FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.61 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63137sm-il-1000000-n5.txt Download as CSV file: xf-fx63137sm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5136 0.05362 0.05118 -0.1127 0.9771 0.0086
-12.500 -0.5571 0.04224 0.03953 -0.1225 0.9606 0.0085
-12.250 -0.5583 0.03634 0.03348 -0.1300 0.9459 0.0086
-12.000 -0.5374 0.03096 0.02788 -0.1409 0.9332 0.0086
-11.500 -0.4416 0.02346 0.01995 -0.1663 0.9105 0.0089
-11.250 -0.3953 0.02138 0.01766 -0.1753 0.8953 0.0091
-11.000 -0.3623 0.01962 0.01566 -0.1810 0.8773 0.0092
-10.750 -0.3361 0.01855 0.01442 -0.1833 0.8625 0.0093
-10.500 -0.3112 0.01766 0.01338 -0.1847 0.8505 0.0095
-10.250 -0.2862 0.01683 0.01240 -0.1858 0.8398 0.0097
-10.000 -0.2604 0.01607 0.01152 -0.1867 0.8306 0.0098
-9.750 -0.2341 0.01543 0.01074 -0.1875 0.8219 0.0100
-9.500 -0.2069 0.01481 0.01001 -0.1883 0.8140 0.0102
-9.000 -0.1515 0.01375 0.00873 -0.1897 0.7993 0.0105
-8.750 -0.1233 0.01331 0.00819 -0.1903 0.7922 0.0106
-8.500 -0.0943 0.01270 0.00749 -0.1913 0.7858 0.0109
-8.250 -0.0650 0.01225 0.00699 -0.1921 0.7791 0.0112
-8.000 -0.0362 0.01194 0.00661 -0.1926 0.7725 0.0115
-7.750 -0.0067 0.01162 0.00623 -0.1932 0.7667 0.0118
-7.500 0.0228 0.01130 0.00585 -0.1938 0.7601 0.0121
-7.250 0.0522 0.01101 0.00548 -0.1944 0.7540 0.0124
-7.000 0.0825 0.01070 0.00512 -0.1951 0.7482 0.0127
-6.750 0.1124 0.01043 0.00479 -0.1958 0.7418 0.0130
-6.500 0.1423 0.01020 0.00448 -0.1963 0.7361 0.0132
-6.250 0.1730 0.00991 0.00416 -0.1971 0.7302 0.0136
-6.000 0.2034 0.00966 0.00386 -0.1978 0.7239 0.0141
-5.750 0.2335 0.00948 0.00363 -0.1983 0.7183 0.0146
-5.500 0.2638 0.00930 0.00342 -0.1989 0.7121 0.0152
-5.250 0.2937 0.00916 0.00323 -0.1994 0.7059 0.0160
-5.000 0.3239 0.00901 0.00303 -0.1999 0.7002 0.0168
-4.750 0.3544 0.00885 0.00286 -0.2005 0.6941 0.0179
-4.500 0.3841 0.00875 0.00271 -0.2009 0.6877 0.0190
-4.250 0.4144 0.00863 0.00256 -0.2014 0.6818 0.0205
-4.000 0.4446 0.00853 0.00244 -0.2019 0.6754 0.0226
-3.750 0.4742 0.00845 0.00232 -0.2023 0.6690 0.0254
-3.500 0.5046 0.00835 0.00222 -0.2028 0.6630 0.0298
-3.250 0.5346 0.00826 0.00213 -0.2032 0.6561 0.0379
-3.000 0.5650 0.00816 0.00205 -0.2038 0.6500 0.0534
-2.750 0.5957 0.00804 0.00198 -0.2045 0.6432 0.0752
-2.500 0.6260 0.00794 0.00193 -0.2051 0.6364 0.1026
-2.250 0.6575 0.00778 0.00187 -0.2060 0.6299 0.1476
-2.000 0.6897 0.00756 0.00182 -0.2071 0.6226 0.2197
-1.750 0.7217 0.00738 0.00180 -0.2082 0.6158 0.2987
-1.500 0.7525 0.00728 0.00183 -0.2090 0.6084 0.3589
-1.250 0.7814 0.00731 0.00186 -0.2091 0.6010 0.3806
-1.000 0.8106 0.00734 0.00189 -0.2094 0.5937 0.3958
-0.500 0.8681 0.00744 0.00198 -0.2096 0.5783 0.4291
-0.250 0.8964 0.00751 0.00204 -0.2097 0.5696 0.4468
0.500 0.9810 0.00776 0.00221 -0.2097 0.5443 0.4710
0.750 1.0086 0.00788 0.00229 -0.2097 0.5352 0.4778
1.000 1.0367 0.00797 0.00237 -0.2097 0.5259 0.4855
1.250 1.0641 0.00810 0.00246 -0.2095 0.5169 0.4922
1.500 1.0918 0.00821 0.00256 -0.2095 0.5071 0.4997
1.750 1.1191 0.00834 0.00266 -0.2094 0.4980 0.5073
2.000 1.1463 0.00849 0.00277 -0.2092 0.4877 0.5140
2.250 1.1736 0.00861 0.00289 -0.2091 0.4783 0.5215
2.500 1.2003 0.00878 0.00302 -0.2089 0.4684 0.5287
2.750 1.2275 0.00892 0.00315 -0.2088 0.4584 0.5367
3.000 1.2535 0.00913 0.00330 -0.2084 0.4444 0.5438
3.250 1.2787 0.00940 0.00350 -0.2080 0.4252 0.5513
