FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il) Reynolds number: 50,000 Max Cl/Cd: 27.09 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxl142k-il-50000.txt Download as CSV file: xf-fxl142k-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX LIII-142 K 25 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.8541 0.07349 0.06625 -0.0219 1.0000 0.1752
-10.750 -0.8874 0.06757 0.06025 -0.0224 1.0000 0.1739
-10.500 -0.9160 0.06246 0.05496 -0.0217 1.0000 0.1731
-10.250 -0.9358 0.05774 0.04994 -0.0206 1.0000 0.1731
-10.000 -0.9481 0.05352 0.04533 -0.0191 1.0000 0.1741
-9.750 -0.9560 0.04978 0.04110 -0.0173 1.0000 0.1764
-9.500 -0.9295 0.04753 0.03904 -0.0172 1.0000 0.1838
-9.250 -0.9242 0.04442 0.03553 -0.0158 1.0000 0.1884
-9.000 -0.9132 0.04139 0.03215 -0.0146 1.0000 0.1930
-8.750 -0.8908 0.03910 0.02981 -0.0140 1.0000 0.2006
-8.500 -0.8734 0.03665 0.02714 -0.0131 1.0000 0.2095
-8.250 -0.8550 0.03471 0.02510 -0.0120 1.0000 0.2232
-8.000 -0.8332 0.03295 0.02351 -0.0111 1.0000 0.2412
-7.750 -0.8124 0.03123 0.02197 -0.0099 1.0000 0.2631
-7.500 -0.7928 0.02971 0.02068 -0.0084 1.0000 0.2903
-7.250 -0.7749 0.02860 0.01983 -0.0065 1.0000 0.3241
-7.000 -0.7583 0.02818 0.01973 -0.0040 1.0000 0.3654
-6.750 -0.7394 0.02846 0.02030 -0.0012 1.0000 0.4101
-6.500 -0.7095 0.03051 0.02266 0.0022 1.0000 0.4508
-6.250 -0.6836 0.03223 0.02442 0.0057 1.0000 0.4887
-6.000 -0.6505 0.03451 0.02673 0.0095 1.0000 0.5202
-5.750 -0.6255 0.03553 0.02771 0.0127 1.0000 0.5478
-5.500 -0.5942 0.03663 0.02874 0.0155 1.0000 0.5699
-5.250 -0.5795 0.03641 0.02846 0.0184 1.0000 0.5925
-5.000 -0.5498 0.03721 0.02922 0.0211 1.0000 0.6119
-4.750 -0.5408 0.03692 0.02894 0.0244 1.0000 0.6316
-4.500 -0.5484 0.03632 0.02838 0.0291 1.0000 0.6485
-4.250 -0.5553 0.03594 0.02799 0.0338 1.0000 0.6633
-4.000 -0.5602 0.03548 0.02750 0.0380 1.0000 0.6789
-3.750 -0.5610 0.03504 0.02702 0.0418 1.0000 0.6954
-3.500 -0.5519 0.03499 0.02692 0.0452 1.0000 0.7124
-3.250 -0.5423 0.03483 0.02671 0.0483 1.0000 0.7296
-3.000 -0.5331 0.03453 0.02636 0.0510 1.0000 0.7465
-2.750 -0.5247 0.03405 0.02581 0.0534 1.0000 0.7617
-2.500 -0.4978 0.03374 0.02540 0.0523 0.9952 0.7761
-2.250 -0.4517 0.03363 0.02513 0.0477 0.9844 0.7905
-2.000 -0.4071 0.03350 0.02487 0.0434 0.9741 0.8051
-1.750 -0.3571 0.03349 0.02473 0.0385 0.9640 0.8193
-1.500 -0.3106 0.03339 0.02454 0.0340 0.9540 0.8317
-1.250 -0.2694 0.03319 0.02425 0.0301 0.9439 0.8432
-1.000 -0.2345 0.03296 0.02395 0.0270 0.9339 0.8549
