FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Reynolds number: 500,000 Max Cl/Cd: 118.67 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74modsm-il-500000.txt Download as CSV file: xf-fx74modsm-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.1617 0.11475 0.11146 -0.1184 0.7872 0.0103
-11.000 0.1698 0.11255 0.10914 -0.1189 0.7668 0.0104
-10.750 0.1783 0.11035 0.10684 -0.1195 0.7495 0.0105
-10.500 0.1871 0.10811 0.10451 -0.1203 0.7344 0.0106
-10.250 0.1961 0.10586 0.10219 -0.1211 0.7210 0.0108
-10.000 0.2053 0.10361 0.09987 -0.1219 0.7092 0.0110
-9.750 0.2145 0.10136 0.09755 -0.1228 0.6987 0.0112
-9.500 0.2241 0.09907 0.09522 -0.1237 0.6888 0.0114
-9.250 0.2338 0.09681 0.09291 -0.1247 0.6801 0.0117
-9.000 0.2435 0.09454 0.09059 -0.1256 0.6716 0.0120
-8.750 0.2535 0.09227 0.08829 -0.1267 0.6641 0.0123
-8.500 0.2638 0.09007 0.08605 -0.1280 0.6567 0.0126
-8.250 0.2733 0.08802 0.08397 -0.1296 0.6503 0.0127
-8.000 0.2823 0.08601 0.08196 -0.1314 0.6440 0.0128
-7.750 0.2903 0.08406 0.07998 -0.1332 0.6383 0.0128
-7.250 0.3123 0.07848 0.07437 -0.1340 0.6271 0.0131
-7.000 0.3231 0.07634 0.07218 -0.1343 0.6218 0.0133
-6.750 0.3341 0.07430 0.07014 -0.1351 0.6166 0.0136
-6.500 0.3446 0.07230 0.06814 -0.1359 0.6114 0.0139
-6.250 0.3545 0.07037 0.06617 -0.1366 0.6068 0.0143
-6.000 0.3636 0.06853 0.06434 -0.1373 0.6025 0.0148
-5.750 0.3761 0.06650 0.06232 -0.1390 0.5981 0.0157
-5.500 0.3948 0.06431 0.06012 -0.1443 0.5938 0.0162
-5.250 0.4164 0.06173 0.05749 -0.1501 0.5898 0.0163
-5.000 0.4399 0.05887 0.05464 -0.1553 0.5857 0.0163
-4.750 0.4567 0.05584 0.05161 -0.1576 0.5815 0.0165
-4.500 0.4695 0.05385 0.04959 -0.1571 0.5773 0.0167
-4.250 0.4889 0.05179 0.04747 -0.1592 0.5734 0.0171
-4.000 0.5135 0.04940 0.04510 -0.1632 0.5696 0.0176
-3.750 0.5433 0.04670 0.04237 -0.1687 0.5656 0.0184
-3.500 0.6286 0.04015 0.03562 -0.1923 0.5614 0.0205
-3.250 0.6566 0.03695 0.03234 -0.1965 0.5576 0.0211
-3.000 0.6854 0.03508 0.03046 -0.1995 0.5537 0.0218
-2.500 0.8180 0.02611 0.02090 -0.2247 0.5458 0.0266
-2.250 0.8546 0.02463 0.01928 -0.2284 0.5419 0.0279
-2.000 0.9063 0.02336 0.01757 -0.2335 0.5382 0.0323
-1.500 0.9870 0.01933 0.01323 -0.2419 0.5305 0.0381
-1.250 1.0302 0.01805 0.01151 -0.2455 0.5269 0.0430
-1.000 1.0635 0.01720 0.01061 -0.2473 0.5237 0.0459
-0.750 1.0911 0.01781 0.01105 -0.2467 0.5200 0.0522
-0.500 1.1308 0.01587 0.00897 -0.2503 0.5164 0.0593
-0.250 1.1688 0.01471 0.00739 -0.2515 0.5131 0.0381
0.000 1.2026 0.01403 0.00650 -0.2526 0.5100 0.0338
0.250 1.2333 0.01368 0.00614 -0.2533 0.5068 0.0342
0.500 1.2634 0.01348 0.00593 -0.2539 0.5034 0.0356
0.750 1.2924 0.01342 0.00583 -0.2544 0.5001 0.0384
1.000 1.3213 0.01346 0.00579 -0.2547 0.4968 0.0409
1.250 1.3520 0.01334 0.00565 -0.2555 0.4937 0.0469
1.500 1.3811 0.01331 0.00562 -0.2560 0.4906 0.0649