3.500 1.3031 0.00972 0.00372 -0.2074 0.4041 0.5598
3.750 1.3278 0.01002 0.00394 -0.2068 0.3850 0.5673
4.000 1.3521 0.01034 0.00419 -0.2062 0.3645 0.5752
4.250 1.3754 0.01073 0.00446 -0.2054 0.3415 0.5830
4.500 1.3993 0.01106 0.00473 -0.2048 0.3238 0.5921
4.750 1.4237 0.01134 0.00497 -0.2042 0.3105 0.6005
5.000 1.4478 0.01165 0.00524 -0.2036 0.2969 0.6091
5.250 1.4710 0.01200 0.00554 -0.2028 0.2813 0.6178
5.500 1.4934 0.01241 0.00587 -0.2019 0.2637 0.6276
5.750 1.5154 0.01281 0.00622 -0.2009 0.2476 0.6367
6.000 1.5374 0.01321 0.00657 -0.2000 0.2330 0.6462
6.250 1.5586 0.01363 0.00694 -0.1989 0.2182 0.6559
6.500 1.5789 0.01409 0.00735 -0.1976 0.2028 0.6666
6.750 1.5975 0.01463 0.00782 -0.1961 0.1853 0.6769
7.000 1.6127 0.01522 0.00833 -0.1939 0.1672 0.6871
7.250 1.6275 0.01582 0.00887 -0.1916 0.1498 0.6988
7.500 1.6418 0.01644 0.00943 -0.1893 0.1347 0.7104
7.750 1.6561 0.01708 0.01003 -0.1871 0.1215 0.7222
8.000 1.6702 0.01773 0.01065 -0.1848 0.1107 0.7353
8.250 1.6852 0.01835 0.01128 -0.1828 0.1024 0.7490
8.500 1.7004 0.01895 0.01190 -0.1808 0.0962 0.7632
8.750 1.7149 0.01962 0.01259 -0.1788 0.0903 0.7783
9.000 1.7297 0.02028 0.01328 -0.1769 0.0857 0.7952
9.250 1.7446 0.02093 0.01398 -0.1750 0.0822 0.8142
9.750 1.7715 0.02240 0.01558 -0.1711 0.0758 0.8649
10.000 1.7793 0.02292 0.01627 -0.1679 0.0744 1.0000
10.250 1.7931 0.02375 0.01713 -0.1662 0.0724 1.0000
10.500 1.8057 0.02469 0.01809 -0.1644 0.0704 1.0000
10.750 1.8172 0.02572 0.01914 -0.1626 0.0682 1.0000
11.000 1.8284 0.02683 0.02027 -0.1608 0.0658 1.0000
11.250 1.8413 0.02783 0.02133 -0.1593 0.0648 1.0000
11.500 1.8533 0.02893 0.02248 -0.1578 0.0637 1.0000
11.750 1.8645 0.03013 0.02373 -0.1562 0.0624 1.0000
12.000 1.8749 0.03144 0.02508 -0.1547 0.0611 1.0000
12.250 1.8843 0.03286 0.02654 -0.1532 0.0598 1.0000
12.500 1.8930 0.03440 0.02811 -0.1517 0.0584 1.0000
12.750 1.9003 0.03611 0.02987 -0.1501 0.0566 1.0000
13.000 1.9105 0.03758 0.03141 -0.1490 0.0559 1.0000
13.250 1.9198 0.03917 0.03306 -0.1478 0.0549 1.0000
13.500 1.9278 0.04094 0.03488 -0.1466 0.0536 1.0000
13.750 1.9345 0.04287 0.03687 -0.1454 0.0521 1.0000
14.000 1.9402 0.04498 0.03901 -0.1443 0.0505 1.0000
14.250 1.9447 0.04727 0.04135 -0.1432 0.0487 1.0000
14.500 1.9514 0.04936 0.04350 -0.1423 0.0478 1.0000
14.750 1.9578 0.05154 0.04575 -0.1415 0.0469 1.0000
15.000 1.9634 0.05385 0.04813 -0.1408 0.0458 1.0000
15.250 1.9669 0.05648 0.05081 -0.1401 0.0440 1.0000
15.500 1.9687 0.05937 0.05374 -0.1395 0.0423 1.0000
15.750 1.9716 0.06219 0.05663 -0.1390 0.0410 1.0000
16.000 1.9756 0.06492 0.05943 -0.1386 0.0399 1.0000
16.250 1.9779 0.06792 0.06250 -0.1383 0.0388 1.0000
16.500 1.9791 0.07113 0.06579 -0.1381 0.0376 1.0000
16.750 1.9788 0.07462 0.06933 -0.1380 0.0362 1.0000
17.000 1.9785 0.07816 0.07294 -0.1380 0.0351 1.0000
17.250 1.9793 0.08158 0.07644 -0.1381 0.0341 1.0000
17.500 1.9784 0.08529 0.08024 -0.1383 0.0327 1.0000
17.750 1.9766 0.08921 0.08424 -0.1387 0.0315 1.0000
18.000 1.9726 0.09350 0.08858 -0.1393 0.0300 1.0000
18.250 1.9700 0.09762 0.09277 -0.1399 0.0284 1.0000
18.500 1.9664 0.10191 0.09715 -0.1407 0.0271 1.0000
18.750 1.9596 0.10680 0.10210 -0.1418 0.0252 1.0000
19.000 1.9548 0.11137 0.10675 -0.1429 0.0237 1.0000
19.250 1.9457 0.11669 0.11213 -0.1444 0.0213 1.0000
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Polar data table (+)
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