FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 151.46 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63137sm-il-1000000.txt Download as CSV file: xf-fx63137sm-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1068 0.09242 0.09066 -0.0925 0.9755 0.0163
-10.000 0.0271 0.07137 0.06961 -0.1103 0.9310 0.0171
-9.750 -0.2458 0.02958 0.02692 -0.1594 0.9218 0.0130
-9.500 -0.1911 0.02282 0.01947 -0.1810 0.9044 0.0132
-9.250 -0.1574 0.02078 0.01707 -0.1863 0.8888 0.0134
-9.000 -0.1339 0.01761 0.01347 -0.1898 0.8737 0.0136
-8.750 -0.1083 0.01636 0.01205 -0.1909 0.8623 0.0139
-8.500 -0.0810 0.01564 0.01122 -0.1918 0.8526 0.0141
-8.250 -0.0536 0.01493 0.01038 -0.1925 0.8432 0.0144
-8.000 -0.0258 0.01428 0.00961 -0.1932 0.8352 0.0147
-7.750 0.0021 0.01367 0.00889 -0.1937 0.8271 0.0150
-7.500 0.0306 0.01310 0.00821 -0.1943 0.8198 0.0154
-7.250 0.0592 0.01264 0.00765 -0.1948 0.8124 0.0159
-7.000 0.0880 0.01240 0.00729 -0.1952 0.8054 0.0163
-6.750 0.1177 0.01148 0.00629 -0.1963 0.7989 0.0168
-6.500 0.1476 0.01098 0.00574 -0.1970 0.7922 0.0173
-6.250 0.1774 0.01064 0.00534 -0.1977 0.7860 0.0178
-6.000 0.2075 0.01031 0.00497 -0.1984 0.7796 0.0183
-5.750 0.2377 0.01003 0.00461 -0.1990 0.7732 0.0189
-5.500 0.2681 0.00976 0.00429 -0.1996 0.7673 0.0195
-5.250 0.2997 0.00936 0.00383 -0.2006 0.7610 0.0203
-5.000 0.3304 0.00911 0.00353 -0.2014 0.7548 0.0214
-4.750 0.3609 0.00893 0.00333 -0.2020 0.7490 0.0228
-4.500 0.3918 0.00870 0.00304 -0.2027 0.7427 0.0243
-4.250 0.4222 0.00854 0.00283 -0.2033 0.7366 0.0265
-4.000 0.4533 0.00833 0.00262 -0.2040 0.7307 0.0296
-3.750 0.4839 0.00817 0.00243 -0.2046 0.7244 0.0350
-3.500 0.5150 0.00800 0.00228 -0.2053 0.7185 0.0491
-3.250 0.5471 0.00773 0.00215 -0.2064 0.7123 0.0883
-3.000 0.5787 0.00751 0.00204 -0.2074 0.7060 0.1369
-2.750 0.6119 0.00719 0.00194 -0.2088 0.7000 0.2213
-2.500 0.6446 0.00691 0.00189 -0.2101 0.6936 0.3150
-2.250 0.6747 0.00685 0.00189 -0.2106 0.6870 0.3637
-2.000 0.7046 0.00682 0.00190 -0.2110 0.6809 0.3908
-1.750 0.7337 0.00683 0.00192 -0.2112 0.6741 0.4142
-1.500 0.7626 0.00687 0.00195 -0.2113 0.6677 0.4354
-1.250 0.7917 0.00688 0.00197 -0.2115 0.6609 0.4480
-1.000 0.8201 0.00695 0.00199 -0.2115 0.6540 0.4584
-0.750 0.8490 0.00698 0.00202 -0.2117 0.6474 0.4692
-0.500 0.8776 0.00703 0.00207 -0.2117 0.6401 0.4834
-0.250 0.9059 0.00710 0.00212 -0.2117 0.6331 0.4958
0.000 0.9344 0.00715 0.00216 -0.2118 0.6256 0.5045
0.250 0.9623 0.00725 0.00221 -0.2117 0.6181 0.5123
0.500 0.9909 0.00729 0.00227 -0.2118 0.6105 0.5206
1.000 1.0470 0.00745 0.00240 -0.2118 0.5948 0.5363
1.250 1.0743 0.00758 0.00247 -0.2116 0.5864 0.5443
1.500 1.1026 0.00764 0.00255 -0.2117 0.5785 0.5523
1.750 1.1298 0.00777 0.00264 -0.2115 0.5698 0.5609
2.000 1.1578 0.00784 0.00273 -0.2115 0.5615 0.5689
2.500 1.2126 0.00807 0.00294 -0.2113 0.5440 0.5859
2.750 1.2392 0.00823 0.00306 -0.2110 0.5346 0.5950
3.000 1.2662 0.00836 0.00318 -0.2109 0.5228 0.6033
3.250 1.2924 0.00854 0.00333 -0.2105 0.5088 0.6127
3.500 1.3184 0.00873 0.00348 -0.2102 0.4942 0.6218
3.750 1.3441 0.00894 0.00364 -0.2098 0.4801 0.6315
