FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.07 at α=11.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxl142k-il-1000000-n5.txt Download as CSV file: xf-fxl142k-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.1442 0.13020 0.12711 0.0172 1.0000 0.0026
-19.500 -1.1767 0.12018 0.11695 0.0120 1.0000 0.0027
-19.250 -1.2049 0.11114 0.10776 0.0074 1.0000 0.0026
-19.000 -1.2266 0.10354 0.10002 0.0037 1.0000 0.0026
-18.750 -1.2508 0.09566 0.09199 -0.0001 1.0000 0.0026
-18.500 -1.2700 0.08882 0.08502 -0.0034 1.0000 0.0026
-18.250 -1.2848 0.08288 0.07897 -0.0061 1.0000 0.0027
-18.000 -1.2990 0.07712 0.07308 -0.0087 1.0000 0.0026
-17.750 -1.3127 0.07161 0.06747 -0.0111 1.0000 0.0027
-17.500 -1.3175 0.06753 0.06328 -0.0127 1.0000 0.0027
-17.250 -1.3276 0.06278 0.05843 -0.0146 1.0000 0.0027
-17.000 -1.3311 0.05911 0.05467 -0.0160 1.0000 0.0027
-16.750 -1.3389 0.05503 0.05049 -0.0173 1.0000 0.0029
-16.500 -1.3420 0.05169 0.04706 -0.0183 1.0000 0.0029
-16.250 -1.3443 0.04854 0.04383 -0.0191 1.0000 0.0030
-16.000 -1.3446 0.04564 0.04084 -0.0199 1.0000 0.0030
-15.750 -1.3449 0.04281 0.03792 -0.0204 1.0000 0.0031
-15.500 -1.3422 0.04032 0.03535 -0.0210 1.0000 0.0031
-15.250 -1.3397 0.03783 0.03278 -0.0214 1.0000 0.0033
-15.000 -1.3351 0.03559 0.03046 -0.0217 1.0000 0.0033
-14.750 -1.3295 0.03345 0.02825 -0.0220 1.0000 0.0035
-14.500 -1.3221 0.03151 0.02624 -0.0223 1.0000 0.0035
-14.250 -1.3140 0.02968 0.02434 -0.0225 1.0000 0.0037
-14.000 -1.3073 0.02773 0.02232 -0.0226 1.0000 0.0041
-13.750 -1.2989 0.02599 0.02051 -0.0226 1.0000 0.0045
-13.500 -1.2867 0.02472 0.01919 -0.0224 1.0000 0.0044
-13.250 -1.2777 0.02327 0.01766 -0.0220 1.0000 0.0051
-13.000 -1.2681 0.02201 0.01634 -0.0212 1.0000 0.0058
-12.750 -1.2571 0.02102 0.01530 -0.0201 1.0000 0.0062
-12.500 -1.2475 0.02009 0.01433 -0.0184 1.0000 0.0071
-12.250 -1.2421 0.01909 0.01332 -0.0157 1.0000 0.0098
-12.000 -1.2326 0.01826 0.01250 -0.0134 1.0000 0.0134
-11.750 -1.2182 0.01753 0.01178 -0.0118 1.0000 0.0168
-11.500 -1.2003 0.01699 0.01123 -0.0106 1.0000 0.0185
-11.250 -1.1823 0.01643 0.01069 -0.0094 1.0000 0.0214
-10.750 -1.0934 0.01540 0.00949 -0.0179 0.8669 0.0288
-10.500 -1.0744 0.01522 0.00915 -0.0164 0.8302 0.0297
-10.250 -1.0536 0.01495 0.00879 -0.0154 0.8158 0.0303
-10.000 -1.0330 0.01457 0.00836 -0.0143 0.8028 0.0318
-9.750 -1.0130 0.01429 0.00795 -0.0130 0.7549 0.0334
-9.500 -0.9915 0.01402 0.00760 -0.0121 0.7404 0.0351
-9.250 -0.9685 0.01375 0.00727 -0.0113 0.7303 0.0362
-9.000 -0.9447 0.01353 0.00699 -0.0108 0.7218 0.0375
-8.750 -0.9205 0.01331 0.00671 -0.0102 0.7130 0.0383
-8.500 -0.8954 0.01312 0.00649 -0.0098 0.7047 0.0390
-8.250 -0.8716 0.01284 0.00613 -0.0092 0.6946 0.0395
-8.000 -0.8475 0.01254 0.00579 -0.0086 0.6818 0.0414
