FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il) Reynolds number: 500,000 Max Cl/Cd: 117.86 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63137sm-il-500000-n5.txt Download as CSV file: xf-fx63137sm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-137 13.7% 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1537 0.10494 0.10243 -0.0787 0.9639 0.0110
-10.000 -0.2865 0.03068 0.02710 -0.1546 0.9013 0.0115
-9.750 -0.2470 0.02597 0.02196 -0.1688 0.8871 0.0117
-9.250 -0.1883 0.02136 0.01669 -0.1792 0.8623 0.0123
-9.000 -0.1609 0.01992 0.01497 -0.1815 0.8525 0.0126
-8.750 -0.1335 0.01873 0.01353 -0.1831 0.8430 0.0130
-8.500 -0.1056 0.01787 0.01245 -0.1843 0.8349 0.0133
-8.250 -0.0783 0.01687 0.01130 -0.1855 0.8266 0.0137
-8.000 -0.0500 0.01619 0.01053 -0.1865 0.8194 0.0140
-7.750 -0.0219 0.01558 0.00982 -0.1872 0.8119 0.0143
-7.500 0.0072 0.01502 0.00914 -0.1881 0.8053 0.0146
-7.250 0.0358 0.01446 0.00849 -0.1888 0.7983 0.0150
-7.000 0.0651 0.01393 0.00785 -0.1895 0.7916 0.0155
-6.750 0.0948 0.01345 0.00726 -0.1903 0.7855 0.0159
-6.500 0.1244 0.01301 0.00673 -0.1910 0.7788 0.0163
-6.250 0.1549 0.01252 0.00617 -0.1920 0.7727 0.0168
-6.000 0.1851 0.01217 0.00578 -0.1928 0.7667 0.0174
-5.750 0.2151 0.01188 0.00544 -0.1935 0.7602 0.0183
-5.250 0.2763 0.01129 0.00471 -0.1950 0.7483 0.0201
-5.000 0.3071 0.01100 0.00438 -0.1958 0.7420 0.0211
-4.750 0.3377 0.01080 0.00411 -0.1965 0.7362 0.0224
-4.500 0.3683 0.01058 0.00384 -0.1972 0.7300 0.0239
-4.250 0.3989 0.01038 0.00361 -0.1978 0.7238 0.0262
-4.000 0.4294 0.01022 0.00341 -0.1984 0.7180 0.0296
-3.750 0.4600 0.01005 0.00323 -0.1991 0.7117 0.0346
-3.500 0.4905 0.00990 0.00306 -0.1997 0.7054 0.0432
-3.250 0.5214 0.00973 0.00293 -0.2004 0.6994 0.0609
-3.000 0.5527 0.00953 0.00281 -0.2013 0.6929 0.0914
-2.750 0.5840 0.00934 0.00269 -0.2023 0.6866 0.1339
-2.500 0.6171 0.00903 0.00259 -0.2037 0.6803 0.2100
-2.250 0.6499 0.00876 0.00254 -0.2051 0.6735 0.3037
-2.000 0.6805 0.00867 0.00256 -0.2058 0.6674 0.3630
-1.750 0.7102 0.00865 0.00259 -0.2061 0.6604 0.3977
-1.500 0.7390 0.00870 0.00260 -0.2062 0.6537 0.4153
-1.250 0.7679 0.00873 0.00263 -0.2064 0.6470 0.4297
-1.000 0.7966 0.00878 0.00267 -0.2065 0.6398 0.4465
-0.750 0.8251 0.00884 0.00272 -0.2066 0.6329 0.4664
-0.500 0.8536 0.00890 0.00276 -0.2066 0.6255 0.4771
-0.250 0.8815 0.00899 0.00281 -0.2066 0.6183 0.4857
0.000 0.9099 0.00905 0.00286 -0.2066 0.6107 0.4935
0.250 0.9376 0.00915 0.00292 -0.2065 0.6029 0.5012
0.500 0.9657 0.00923 0.00298 -0.2065 0.5951 0.5091
0.750 0.9932 0.00933 0.00306 -0.2064 0.5868 0.5164
1.000 1.0210 0.00943 0.00314 -0.2063 0.5786 0.5246
1.250 1.0481 0.00955 0.00324 -0.2061 0.5700 0.5319
1.500 1.0757 0.00966 0.00334 -0.2060 0.5614 0.5397
2.000 1.1298 0.00992 0.00357 -0.2057 0.5433 0.5556
2.500 1.1833 0.01021 0.00384 -0.2052 0.5246 0.5715
2.750 1.2096 0.01038 0.00399 -0.2049 0.5153 0.5803
3.000 1.2359 0.01055 0.00415 -0.2046 0.5052 0.5885