4.000 1.3694 0.00916 0.00383 -0.2093 0.4642 0.6407
4.250 1.3945 0.00941 0.00402 -0.2088 0.4481 0.6507
4.500 1.4197 0.00965 0.00423 -0.2084 0.4345 0.6610
4.750 1.4448 0.00989 0.00444 -0.2079 0.4215 0.6714
5.000 1.4699 0.01012 0.00466 -0.2074 0.4081 0.6821
5.250 1.4943 0.01039 0.00490 -0.2069 0.3933 0.6930
5.500 1.5182 0.01070 0.00517 -0.2062 0.3776 0.7046
5.750 1.5418 0.01101 0.00545 -0.2055 0.3626 0.7166
6.000 1.5650 0.01134 0.00574 -0.2047 0.3475 0.7283
6.250 1.5877 0.01170 0.00606 -0.2038 0.3319 0.7411
6.500 1.6096 0.01208 0.00640 -0.2028 0.3151 0.7546
6.750 1.6306 0.01251 0.00677 -0.2017 0.2971 0.7686
7.000 1.6507 0.01298 0.00718 -0.2004 0.2787 0.7831
7.250 1.6699 0.01347 0.00762 -0.1989 0.2611 0.7990
7.500 1.6876 0.01399 0.00808 -0.1972 0.2437 0.8161
7.750 1.7031 0.01452 0.00857 -0.1950 0.2264 0.8352
8.000 1.7171 0.01508 0.00910 -0.1926 0.2088 0.8590
8.250 1.7282 0.01566 0.00967 -0.1896 0.1905 0.8959
8.500 1.7333 0.01626 0.01025 -0.1855 0.1721 1.0000
8.750 1.7428 0.01720 0.01105 -0.1826 0.1512 1.0000
9.000 1.7519 0.01817 0.01191 -0.1797 0.1323 1.0000
9.250 1.7616 0.01913 0.01280 -0.1769 0.1181 1.0000
9.500 1.7722 0.02006 0.01368 -0.1744 0.1078 1.0000
9.750 1.7821 0.02106 0.01465 -0.1719 0.0993 1.0000
10.000 1.7947 0.02192 0.01552 -0.1699 0.0945 1.0000
10.250 1.8045 0.02299 0.01657 -0.1676 0.0893 1.0000
10.500 1.8168 0.02392 0.01753 -0.1657 0.0860 1.0000
10.750 1.8288 0.02490 0.01855 -0.1638 0.0833 1.0000
11.000 1.8386 0.02608 0.01974 -0.1618 0.0802 1.0000
11.250 1.8462 0.02747 0.02115 -0.1597 0.0769 1.0000
11.500 1.8575 0.02862 0.02236 -0.1580 0.0754 1.0000
11.750 1.8692 0.02977 0.02357 -0.1565 0.0741 1.0000
12.000 1.8794 0.03108 0.02493 -0.1549 0.0726 1.0000
12.250 1.8882 0.03255 0.02644 -0.1533 0.0709 1.0000
12.500 1.8954 0.03421 0.02814 -0.1517 0.0692 1.0000
12.750 1.8995 0.03622 0.03019 -0.1499 0.0670 1.0000
13.000 1.9054 0.03812 0.03216 -0.1484 0.0656 1.0000
13.250 1.9161 0.03959 0.03370 -0.1473 0.0648 1.0000
13.500 1.9255 0.04123 0.03540 -0.1463 0.0636 1.0000
13.750 1.9332 0.04308 0.03731 -0.1452 0.0622 1.0000
14.000 1.9396 0.04511 0.03938 -0.1441 0.0607 1.0000
14.250 1.9437 0.04745 0.04176 -0.1430 0.0590 1.0000
14.500 1.9439 0.05030 0.04468 -0.1419 0.0573 1.0000
14.750 1.9481 0.05278 0.04724 -0.1410 0.0563 1.0000
15.000 1.9562 0.05481 0.04935 -0.1404 0.0556 1.0000
15.250 1.9642 0.05689 0.05150 -0.1399 0.0544 1.0000
15.500 1.9695 0.05936 0.05402 -0.1393 0.0530 1.0000
15.750 1.9726 0.06215 0.05686 -0.1388 0.0518 1.0000
16.000 1.9741 0.06521 0.05997 -0.1384 0.0505 1.0000
16.250 1.9723 0.06880 0.06363 -0.1381 0.0491 1.0000
16.500 1.9726 0.07218 0.06710 -0.1379 0.0483 1.0000
16.750 1.9776 0.07492 0.06993 -0.1378 0.0476 1.0000
17.000 1.9811 0.07789 0.07299 -0.1378 0.0468 1.0000
17.250 1.9829 0.08115 0.07633 -0.1379 0.0458 1.0000
17.500 1.9835 0.08464 0.07989 -0.1381 0.0448 1.0000
17.750 1.9825 0.08841 0.08373 -0.1385 0.0437 1.0000
18.000 1.9797 0.09251 0.08789 -0.1390 0.0425 1.0000
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Polar data table (+)
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