-7.500 -0.7985 0.01205 0.00519 -0.0075 0.6549 0.0443
-7.250 -0.7736 0.01182 0.00492 -0.0070 0.6472 0.0459
-7.000 -0.7484 0.01160 0.00467 -0.0066 0.6413 0.0474
-6.750 -0.7229 0.01140 0.00443 -0.0061 0.6362 0.0492
-6.500 -0.6977 0.01113 0.00418 -0.0057 0.6319 0.0548
-6.250 -0.6717 0.01093 0.00397 -0.0054 0.6273 0.0597
-6.000 -0.6460 0.01072 0.00374 -0.0050 0.6220 0.0657
-5.750 -0.6198 0.01051 0.00354 -0.0047 0.6159 0.0721
-5.500 -0.5939 0.01028 0.00334 -0.0044 0.6080 0.0816
-5.250 -0.5682 0.01002 0.00314 -0.0040 0.6011 0.0976
-5.000 -0.5411 0.00989 0.00298 -0.0038 0.5951 0.1027
-4.750 -0.5146 0.00971 0.00281 -0.0036 0.5905 0.1106
-4.500 -0.4875 0.00957 0.00267 -0.0034 0.5861 0.1176
-4.250 -0.4608 0.00939 0.00252 -0.0032 0.5816 0.1280
-4.000 -0.4342 0.00921 0.00237 -0.0029 0.5773 0.1413
-3.750 -0.4073 0.00905 0.00223 -0.0027 0.5739 0.1532
-3.500 -0.3805 0.00884 0.00209 -0.0025 0.5705 0.1702
-3.250 -0.3553 0.00847 0.00189 -0.0021 0.5670 0.2134
-3.000 -0.3295 0.00819 0.00173 -0.0018 0.5636 0.2510
-2.750 -0.3034 0.00794 0.00160 -0.0015 0.5605 0.2833
-2.500 -0.2770 0.00767 0.00147 -0.0012 0.5570 0.3211
-2.250 -0.2506 0.00742 0.00137 -0.0009 0.5510 0.3603
-2.000 -0.2239 0.00724 0.00128 -0.0007 0.5443 0.3915
-1.750 -0.1964 0.00712 0.00122 -0.0005 0.5389 0.4114
-1.500 -0.1688 0.00702 0.00117 -0.0004 0.5325 0.4296
-1.250 -0.1409 0.00696 0.00114 -0.0003 0.5278 0.4437
-1.000 -0.1132 0.00690 0.00113 -0.0002 0.5221 0.4668
-0.750 -0.0851 0.00690 0.00113 -0.0001 0.5163 0.4843
-0.500 -0.0568 0.00687 0.00113 0.0000 0.5124 0.4938
-0.250 -0.0283 0.00688 0.00112 0.0000 0.5081 0.4990
0.000 0.0000 0.00690 0.00112 0.0000 0.5030 0.5028
0.250 0.0283 0.00688 0.00112 0.0000 0.4989 0.5081
0.500 0.0568 0.00687 0.00113 0.0000 0.4937 0.5124
0.750 0.0851 0.00690 0.00113 0.0001 0.4830 0.5163
1.000 0.1132 0.00690 0.00113 0.0002 0.4648 0.5221
1.250 0.1409 0.00696 0.00114 0.0003 0.4444 0.5277
1.750 0.1962 0.00713 0.00122 0.0006 0.4090 0.5383
2.000 0.2237 0.00727 0.00129 0.0007 0.3863 0.5443
2.250 0.2505 0.00743 0.00137 0.0009 0.3577 0.5507
2.500 0.2770 0.00766 0.00147 0.0012 0.3213 0.5567
2.750 0.3033 0.00795 0.00160 0.0015 0.2821 0.5605
3.000 0.3296 0.00819 0.00173 0.0018 0.2517 0.5636
3.250 0.3554 0.00847 0.00189 0.0021 0.2145 0.5670
3.500 0.3805 0.00884 0.00209 0.0025 0.1698 0.5705
3.750 0.4072 0.00905 0.00223 0.0027 0.1522 0.5739
4.000 0.4342 0.00922 0.00237 0.0029 0.1407 0.5772
4.250 0.4608 0.00939 0.00252 0.0032 0.1277 0.5816
4.500 0.4875 0.00957 0.00267 0.0034 0.1174 0.5861
4.750 0.5145 0.00972 0.00281 0.0036 0.1103 0.5905
5.000 0.5412 0.00988 0.00298 0.0038 0.1037 0.5952
5.250 0.5682 0.01002 0.00314 0.0040 0.0980 0.6013
5.500 0.5940 0.01027 0.00333 0.0044 0.0823 0.6079
5.750 0.6198 0.01051 0.00354 0.0047 0.0720 0.6160
