835 1.0000
12.000 2.1085 0.03614 0.03025 -0.2029 0.2678 1.0000
12.250 2.0932 0.03996 0.03405 -0.1999 0.2513 1.0000
12.500 2.0740 0.04440 0.03847 -0.1970 0.2351 1.0000
12.750 2.0510 0.04944 0.04350 -0.1943 0.2192 1.0000
13.000 2.0267 0.05484 0.04890 -0.1918 0.2044 1.0000
13.250 1.9989 0.06084 0.05490 -0.1896 0.1887 1.0000
13.500 1.9726 0.06679 0.06087 -0.1876 0.1753 1.0000
13.750 1.9447 0.07315 0.06723 -0.1859 0.1610 1.0000
14.000 1.9169 0.07962 0.07372 -0.1845 0.1475 1.0000
14.250 1.8875 0.08643 0.08053 -0.1833 0.1325 1.0000
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Polar data table (+)
Polar graphs
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