FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Reynolds number: 200,000 Max Cl/Cd: 76.35 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74modsm-il-200000.txt Download as CSV file: xf-fx74modsm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 0.2475 0.09657 0.09213 -0.1279 0.7707 0.0214
-8.750 0.2575 0.09436 0.08983 -0.1286 0.7590 0.0218
-8.500 0.2675 0.09222 0.08761 -0.1294 0.7484 0.0224
-8.250 0.2772 0.09014 0.08549 -0.1302 0.7379 0.0232
-8.000 0.2875 0.08810 0.08337 -0.1313 0.7294 0.0242
-7.750 0.2972 0.08645 0.08170 -0.1329 0.7206 0.0252
-7.500 0.3049 0.08559 0.08079 -0.1357 0.7131 0.0256
-7.250 0.3116 0.08452 0.07973 -0.1383 0.7051 0.0257
-7.000 0.3193 0.08322 0.07837 -0.1405 0.6987 0.0258
-6.750 0.3355 0.07824 0.07337 -0.1383 0.6915 0.0262
-6.500 0.3484 0.07557 0.07063 -0.1382 0.6855 0.0268
-6.250 0.3591 0.07354 0.06860 -0.1386 0.6791 0.0274
-6.000 0.3685 0.07176 0.06681 -0.1391 0.6731 0.0280
-5.500 0.3945 0.06789 0.06289 -0.1424 0.6621 0.0297
-5.250 0.4111 0.06587 0.06084 -0.1455 0.6566 0.0309
-5.000 0.4452 0.06400 0.05888 -0.1573 0.6518 0.0322
-4.750 0.4804 0.06103 0.05592 -0.1679 0.6459 0.0325
-4.500 0.4798 0.05821 0.05310 -0.1618 0.6414 0.0332
-4.250 0.4947 0.05608 0.05090 -0.1613 0.6373 0.0342
-4.000 0.5153 0.05394 0.04878 -0.1639 0.6323 0.0357
-3.750 0.5995 0.04980 0.04440 -0.1892 0.6265 0.0410
-3.500 0.6133 0.04640 0.04098 -0.1890 0.6226 0.0421
-3.250 0.6279 0.04470 0.03929 -0.1879 0.6182 0.0436
-3.000 0.6594 0.04239 0.03694 -0.1923 0.6132 0.0463
-2.750 0.7512 0.03677 0.03084 -0.2142 0.6085 0.0535
-2.500 0.7733 0.03512 0.02917 -0.2147 0.6048 0.0561
-2.250 0.8403 0.03194 0.02556 -0.2267 0.5994 0.0673
-2.000 0.8625 0.03049 0.02422 -0.2270 0.5949 0.0730
-1.750 0.9128 0.02835 0.02174 -0.2338 0.5910 0.0867
-1.500 0.9540 0.02690 0.02009 -0.2382 0.5869 0.1029
-1.250 0.9900 0.02592 0.01898 -0.2410 0.5822 0.1250
-1.000 1.0250 0.02502 0.01796 -0.2436 0.5781 0.1586
-0.500 1.1232 0.02151 0.01317 -0.2506 0.5706 0.0752
-0.250 1.1566 0.02081 0.01219 -0.2512 0.5664 0.0626
0.000 1.1893 0.02022 0.01140 -0.2521 0.5627 0.0598
0.250 1.2213 0.01995 0.01097 -0.2529 0.5594 0.0626
0.500 1.2509 0.01977 0.01075 -0.2533 0.5557 0.0640
0.750 1.2791 0.01965 0.01065 -0.2535 0.5515 0.0659
1.000 1.3113 0.01943 0.01044 -0.2547 0.5478 0.0743
1.250 1.3434 0.01940 0.01031 -0.2557 0.5447 0.0962
1.500 1.3685 0.01841 0.01087 -0.2552 0.5419 0.8834
1.750 1.3899 0.01856 0.01103 -0.2540 0.5378 1.0000
2.000 1.4167 0.01885 0.01120 -0.2540 0.5339 1.0000
2.250 1.4450 0.01910 0.01131 -0.2543 0.5306 1.0000
2.500 1.4746 0.01941 0.01144 -0.2549 0.5278 1.0000
2.750 1.5003 0.01980 0.01180 -0.2548 0.5245 1.0000
3.000 1.5244 0.02015 0.01216 -0.2544 0.5206 1.0000
3.250 1.5505 0.02044 0.01240 -0.2543 0.5171 1.0000
3.500 1.5784 0.02071 0.01257 -0.2545 0.5140 1.0000
