FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il) Reynolds number: 50,000 Max Cl/Cd: 28.29 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxl142k-il-50000-n5.txt Download as CSV file: xf-fxl142k-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8241 0.09679 0.08924 -0.0134 1.0000 0.0866
-13.250 -0.8672 0.08607 0.07838 -0.0200 1.0000 0.0862
-13.000 -0.9012 0.07800 0.07013 -0.0244 1.0000 0.0861
-12.750 -0.9308 0.07145 0.06334 -0.0275 1.0000 0.0863
-12.500 -0.9558 0.06608 0.05769 -0.0293 1.0000 0.0868
-12.250 -0.9418 0.06427 0.05597 -0.0289 1.0000 0.0895
-12.000 -0.9456 0.06117 0.05274 -0.0291 1.0000 0.0914
-11.750 -0.9518 0.05791 0.04929 -0.0291 1.0000 0.0931
-11.500 -0.9564 0.05483 0.04598 -0.0285 1.0000 0.0949
-11.250 -0.9577 0.05198 0.04285 -0.0276 1.0000 0.0967
-11.000 -0.9570 0.04937 0.03992 -0.0263 1.0000 0.0989
-10.750 -0.9486 0.04723 0.03757 -0.0252 1.0000 0.1020
-10.500 -0.9321 0.04564 0.03599 -0.0245 1.0000 0.1059
-10.250 -0.9187 0.04383 0.03402 -0.0236 1.0000 0.1101
-10.000 -0.9028 0.04193 0.03182 -0.0227 1.0000 0.1143
-9.750 -0.8795 0.04038 0.03027 -0.0222 1.0000 0.1187
-9.500 -0.8596 0.03896 0.02880 -0.0215 1.0000 0.1243
-9.250 -0.8418 0.03752 0.02717 -0.0205 1.0000 0.1314
-9.000 -0.8268 0.03618 0.02589 -0.0195 1.0000 0.1397
-8.750 -0.8122 0.03480 0.02449 -0.0183 1.0000 0.1494
-8.500 -0.7981 0.03344 0.02309 -0.0170 1.0000 0.1610
-8.250 -0.7858 0.03208 0.02185 -0.0155 1.0000 0.1724
-8.000 -0.7742 0.03074 0.02062 -0.0140 1.0000 0.1861
-7.750 -0.7626 0.02946 0.01944 -0.0125 1.0000 0.2025
-7.500 -0.7516 0.02821 0.01831 -0.0109 1.0000 0.2249
-7.250 -0.7405 0.02702 0.01732 -0.0092 1.0000 0.2542
-7.000 -0.7288 0.02601 0.01663 -0.0074 1.0000 0.2885
-6.750 -0.7151 0.02528 0.01617 -0.0055 1.0000 0.3302
-6.500 -0.6994 0.02491 0.01602 -0.0035 1.0000 0.3717
-6.250 -0.6824 0.02477 0.01599 -0.0016 1.0000 0.4102
-6.000 -0.6637 0.02482 0.01606 0.0003 1.0000 0.4401
-5.750 -0.6441 0.02496 0.01620 0.0021 1.0000 0.4628
-5.500 -0.6280 0.02475 0.01589 0.0038 1.0000 0.4841
-5.250 -0.6134 0.02459 0.01567 0.0058 1.0000 0.5019
-5.000 -0.6010 0.02461 0.01568 0.0081 1.0000 0.5169
-4.750 -0.5639 0.02490 0.01588 0.0064 0.9762 0.5347
-4.500 -0.5225 0.02514 0.01599 0.0040 0.9549 0.5541
-4.250 -0.4829 0.02529 0.01599 0.0019 0.9363 0.5748
-4.000 -0.4445 0.02549 0.01608 0.0003 0.9190 0.5919
-3.750 -0.4092 0.02546 0.01590 -0.0010 0.9018 0.6061
-3.500 -0.3728 0.02540 0.01571 -0.0023 0.8872 0.6161
-3.250 -0.3403 0.02524 0.01541 -0.0031 0.8728 0.6263
-3.000 -0.3117 0.02506 0.01509 -0.0033 0.8584 0.6373
-2.750 -0.2831 0.02497 0.01490 -0.0033 0.8452 0.6466
-2.500 -0.2550 0.02486 0.01467 -0.0032 0.8332 0.6548
-2.250 -0.2294 0.02464 0.01431 -0.0031 0.8221 0.6643
-2.000 -0.2020 0.02459 0.01420 -0.0027 0.8110 0.6711
-1.750 -0.1789 0.02441 0.01392 -0.0023 0.7993 0.6806
-1.500 -0.1532 0.02435 0.01383 -0.0019 0.7885 0.6879
-1.250 -0.1292 0.02419 0.01359 -0.0015 0.7785 0.6971
-1.000 -0.1027 0.02409 0.01343 -0.0011 0.7699 0.7049
-0.750 -0.0778 0.02397 0.01327 -0.0009 0.7610 0.7135