1.750 1.4167 0.01260 0.00617 -0.2584 0.4874 0.7157
2.000 1.4393 0.01258 0.00633 -0.2573 0.4844 0.8459
2.250 1.4614 0.01258 0.00635 -0.2562 0.4814 1.0000
2.500 1.4883 0.01276 0.00649 -0.2562 0.4784 1.0000
2.750 1.5149 0.01290 0.00661 -0.2561 0.4753 1.0000
3.000 1.5413 0.01307 0.00674 -0.2561 0.4724 1.0000
3.250 1.5674 0.01326 0.00688 -0.2559 0.4695 1.0000
3.500 1.5933 0.01351 0.00705 -0.2558 0.4665 1.0000
3.750 1.6191 0.01374 0.00725 -0.2557 0.4636 1.0000
4.000 1.6444 0.01389 0.00742 -0.2554 0.4606 1.0000
4.250 1.6696 0.01408 0.00761 -0.2551 0.4577 1.0000
4.500 1.6946 0.01428 0.00779 -0.2548 0.4549 1.0000
4.750 1.7193 0.01454 0.00800 -0.2545 0.4520 1.0000
5.000 1.7443 0.01483 0.00825 -0.2542 0.4491 1.0000
5.250 1.7681 0.01501 0.00849 -0.2537 0.4463 1.0000
5.500 1.7919 0.01521 0.00872 -0.2532 0.4434 1.0000
5.750 1.8155 0.01543 0.00895 -0.2527 0.4406 1.0000
6.000 1.8388 0.01570 0.00919 -0.2521 0.4378 1.0000
6.250 1.8629 0.01607 0.00952 -0.2518 0.4347 1.0000
6.500 1.8847 0.01627 0.00980 -0.2509 0.4322 1.0000
6.750 1.9066 0.01650 0.01009 -0.2501 0.4293 1.0000
7.000 1.9283 0.01676 0.01039 -0.2493 0.4265 1.0000
7.250 1.9494 0.01704 0.01069 -0.2483 0.4239 1.0000
7.500 1.9704 0.01739 0.01102 -0.2474 0.4210 1.0000
7.750 1.9902 0.01773 0.01140 -0.2463 0.4182 1.0000
8.000 2.0081 0.01800 0.01178 -0.2447 0.4155 1.0000
8.250 2.0261 0.01832 0.01215 -0.2432 0.4127 1.0000
8.500 2.0438 0.01865 0.01253 -0.2417 0.4100 1.0000
8.750 2.0621 0.01904 0.01293 -0.2403 0.4072 1.0000
9.000 2.0816 0.01950 0.01340 -0.2393 0.4042 1.0000
9.250 2.0951 0.01987 0.01391 -0.2370 0.4011 1.0000
9.500 2.1057 0.02028 0.01440 -0.2343 0.3959 1.0000
9.750 2.1159 0.02089 0.01495 -0.2317 0.3896 1.0000
10.000 2.1258 0.02140 0.01562 -0.2290 0.3840 1.0000
10.250 2.1369 0.02203 0.01630 -0.2267 0.3790 1.0000
10.500 2.1462 0.02281 0.01711 -0.2242 0.3736 1.0000
10.750 2.1574 0.02351 0.01793 -0.2221 0.3676 1.0000
11.000 2.1650 0.02447 0.01891 -0.2195 0.3620 1.0000
11.250 2.1741 0.02541 0.01996 -0.2174 0.3554 1.0000
11.500 2.1771 0.02678 0.02134 -0.2145 0.3468 1.0000
11.750 2.1814 0.02817 0.02281 -0.2120 0.3365 1.0000
12.000 2.1806 0.03006 0.02472 -0.2092 0.3246 1.0000
12.250 2.1731 0.03266 0.02731 -0.2060 0.3086 1.0000
12.500 2.1566 0.03626 0.03086 -0.2024 0.2897 1.0000
12.750 2.1357 0.04061 0.03516 -0.1991 0.2688 1.0000
13.000 2.1093 0.04580 0.04030 -0.1958 0.2484 1.0000
13.250 2.0797 0.05159 0.04606 -0.1929 0.2300 1.0000
13.500 2.0508 0.05756 0.05202 -0.1903 0.2129 1.0000
13.750 2.0188 0.06409 0.05854 -0.1881 0.1963 1.0000
14.000 1.9882 0.07065 0.06510 -0.1861 0.1814 1.0000
14.250 1.9569 0.07749 0.07194 -0.1845 0.1665 1.0000
14.500 1.9261 0.08439 0.07884 -0.1831 0.1522 1.0000
14.750 1.8972 0.09121 0.08565 -0.1821 0.1379 1.0000
15.000 1.8672 0.09832 0.09275 -0.1814 0.1219 1.0000
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