FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il) Reynolds number: 100,000 Max Cl/Cd: 60.51 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63137sm-il-100000.txt Download as CSV file: xf-fx63137sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2302 0.11133 0.10701 -0.0485 0.9751 0.1054
-7.750 -0.2291 0.10879 0.10449 -0.0531 0.9667 0.1105
-7.500 -0.2619 0.10841 0.10422 -0.0617 0.9535 0.1124
-7.250 -0.2052 0.10149 0.09723 -0.0583 0.9545 0.1166
-7.000 -0.1870 0.09840 0.09413 -0.0613 0.9495 0.1224
-6.750 -0.2168 0.09747 0.09329 -0.0679 0.9360 0.1276
-6.500 -0.2126 0.09367 0.08953 -0.0674 0.9280 0.1296
-6.250 -0.1749 0.09037 0.08618 -0.0662 0.9257 0.1347
-6.000 -0.1803 0.08835 0.08419 -0.0682 0.9155 0.1414
-5.750 -0.1696 0.08386 0.07973 -0.0740 0.9089 0.1475
-5.500 -0.1710 0.07979 0.07565 -0.0871 0.8957 0.1607
-5.250 -0.1492 0.07801 0.07390 -0.0787 0.8934 0.1647
-5.000 -0.1396 0.07637 0.07227 -0.0779 0.8857 0.1728
-4.750 -0.0386 0.04454 0.03862 -0.1382 0.8811 0.0873
-4.500 0.0302 0.03857 0.03170 -0.1489 0.8792 0.0772
-4.250 0.0908 0.03515 0.02757 -0.1561 0.8770 0.0762
-4.000 0.1450 0.03322 0.02526 -0.1611 0.8748 0.0810
-3.750 0.1684 0.03254 0.02432 -0.1609 0.8661 0.0828
-3.500 0.2113 0.03091 0.02262 -0.1636 0.8621 0.0875
-3.250 0.2591 0.02969 0.02132 -0.1669 0.8592 0.0986
-3.000 0.3044 0.02842 0.02025 -0.1699 0.8560 0.1160
-2.750 0.3315 0.02801 0.02003 -0.1707 0.8471 0.1467
-2.500 0.3965 0.02655 0.01992 -0.1781 0.8447 0.4690
-2.250 0.4359 0.02684 0.02017 -0.1785 0.8415 0.5260
-2.000 0.4425 0.02789 0.02128 -0.1745 0.8304 0.5495
-1.750 0.4780 0.02797 0.02130 -0.1744 0.8262 0.5813
-1.500 0.5165 0.02778 0.02108 -0.1745 0.8238 0.6044
-1.250 0.5205 0.02875 0.02205 -0.1706 0.8115 0.6198
-1.000 0.5564 0.02852 0.02179 -0.1704 0.8082 0.6423
-0.750 0.5699 0.02915 0.02241 -0.1679 0.7985 0.6574
-0.500 0.6069 0.02890 0.02208 -0.1690 0.7934 0.6728
-0.250 0.6550 0.02828 0.02134 -0.1718 0.7907 0.6879
0.000 0.6666 0.02897 0.02203 -0.1694 0.7801 0.6981
0.250 0.7064 0.02853 0.02153 -0.1709 0.7756 0.7108
0.500 0.7538 0.02780 0.02071 -0.1736 0.7728 0.7244
0.750 0.7674 0.02860 0.02151 -0.1719 0.7615 0.7362
1.000 0.8071 0.02799 0.02086 -0.1731 0.7575 0.7483
1.250 0.8527 0.02721 0.02002 -0.1752 0.7545 0.7618
1.500 0.8625 0.02810 0.02095 -0.1729 0.7424 0.7734
1.750 0.9074 0.02733 0.02013 -0.1750 0.7388 0.7881
2.000 0.9186 0.02806 0.02092 -0.1725 0.7277 0.8007
2.250 0.9578 0.02738 0.02021 -0.1736 0.7230 0.8157
2.500 0.9767 0.02771 0.02058 -0.1721 0.7139 0.8303
2.750 1.0085 0.02732 0.02018 -0.1722 0.7073 0.8473
3.250 1.0556 0.02711 0.02001 -0.1701 0.6915 0.8851
3.750 1.0925 0.02665 0.01966 -0.1659 0.6755 0.9479
4.000 1.1499 0.02572 0.01866 -0.1707 0.6705 1.0000
4.250 1.1808 0.02637 0.01937 -0.1724 0.6589 1.0000
4.500 1.2378 0.02563 0.01852 -0.1772 0.6533 1.0000