6.000 0.6459 0.01072 0.00375 0.0050 0.0654 0.6220
6.250 0.6717 0.01093 0.00397 0.0054 0.0598 0.6273
6.500 0.6977 0.01113 0.00418 0.0057 0.0550 0.6319
6.750 0.7229 0.01140 0.00443 0.0061 0.0492 0.6362
7.000 0.7484 0.01160 0.00467 0.0066 0.0474 0.6413
7.250 0.7737 0.01182 0.00492 0.0070 0.0459 0.6471
7.500 0.7985 0.01205 0.00519 0.0075 0.0442 0.6548
8.000 0.8476 0.01254 0.00579 0.0086 0.0416 0.6818
8.250 0.8718 0.01282 0.00612 0.0091 0.0402 0.6948
8.500 0.8956 0.01311 0.00648 0.0098 0.0392 0.7047
8.750 0.9204 0.01331 0.00672 0.0102 0.0384 0.7131
9.000 0.9446 0.01354 0.00700 0.0108 0.0378 0.7218
9.250 0.9685 0.01376 0.00728 0.0114 0.0364 0.7299
9.500 0.9915 0.01402 0.00760 0.0121 0.0349 0.7404
9.750 1.0131 0.01429 0.00795 0.0131 0.0334 0.7551
10.000 1.0331 0.01456 0.00836 0.0143 0.0319 0.8024
10.250 1.0537 0.01494 0.00878 0.0153 0.0303 0.8160
10.500 1.0745 0.01521 0.00914 0.0164 0.0296 0.8306
10.750 1.0934 0.01539 0.00949 0.0179 0.0287 0.8681
11.250 1.1827 0.01641 0.01068 0.0094 0.0219 1.0000
11.500 1.2007 0.01697 0.01121 0.0106 0.0189 1.0000
11.750 1.2182 0.01754 0.01179 0.0118 0.0165 1.0000
12.000 1.2336 0.01820 0.01245 0.0133 0.0139 1.0000
12.250 1.2424 0.01909 0.01332 0.0157 0.0098 1.0000
12.500 1.2509 0.01992 0.01417 0.0180 0.0080 1.0000
12.750 1.2593 0.02090 0.01519 0.0199 0.0066 1.0000
13.000 1.2672 0.02212 0.01646 0.0212 0.0054 1.0000
13.250 1.2789 0.02322 0.01761 0.0218 0.0052 1.0000
13.500 1.2893 0.02456 0.01902 0.0223 0.0047 1.0000
13.750 1.2991 0.02604 0.02056 0.0225 0.0043 1.0000
14.000 1.3076 0.02779 0.02238 0.0224 0.0040 1.0000
14.250 1.3167 0.02950 0.02416 0.0223 0.0039 1.0000
14.500 1.3233 0.03149 0.02622 0.0221 0.0036 1.0000
14.750 1.3315 0.03335 0.02814 0.0219 0.0035 1.0000
15.000 1.3373 0.03549 0.03036 0.0215 0.0035 1.0000
15.250 1.3424 0.03769 0.03263 0.0212 0.0033 1.0000
15.500 1.3449 0.04018 0.03520 0.0207 0.0031 1.0000
15.750 1.3469 0.04276 0.03787 0.0202 0.0031 1.0000
16.000 1.3472 0.04553 0.04072 0.0196 0.0030 1.0000
16.250 1.3468 0.04844 0.04371 0.0189 0.0029 1.0000
16.500 1.3439 0.05169 0.04706 0.0180 0.0029 1.0000
16.750 1.3399 0.05512 0.05058 0.0170 0.0028 1.0000
17.000 1.3363 0.05870 0.05424 0.0158 0.0028 1.0000
17.250 1.3303 0.06270 0.05835 0.0143 0.0028 1.0000
17.500 1.3233 0.06700 0.06275 0.0126 0.0028 1.0000
17.750 1.3131 0.07187 0.06773 0.0106 0.0027 1.0000
18.000 1.3035 0.07678 0.07274 0.0085 0.0027 1.0000
18.250 1.2882 0.08270 0.07878 0.0058 0.0026 1.0000
18.500 1.2740 0.08857 0.08477 0.0031 0.0026 1.0000
18.750 1.2544 0.09547 0.09181 -0.0002 0.0026 1.0000
19.000 1.2363 0.10233 0.09878 -0.0035 0.0026 1.0000
19.250 1.2135 0.11008 0.10667 -0.0073 0.0026 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX LIII-142 K 25 AIRFOIL (fxl142k-il)