-0.750 -0.1689 0.03311 0.02403 0.0193 0.9252 0.8654
-0.500 -0.1132 0.03312 0.02400 0.0131 0.9155 0.8757
-0.250 -0.0756 0.03309 0.02394 0.0097 0.9055 0.8866
0.000 -0.0001 0.03313 0.02396 0.0000 0.8965 0.8965
0.250 0.0755 0.03309 0.02394 -0.0097 0.8866 0.9056
0.500 0.1138 0.03312 0.02400 -0.0131 0.8757 0.9155
0.750 0.1688 0.03311 0.02403 -0.0193 0.8653 0.9252
1.000 0.2348 0.03295 0.02394 -0.0271 0.8549 0.9339
1.250 0.2696 0.03318 0.02425 -0.0301 0.8432 0.9439
1.500 0.3107 0.03338 0.02453 -0.0340 0.8317 0.9539
1.750 0.3571 0.03348 0.02472 -0.0385 0.8191 0.9640
2.000 0.4072 0.03349 0.02486 -0.0434 0.8050 0.9742
2.250 0.4521 0.03362 0.02511 -0.0478 0.7905 0.9845
2.500 0.4981 0.03372 0.02537 -0.0523 0.7760 0.9952
2.750 0.5245 0.03405 0.02582 -0.0534 0.7618 1.0000
3.000 0.5330 0.03453 0.02635 -0.0510 0.7465 1.0000
3.250 0.5418 0.03486 0.02674 -0.0483 0.7298 1.0000
3.500 0.5521 0.03497 0.02690 -0.0452 0.7124 1.0000
3.750 0.5607 0.03505 0.02704 -0.0418 0.6954 1.0000
4.000 0.5600 0.03548 0.02750 -0.0380 0.6788 1.0000
4.250 0.5552 0.03594 0.02799 -0.0338 0.6633 1.0000
4.500 0.5478 0.03633 0.02839 -0.0290 0.6483 1.0000
4.750 0.5407 0.03691 0.02893 -0.0244 0.6315 1.0000
5.000 0.5499 0.03720 0.02921 -0.0211 0.6119 1.0000
5.250 0.5797 0.03639 0.02844 -0.0184 0.5925 1.0000
5.500 0.5943 0.03661 0.02873 -0.0155 0.5698 1.0000
5.750 0.6255 0.03554 0.02771 -0.0127 0.5478 1.0000
6.000 0.6503 0.03454 0.02677 -0.0095 0.5202 1.0000
6.250 0.6836 0.03224 0.02443 -0.0057 0.4887 1.0000
6.500 0.7095 0.03050 0.02265 -0.0022 0.4507 1.0000
6.750 0.7395 0.02845 0.02030 0.0012 0.4101 1.0000
7.000 0.7583 0.02818 0.01973 0.0040 0.3654 1.0000
7.250 0.7750 0.02861 0.01984 0.0065 0.3243 1.0000
7.500 0.7929 0.02971 0.02068 0.0084 0.2903 1.0000
7.750 0.8123 0.03123 0.02197 0.0099 0.2628 1.0000
8.000 0.8333 0.03295 0.02352 0.0111 0.2411 1.0000
8.250 0.8550 0.03471 0.02511 0.0120 0.2232 1.0000
8.500 0.8735 0.03666 0.02714 0.0131 0.2095 1.0000
8.750 0.8908 0.03910 0.02981 0.0140 0.2005 1.0000
9.000 0.9134 0.04139 0.03214 0.0146 0.1929 1.0000
9.250 0.9242 0.04443 0.03554 0.0158 0.1883 1.0000
9.500 0.9297 0.04751 0.03901 0.0172 0.1836 1.0000
9.750 0.9570 0.04981 0.04108 0.0173 0.1762 1.0000
10.000 0.9481 0.05352 0.04534 0.0191 0.1741 1.0000
10.250 0.9354 0.05777 0.04998 0.0205 0.1730 1.0000
10.500 0.9156 0.06250 0.05500 0.0216 0.1730 1.0000
10.750 0.8864 0.06762 0.06030 0.0224 0.1738 1.0000
11.000 0.8534 0.07357 0.06633 0.0218 0.1751 1.0000
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