3.250 1.2621 0.01072 0.00432 -0.2043 0.4956 0.5970
3.500 1.2876 0.01093 0.00451 -0.2038 0.4856 0.6057
3.750 1.3130 0.01114 0.00471 -0.2034 0.4728 0.6152
4.000 1.3371 0.01142 0.00494 -0.2027 0.4559 0.6239
4.250 1.3600 0.01176 0.00520 -0.2018 0.4369 0.6331
4.500 1.3831 0.01209 0.00548 -0.2010 0.4178 0.6427
4.750 1.4056 0.01245 0.00577 -0.2000 0.3979 0.6526
5.000 1.4278 0.01284 0.00611 -0.1991 0.3787 0.6626
5.250 1.4500 0.01321 0.00643 -0.1981 0.3619 0.6725
5.500 1.4719 0.01359 0.00678 -0.1971 0.3464 0.6837
5.750 1.4936 0.01397 0.00714 -0.1961 0.3323 0.6946
6.000 1.5146 0.01438 0.00752 -0.1949 0.3178 0.7058
6.250 1.5345 0.01484 0.00794 -0.1936 0.3019 0.7180
6.500 1.5527 0.01533 0.00839 -0.1919 0.2849 0.7303
6.750 1.5694 0.01584 0.00887 -0.1900 0.2684 0.7428
7.000 1.5856 0.01638 0.00938 -0.1880 0.2531 0.7564
7.250 1.6011 0.01695 0.00992 -0.1859 0.2380 0.7711
7.500 1.6159 0.01757 0.01052 -0.1838 0.2227 0.7867
8.000 1.6412 0.01904 0.01193 -0.1790 0.1886 0.8222
8.250 1.6515 0.01990 0.01275 -0.1763 0.1707 0.8450
8.500 1.6598 0.02080 0.01364 -0.1733 0.1543 0.8766
8.750 1.6619 0.02153 0.01440 -0.1690 0.1417 1.0000
9.000 1.6719 0.02261 0.01542 -0.1667 0.1286 1.0000
9.250 1.6823 0.02369 0.01647 -0.1645 0.1181 1.0000
9.500 1.6922 0.02484 0.01760 -0.1624 0.1098 1.0000
9.750 1.7026 0.02599 0.01875 -0.1604 0.1030 1.0000
10.000 1.7127 0.02720 0.01997 -0.1585 0.0974 1.0000
10.250 1.7231 0.02843 0.02123 -0.1567 0.0927 1.0000
10.500 1.7317 0.02984 0.02265 -0.1548 0.0884 1.0000
10.750 1.7424 0.03113 0.02399 -0.1533 0.0855 1.0000
11.000 1.7526 0.03250 0.02541 -0.1517 0.0829 1.0000
11.250 1.7614 0.03403 0.02698 -0.1502 0.0803 1.0000
11.500 1.7690 0.03571 0.02870 -0.1487 0.0779 1.0000
11.750 1.7766 0.03745 0.03051 -0.1472 0.0758 1.0000
12.000 1.7859 0.03907 0.03220 -0.1460 0.0743 1.0000
12.250 1.7941 0.04082 0.03403 -0.1448 0.0726 1.0000
12.500 1.8011 0.04274 0.03601 -0.1436 0.0708 1.0000
12.750 1.8071 0.04484 0.03817 -0.1425 0.0692 1.0000
13.000 1.8120 0.04710 0.04050 -0.1414 0.0678 1.0000
13.250 1.8152 0.04962 0.04308 -0.1403 0.0663 1.0000
13.500 1.8207 0.05193 0.04548 -0.1395 0.0653 1.0000
13.750 1.8271 0.05419 0.04784 -0.1387 0.0644 1.0000
14.000 1.8324 0.05664 0.05038 -0.1381 0.0633 1.0000
14.250 1.8368 0.05923 0.05307 -0.1375 0.0622 1.0000
14.500 1.8407 0.06196 0.05589 -0.1370 0.0611 1.0000
14.750 1.8434 0.06489 0.05890 -0.1366 0.0600 1.0000
15.000 1.8448 0.06806 0.06214 -0.1363 0.0589 1.0000
15.250 1.8446 0.07153 0.06569 -0.1361 0.0577 1.0000
15.500 1.8441 0.07510 0.06934 -0.1360 0.0564 1.0000
15.750 1.8490 0.07793 0.07228 -0.1360 0.0554 1.0000
16.000 1.8527 0.08098 0.07543 -0.1361 0.0539 1.0000
16.250 1.8545 0.08434 0.07888 -0.1363 0.0523 1.0000
16.500 1.8548 0.08796 0.08257 -0.1366 0.0508 1.0000
16.750 1.8532 0.09194 0.08662 -0.1371 0.0495 1.0000
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Polar data table (+)
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