3.750 1.6080 0.02106 0.01277 -0.2551 0.5114 1.0000
4.000 1.6295 0.02150 0.01331 -0.2543 0.5079 1.0000
4.250 1.6527 0.02189 0.01373 -0.2537 0.5043 1.0000
4.500 1.6781 0.02220 0.01403 -0.2536 0.5010 1.0000
4.750 1.7057 0.02247 0.01422 -0.2538 0.4981 1.0000
5.000 1.7348 0.02287 0.01451 -0.2543 0.4955 1.0000
5.250 1.7532 0.02338 0.01520 -0.2530 0.4919 1.0000
5.500 1.7750 0.02382 0.01570 -0.2522 0.4884 1.0000
5.750 1.7995 0.02415 0.01604 -0.2519 0.4853 1.0000
6.000 1.8269 0.02443 0.01626 -0.2522 0.4826 1.0000
6.250 1.8552 0.02485 0.01664 -0.2526 0.4800 1.0000
6.500 1.8705 0.02546 0.01744 -0.2508 0.4764 1.0000
6.750 1.8903 0.02597 0.01804 -0.2497 0.4730 1.0000
7.000 1.9135 0.02634 0.01844 -0.2492 0.4699 1.0000
7.250 1.9407 0.02662 0.01871 -0.2494 0.4673 1.0000
7.500 1.9694 0.02705 0.01910 -0.2500 0.4647 1.0000
7.750 1.9800 0.02782 0.02010 -0.2474 0.4611 1.0000
8.000 1.9968 0.02843 0.02084 -0.2459 0.4578 1.0000
8.250 2.0179 0.02886 0.02134 -0.2451 0.4548 1.0000
8.500 2.0448 0.02913 0.02162 -0.2453 0.4521 1.0000
8.750 2.0750 0.02954 0.02199 -0.2462 0.4496 1.0000
9.000 2.0785 0.03054 0.02327 -0.2424 0.4460 1.0000
9.250 2.0903 0.03128 0.02418 -0.2401 0.4426 1.0000
9.500 2.1089 0.03176 0.02474 -0.2389 0.4395 1.0000
9.750 2.1362 0.03202 0.02502 -0.2392 0.4369 1.0000
10.000 2.1675 0.03243 0.02545 -0.2404 0.4344 1.0000
10.250 2.1579 0.03372 0.02704 -0.2345 0.4305 1.0000
10.500 2.1615 0.03433 0.02779 -0.2307 0.4261 1.0000
10.750 2.2005 0.03317 0.02644 -0.2324 0.4193 1.0000
11.000 2.1761 0.03457 0.02812 -0.2240 0.4152 1.0000
11.250 2.1736 0.03501 0.02865 -0.2193 0.4093 1.0000
11.500 2.1869 0.03496 0.02857 -0.2171 0.4031 1.0000
11.750 2.1685 0.03673 0.03057 -0.2108 0.3984 1.0000
12.000 2.1757 0.03701 0.03086 -0.2081 0.3918 1.0000
12.250 2.1659 0.03871 0.03271 -0.2036 0.3863 1.0000
12.500 2.1534 0.04070 0.03486 -0.1993 0.3801 1.0000
12.750 2.1557 0.04182 0.03599 -0.1968 0.3733 1.0000
13.000 2.1345 0.04511 0.03952 -0.1927 0.3672 1.0000
13.250 2.1305 0.04700 0.04141 -0.1901 0.3587 1.0000
13.500 2.1082 0.05115 0.04579 -0.1871 0.3523 1.0000
13.750 2.0993 0.05406 0.04876 -0.1850 0.3434 1.0000
14.000 2.0772 0.05882 0.05370 -0.1828 0.3352 1.0000
14.250 2.0567 0.06367 0.05866 -0.1811 0.3253 1.0000
14.500 2.0373 0.06857 0.06361 -0.1797 0.3139 1.0000
14.750 2.0160 0.07390 0.06898 -0.1784 0.3021 1.0000
15.000 1.9886 0.08039 0.07563 -0.1775 0.2917 1.0000
15.250 1.9617 0.08687 0.08215 -0.1768 0.2778 1.0000
15.500 1.9353 0.09341 0.08871 -0.1762 0.2631 1.0000
15.750 1.9093 0.09997 0.09524 -0.1759 0.2463 1.0000
16.000 1.8809 0.10703 0.10227 -0.1758 0.2267 1.0000
16.250 1.8536 0.11401 0.10916 -0.1761 0.2068 1.0000
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Polar data table (+)
Polar graphs
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