-0.500 -0.0510 0.02387 0.01312 -0.0006 0.7536 0.7213
-0.250 -0.0256 0.02382 0.01305 -0.0003 0.7450 0.7293
0.000 0.0000 0.02380 0.01301 0.0000 0.7375 0.7374
0.250 0.0256 0.02382 0.01305 0.0003 0.7293 0.7450
0.500 0.0510 0.02387 0.01313 0.0006 0.7213 0.7536
0.750 0.0778 0.02397 0.01327 0.0009 0.7134 0.7610
1.000 0.1027 0.02409 0.01344 0.0011 0.7049 0.7699
1.250 0.1292 0.02419 0.01360 0.0015 0.6971 0.7785
1.500 0.1532 0.02435 0.01383 0.0019 0.6879 0.7885
1.750 0.1789 0.02441 0.01392 0.0023 0.6805 0.7994
2.000 0.2020 0.02459 0.01420 0.0027 0.6711 0.8110
2.250 0.2293 0.02464 0.01431 0.0031 0.6642 0.8221
2.500 0.2550 0.02486 0.01467 0.0032 0.6548 0.8332
2.750 0.2831 0.02497 0.01489 0.0033 0.6465 0.8452
3.000 0.3118 0.02505 0.01508 0.0033 0.6372 0.8584
3.250 0.3403 0.02524 0.01541 0.0031 0.6263 0.8728
3.500 0.3728 0.02540 0.01572 0.0023 0.6161 0.8872
3.750 0.4092 0.02546 0.01590 0.0010 0.6061 0.9018
4.000 0.4445 0.02549 0.01608 -0.0003 0.5919 0.9190
4.250 0.4829 0.02529 0.01598 -0.0019 0.5750 0.9362
4.500 0.5225 0.02513 0.01599 -0.0040 0.5540 0.9549
4.750 0.5639 0.02489 0.01587 -0.0064 0.5346 0.9762
5.000 0.6010 0.02460 0.01568 -0.0081 0.5168 1.0000
5.250 0.6134 0.02459 0.01567 -0.0057 0.5019 1.0000
5.500 0.6280 0.02475 0.01589 -0.0038 0.4840 1.0000
5.750 0.6441 0.02496 0.01620 -0.0021 0.4629 1.0000
6.000 0.6638 0.02482 0.01605 -0.0003 0.4403 1.0000
6.250 0.6824 0.02477 0.01600 0.0016 0.4103 1.0000
6.500 0.6994 0.02491 0.01602 0.0035 0.3717 1.0000
6.750 0.7151 0.02528 0.01616 0.0055 0.3298 1.0000
7.000 0.7288 0.02600 0.01663 0.0074 0.2885 1.0000
7.250 0.7406 0.02701 0.01732 0.0092 0.2545 1.0000
7.500 0.7516 0.02821 0.01831 0.0109 0.2249 1.0000
7.750 0.7626 0.02946 0.01944 0.0125 0.2023 1.0000
8.000 0.7743 0.03074 0.02062 0.0140 0.1859 1.0000
8.250 0.7859 0.03208 0.02185 0.0155 0.1724 1.0000
8.500 0.7983 0.03344 0.02309 0.0170 0.1610 1.0000
8.750 0.8123 0.03480 0.02449 0.0182 0.1493 1.0000
9.000 0.8270 0.03618 0.02589 0.0194 0.1397 1.0000
9.250 0.8419 0.03752 0.02716 0.0205 0.1313 1.0000
9.500 0.8599 0.03896 0.02880 0.0214 0.1242 1.0000
9.750 0.8799 0.04038 0.03027 0.0222 0.1187 1.0000
10.000 0.9032 0.04194 0.03182 0.0227 0.1143 1.0000
10.250 0.9188 0.04384 0.03402 0.0236 0.1099 1.0000
10.500 0.9322 0.04564 0.03599 0.0245 0.1058 1.0000
10.750 0.9489 0.04720 0.03751 0.0251 0.1018 1.0000
11.000 0.9570 0.04938 0.03989 0.0263 0.0988 1.0000
11.250 0.9579 0.05199 0.04286 0.0275 0.0966 1.0000
11.500 0.9566 0.05484 0.04599 0.0285 0.0948 1.0000
11.750 0.9523 0.05792 0.04930 0.0290 0.0930 1.0000
12.000 0.9464 0.06114 0.05271 0.0291 0.0913 1.0000
12.250 0.9434 0.06419 0.05588 0.0289 0.0893 1.0000
12.500 0.9563 0.06613 0.05774 0.0292 0.0868 1.0000
12.750 0.9305 0.07153 0.06342 0.0273 0.0862 1.0000
13.000 0.9004 0.07820 0.07033 0.0242 0.0860 1.0000
13.250 0.8648 0.08651 0.07882 0.0195 0.0861 1.0000
13.500 0.8218 0.09738 0.08982 0.0129 0.0865 1.0000
13.750 0.7750 0.11107 0.10354 0.0044 0.0868 1.0000
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