4.750 1.2641 0.02627 0.01922 -0.1777 0.6413 1.0000
5.000 1.3114 0.02584 0.01872 -0.1809 0.6342 1.0000
5.250 1.3392 0.02620 0.01911 -0.1812 0.6229 1.0000
5.500 1.3693 0.02644 0.01938 -0.1817 0.6126 1.0000
5.750 1.4098 0.02610 0.01896 -0.1835 0.6037 1.0000
6.000 1.4320 0.02657 0.01950 -0.1827 0.5916 1.0000
6.250 1.4632 0.02650 0.01942 -0.1830 0.5802 1.0000
6.500 1.4970 0.02602 0.01885 -0.1833 0.5665 1.0000
6.750 1.5261 0.02570 0.01844 -0.1829 0.5512 1.0000
7.000 1.5512 0.02565 0.01836 -0.1821 0.5360 1.0000
7.250 1.5708 0.02596 0.01872 -0.1805 0.5215 1.0000
7.500 1.5908 0.02630 0.01910 -0.1791 0.5071 1.0000
7.750 1.6111 0.02663 0.01947 -0.1777 0.4927 1.0000
8.000 1.6308 0.02698 0.01982 -0.1762 0.4779 1.0000
8.250 1.6492 0.02737 0.02022 -0.1745 0.4628 1.0000
8.500 1.6658 0.02783 0.02070 -0.1725 0.4473 1.0000
8.750 1.6798 0.02837 0.02124 -0.1702 0.4313 1.0000
9.000 1.6911 0.02900 0.02188 -0.1675 0.4149 1.0000
9.250 1.6982 0.02971 0.02261 -0.1641 0.3985 1.0000
9.500 1.7027 0.03057 0.02348 -0.1604 0.3818 1.0000
9.750 1.7046 0.03160 0.02454 -0.1566 0.3642 1.0000
10.000 1.7043 0.03284 0.02577 -0.1527 0.3457 1.0000
10.250 1.7023 0.03430 0.02719 -0.1488 0.3264 1.0000
10.500 1.6992 0.03601 0.02879 -0.1451 0.3064 1.0000
10.750 1.6921 0.03817 0.03095 -0.1414 0.2849 1.0000
11.000 1.6853 0.04058 0.03327 -0.1382 0.2637 1.0000
11.250 1.6800 0.04315 0.03568 -0.1353 0.2441 1.0000
11.500 1.6770 0.04579 0.03818 -0.1329 0.2263 1.0000
11.750 1.6767 0.04838 0.04067 -0.1308 0.2110 1.0000
12.000 1.6789 0.05085 0.04308 -0.1291 0.1983 1.0000
12.250 1.6833 0.05326 0.04553 -0.1277 0.1875 1.0000
12.500 1.6939 0.05530 0.04750 -0.1265 0.1786 1.0000
12.750 1.7041 0.05733 0.04956 -0.1254 0.1710 1.0000
13.000 1.7189 0.05918 0.05141 -0.1245 0.1643 1.0000
13.250 1.7289 0.06129 0.05362 -0.1236 0.1583 1.0000
13.500 1.7550 0.06250 0.05467 -0.1232 0.1523 1.0000
13.750 1.7595 0.06513 0.05760 -0.1221 0.1484 1.0000
14.000 1.7727 0.06718 0.05976 -0.1214 0.1442 1.0000
14.250 1.8128 0.06788 0.06024 -0.1217 0.1389 1.0000
14.500 1.8084 0.07112 0.06384 -0.1203 0.1365 1.0000
14.750 1.8073 0.07434 0.06735 -0.1193 0.1339 1.0000
15.000 1.8124 0.07720 0.07043 -0.1185 0.1312 1.0000
15.250 1.8280 0.07928 0.07256 -0.1181 0.1282 1.0000
15.500 1.8540 0.08141 0.07470 -0.1180 0.1249 1.0000
15.750 1.8366 0.08594 0.07961 -0.1170 0.1237 1.0000
16.000 1.8185 0.09085 0.08488 -0.1164 0.1225 1.0000
16.250 1.7998 0.09611 0.09048 -0.1163 0.1213 1.0000
16.500 1.7791 0.10188 0.09657 -0.1169 0.1202 1.0000
16.750 1.7555 0.10828 0.10328 -0.1181 0.1193 1.0000
17.000 1.7241 0.11611 0.11143 -0.1205 0.1188 1.0000
17.250 1.6705 0.12793 0.12364 -0.1258 0.1191 1.0000
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Polar data table (+)
Polar graphs
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