FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX74_CL5_140 (fx74cl5140-il) Reynolds number: 1,000,000 Max Cl/Cd: 156.91 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74cl5140-il-1000000.txt Download as CSV file: xf-fx74cl5140-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX74_CL5_140
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 0.0698 0.13688 0.13385 -0.1025 0.6830 0.0036
-15.750 0.0754 0.13514 0.13193 -0.1032 0.6468 0.0036
-9.750 0.1999 0.09452 0.09035 -0.1285 0.5086 0.0047
-9.250 0.2187 0.08996 0.08580 -0.1303 0.5049 0.0050
-9.000 0.2281 0.08772 0.08356 -0.1312 0.5031 0.0052
-7.750 0.2741 0.07702 0.07286 -0.1349 0.4939 0.0055
-7.500 0.2833 0.07495 0.07081 -0.1356 0.4929 0.0055
-7.250 0.2919 0.07288 0.06875 -0.1361 0.4919 0.0055
-7.000 0.3005 0.07084 0.06674 -0.1367 0.4904 0.0055
-6.750 0.3083 0.06885 0.06476 -0.1370 0.4890 0.0055
-6.500 0.3151 0.06691 0.06285 -0.1372 0.4878 0.0056
-6.250 0.3198 0.06512 0.06107 -0.1368 0.4866 0.0056
-6.000 0.3251 0.06336 0.05934 -0.1370 0.4853 0.0057
-5.750 0.3353 0.06135 0.05732 -0.1381 0.4841 0.0056
-5.500 0.3470 0.05920 0.05518 -0.1398 0.4826 0.0056
-5.250 0.3608 0.05693 0.05291 -0.1422 0.4811 0.0057
-5.000 0.3779 0.05440 0.05038 -0.1458 0.4798 0.0057
-4.750 0.3977 0.05174 0.04773 -0.1497 0.4790 0.0057
-4.500 0.4227 0.04861 0.04460 -0.1553 0.4781 0.0057
-4.250 0.4510 0.04540 0.04136 -0.1613 0.4772 0.0057
-4.000 0.4824 0.04212 0.03804 -0.1672 0.4761 0.0057
-3.750 0.5179 0.03867 0.03452 -0.1735 0.4750 0.0057
-3.500 0.5550 0.03538 0.03114 -0.1794 0.4738 0.0058
-3.250 0.5954 0.03197 0.02761 -0.1853 0.4726 0.0058
-3.000 0.6384 0.02855 0.02402 -0.1911 0.4714 0.0058
-1.750 0.8546 0.01611 0.01031 -0.2141 0.4643 0.0089
-1.500 0.8904 0.01513 0.00918 -0.2163 0.4634 0.0097
-1.250 0.9228 0.01510 0.00889 -0.2168 0.4624 0.0114
-1.000 0.9606 0.01395 0.00748 -0.2192 0.4613 0.0118
-0.750 0.9943 0.01300 0.00653 -0.2209 0.4601 0.0127
-0.500 1.0262 0.01258 0.00602 -0.2219 0.4590 0.0140
-0.250 1.0545 0.01292 0.00619 -0.2217 0.4578 0.0156
0.000 1.0900 0.01179 0.00512 -0.2239 0.4567 0.0192
0.250 1.1228 0.01139 0.00472 -0.2252 0.4554 0.0262
1.000 1.2172 0.01115 0.00429 -0.2275 0.4501 0.0164
1.250 1.2490 0.01102 0.00413 -0.2284 0.4491 0.0125
1.500 1.2799 0.01096 0.00403 -0.2292 0.4480 0.0138
1.750 1.3093 0.01097 0.00402 -0.2297 0.4469 0.0181
2.000 1.3379 0.01102 0.00405 -0.2301 0.4457 0.0212
2.250 1.3834 0.01039 0.00464 -0.2348 0.4443 0.7573
2.500 1.4097 0.01049 0.00479 -0.2345 0.4430 0.7924
2.750 1.4372 0.01058 0.00487 -0.2347 0.4416 0.7985
3.000 1.4645 0.01069 0.00497 -0.2348 0.4403 0.8036
3.250 1.4918 0.01083 0.00511 -0.2350 0.4388 0.8063
3.500 1.5191 0.01104 0.00529 -0.2352 0.4370 0.8086
3.750 1.5466 0.01122 0.00546 -0.2354 0.4355 0.8111
4.000 1.5740 0.01129 0.00556 -0.2356 0.4347 0.8136
4.250 1.6013 0.01137 0.00570 -0.2357 0.4337 0.8163
4.500 1.6285 0.01146 0.00582 -0.2359 0.4324 0.8192
4.750 1.6556 0.01155 0.00594 -0.2361 0.4310 0.8221
5.000 1.6826 0.01165 0.00607 -0.2362 0.4294 0.8250
5.250 1.7095 0.01175 0.00620 -0.2364 0.4280 0.8283
5.500 1.7361 0.01186 0.00636 -0.2365 0.4265 0.8321
5.750 1.7626 0.01200 0.00653 -0.2366 0.4249 0.8366
6.000 1.7889 0.01219 0.00674 -0.2367 0.4229 0.8416
6.250 1.8153 0.01241 0.00701 -0.2368 0.4209 0.8481
6.500 1.8415 0.01244 0.00714 -0.2368 0.4195 0.8572
6.750 1.8673 0.01242 0.00723 -0.2368 0.4168 0.8735
7.000 1.8859 0.01232 0.00730 -0.2351 0.4144 1.0000
7.250 1.9117 0.01241 0.00743 -0.2351 0.4116 1.0000
7.500 1.9362 0.01255 0.00756 -0.2349 0.4062 1.0000
7.750 1.9625 0.01254 0.00764 -0.2350 0.4009 1.0000
8.000 1.9864 0.01270 0.00778 -0.2346 0.3938 1.0000
8.250 2.0116 0.01282 0.00796 -0.2346 0.3858 1.0000
8.500 2.0338 0.01311 0.00822 -0.2339 0.3718 1.0000
8.750 2.0481 0.01398 0.00886 -0.2320 0.3330 1.0000
9.000 2.0374 0.01649 0.01081 -0.2258 0.2555 1.0000
9.250 2.0095 0.01933 0.01322 -0.2166 0.1901 1.0000
9.500 1.9783 0.02248 0.01607 -0.2075 0.1381 1.0000
9.750 1.9485 0.02591 0.01932 -0.1999 0.0967 1.0000
10.000 1.9191 0.02990 0.02321 -0.1937 0.0650 1.0000
10.250 1.8901 0.03468 0.02795 -0.1891 0.0393 1.0000
10.500 1.8654 0.03997 0.03326 -0.1864 0.0214 1.0000
10.750 1.8473 0.04523 0.03860 -0.1850 0.0138 1.0000
11.000 1.8348 0.05021 0.04369 -0.1843 0.0110 1.0000
11.250 1.8244 0.05509 0.04870 -0.1839 0.0095 1.0000
11.500 1.8132 0.06017 0.05389 -0.1835 0.0087 1.0000
11.750 1.7979 0.06588 0.05972 -0.1832 0.0076 1.0000
12.000 1.7839 0.07149 0.06546 -0.1830 0.0068 1.0000
12.250 1.7773 0.07606 0.07012 -0.1830 0.0062 1.0000
12.500 1.7684 0.08107 0.07524 -0.1830 0.0058 1.0000
12.750 1.7594 0.08615 0.08040 -0.1831 0.0053 1.0000
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Polar data table (+)
Polar graphs
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