WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 74-080 (fx74080-il) Reynolds number: 1,000,000 Max Cl/Cd: 164.5 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74080-il-1000000-n5.txt Download as CSV file: xf-fx74080-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 74-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1667 0.08302 0.08050 -0.0892 0.8143 0.0032
-8.250 -0.1560 0.07975 0.07723 -0.0920 0.8123 0.0032
-8.000 -0.1500 0.07549 0.07297 -0.0949 0.8102 0.0029
-7.750 -0.1413 0.07148 0.06896 -0.0986 0.8081 0.0027
-7.500 -0.1313 0.06785 0.06533 -0.1024 0.8063 0.0026
-7.250 -0.1207 0.06431 0.06180 -0.1069 0.8044 0.0026
-7.000 -0.1070 0.05974 0.05723 -0.1133 0.8022 0.0025
-6.750 -0.0917 0.05507 0.05253 -0.1192 0.8000 0.0024
-6.500 -0.0746 0.05112 0.04853 -0.1238 0.7981 0.0023
-6.250 -0.0571 0.04620 0.04352 -0.1284 0.7959 0.0023
-6.000 -0.0386 0.04147 0.03866 -0.1319 0.7935 0.0023
-5.750 -0.0200 0.03670 0.03376 -0.1341 0.7908 0.0023
-5.500 -0.0010 0.03121 0.02804 -0.1354 0.7882 0.0026
-5.000 0.0398 0.02253 0.01881 -0.1353 0.7840 0.0038
-4.750 0.0636 0.02194 0.01812 -0.1356 0.7824 0.0043
-4.250 0.1116 0.01878 0.01457 -0.1352 0.7793 0.0059
-4.000 0.1354 0.01637 0.01189 -0.1345 0.7776 0.0060
-3.750 0.1593 0.01384 0.00900 -0.1337 0.7759 0.0057
-3.500 0.1839 0.01160 0.00642 -0.1328 0.7742 0.0053
-3.250 0.2088 0.01002 0.00459 -0.1321 0.7726 0.0051
-3.000 0.2336 0.00897 0.00337 -0.1314 0.7708 0.0050
-2.750 0.2588 0.00832 0.00258 -0.1309 0.7691 0.0051
-2.250 0.3110 0.00759 0.00168 -0.1304 0.7659 0.0074
-2.000 0.3379 0.00750 0.00159 -0.1304 0.7640 0.0092
-1.750 0.3643 0.00727 0.00129 -0.1302 0.7619 0.0114
-1.500 0.3911 0.00712 0.00109 -0.1300 0.7599 0.0138
-1.250 0.4179 0.00701 0.00100 -0.1299 0.7578 0.0229
-1.000 0.4445 0.00690 0.00093 -0.1299 0.7559 0.0454
-0.750 0.4711 0.00678 0.00089 -0.1298 0.7540 0.0812
-0.500 0.4930 0.00606 0.00091 -0.1292 0.7519 0.3611
-0.250 0.5172 0.00574 0.00091 -0.1288 0.7495 0.4885
0.000 0.5386 0.00529 0.00093 -0.1277 0.7469 0.6673
0.250 0.5568 0.00497 0.00106 -0.1255 0.7443 0.8434
0.500 0.5815 0.00494 0.00108 -0.1249 0.7419 0.8728
0.750 0.6064 0.00491 0.00111 -0.1242 0.7392 0.8960
1.000 0.6316 0.00487 0.00115 -0.1237 0.7360 0.9159
1.250 0.6581 0.00486 0.00116 -0.1235 0.7326 0.9282
1.500 0.6855 0.00486 0.00117 -0.1236 0.7294 0.9358
1.750 0.7137 0.00487 0.00121 -0.1238 0.7261 0.9441
2.000 0.7444 0.00487 0.00125 -0.1247 0.7218 0.9535
2.250 0.7773 0.00488 0.00131 -0.1261 0.7140 0.9634
2.500 0.8110 0.00493 0.00132 -0.1276 0.6903 0.9740
2.750 0.8427 0.00518 0.00138 -0.1288 0.6420 0.9932
3.250 0.8646 0.00649 0.00195 -0.1221 0.4786 1.0000
3.500 0.8610 0.00811 0.00268 -0.1162 0.2905 1.0000
3.750 0.8539 0.01009 0.00359 -0.1099 0.0522 1.0000
4.000 0.8727 0.01059 0.00393 -0.1083 0.0157 1.0000
4.250 0.8948 0.01087 0.00421 -0.1074 0.0087 1.0000
4.500 0.9157 0.01124 0.00461 -0.1062 0.0037 1.0000
4.750 0.9371 0.01158 0.00498 -0.1052 0.0028 1.0000
5.000 0.9573 0.01199 0.00546 -0.1038 0.0025 1.0000
5.250 0.9746 0.01260 0.00617 -0.1018 0.0022 1.0000
5.500 0.9909 0.01324 0.00691 -0.0997 0.0022 1.0000
5.750 1.0028 0.01407 0.00785 -0.0967 0.0022 1.0000
6.000 1.0138 0.01502 0.00892 -0.0936 0.0022 1.0000
6.250 1.0250 0.01616 0.01016 -0.0906 0.0022 1.0000
6.500 1.0378 0.01763 0.01174 -0.0879 0.0022 1.0000
6.750 1.0597 0.01945 0.01368 -0.0869 0.0023 1.0000
7.000 1.0975 0.02227 0.01669 -0.0886 0.0025 1.0000
7.250 1.1305 0.02546 0.02018 -0.0892 0.0027 1.0000
7.500 1.1549 0.02866 0.02367 -0.0883 0.0028 1.0000
7.750 1.1746 0.03136 0.02660 -0.0866 0.0027 1.0000
8.000 1.1925 0.03287 0.02827 -0.0852 0.0022 1.0000
8.250 1.2060 0.03604 0.03171 -0.0826 0.0022 1.0000
8.500 1.2164 0.03922 0.03516 -0.0796 0.0021 1.0000
8.750 1.2267 0.04101 0.03711 -0.0774 0.0019 1.0000
9.000 1.2296 0.04497 0.04135 -0.0735 0.0019 1.0000
9.250 1.2357 0.04639 0.04290 -0.0710 0.0017 1.0000
9.500 1.2333 0.05006 0.04681 -0.0669 0.0017 1.0000
9.750 1.2308 0.05235 0.04927 -0.0633 0.0016 1.0000
10.000 1.2255 0.05402 0.05106 -0.0595 0.0015 1.0000
10.250 1.2158 0.05616 0.05334 -0.0554 0.0014 1.0000
10.500 1.2014 0.05900 0.05634 -0.0513 0.0014 1.0000
10.750 1.1852 0.06191 0.05939 -0.0478 0.0014 1.0000
11.000 1.1678 0.06603 0.06368 -0.0446 0.0014 1.0000
11.250 1.1489 0.06915 0.06693 -0.0426 0.0013 1.0000
11.500 1.1300 0.07381 0.07173 -0.0407 0.0014 1.0000
11.750 1.1084 0.07815 0.07620 -0.0400 0.0013 1.0000
12.000 1.0878 0.08405 0.08223 -0.0397 0.0014 1.0000
12.250 1.0679 0.08902 0.08730 -0.0408 0.0013 1.0000
12.500 1.0428 0.09580 0.09419 -0.0434 0.0013 1.0000
12.750 1.0234 0.10379 0.10229 -0.0467 0.0014 1.0000
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Polar data table (+)
Polar graphs
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