FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il) Reynolds number: 200,000 Max Cl/Cd: 54.84 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxl142k-il-200000.txt Download as CSV file: xf-fxl142k-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7142 0.18196 0.17817 0.0345 1.0000 0.0470
-16.500 -0.9370 0.11121 0.10740 -0.0022 1.0000 0.0363
-16.000 -1.0729 0.07802 0.07316 -0.0211 1.0000 0.0311
-15.750 -1.0643 0.07634 0.07161 -0.0222 1.0000 0.0332
-15.500 -1.0749 0.07165 0.06680 -0.0245 1.0000 0.0346
-15.250 -1.0831 0.06769 0.06271 -0.0268 1.0000 0.0361
-15.000 -1.0971 0.06306 0.05786 -0.0289 1.0000 0.0375
-14.750 -1.1072 0.05946 0.05405 -0.0307 1.0000 0.0386
-14.500 -1.1226 0.05455 0.04893 -0.0316 1.0000 0.0403
-14.250 -1.1196 0.05239 0.04681 -0.0320 1.0000 0.0422
-14.000 -1.1182 0.05040 0.04479 -0.0326 1.0000 0.0442
-13.750 -1.1207 0.04810 0.04235 -0.0329 1.0000 0.0462
-13.500 -1.1237 0.04564 0.03969 -0.0329 1.0000 0.0477
-13.250 -1.1288 0.04382 0.03765 -0.0326 1.0000 0.0490
-13.000 -1.1256 0.04107 0.03484 -0.0319 1.0000 0.0514
-12.750 -1.1180 0.03969 0.03346 -0.0312 1.0000 0.0532
-12.500 -1.1135 0.03846 0.03216 -0.0302 1.0000 0.0552
-12.250 -1.1100 0.03731 0.03089 -0.0287 1.0000 0.0573
-12.000 -1.1088 0.03643 0.02983 -0.0264 1.0000 0.0594
-11.750 -1.1082 0.03559 0.02879 -0.0236 1.0000 0.0611
-11.500 -1.0916 0.03332 0.02656 -0.0233 1.0000 0.0646
-11.250 -1.0791 0.03242 0.02562 -0.0219 1.0000 0.0672
-11.000 -1.0641 0.03119 0.02427 -0.0206 1.0000 0.0692
-10.750 -1.0470 0.02994 0.02286 -0.0195 1.0000 0.0711
-10.500 -1.0300 0.02891 0.02166 -0.0184 1.0000 0.0728
-10.250 -1.0103 0.02739 0.02003 -0.0176 1.0000 0.0749
-10.000 -0.9902 0.02604 0.01869 -0.0169 1.0000 0.0775
-9.750 -0.9712 0.02509 0.01772 -0.0159 1.0000 0.0798
-9.500 -0.9519 0.02419 0.01678 -0.0149 1.0000 0.0822
-9.250 -0.9324 0.02335 0.01586 -0.0138 1.0000 0.0847
-9.000 -0.9131 0.02248 0.01492 -0.0127 1.0000 0.0875
-8.750 -0.8958 0.02145 0.01398 -0.0115 1.0000 0.0912
-8.500 -0.8767 0.02073 0.01323 -0.0104 1.0000 0.0953
-8.250 -0.8566 0.02007 0.01249 -0.0092 1.0000 0.0997
-8.000 -0.8406 0.01903 0.01155 -0.0077 1.0000 0.1060
-7.750 -0.8209 0.01837 0.01085 -0.0066 1.0000 0.1150
-7.500 -0.8047 0.01741 0.01002 -0.0051 1.0000 0.1277
-7.250 -0.7872 0.01657 0.00925 -0.0037 1.0000 0.1456
-7.000 -0.7714 0.01561 0.00846 -0.0021 1.0000 0.1664
-6.750 -0.7540 0.01482 0.00782 -0.0008 1.0000 0.1910
-6.500 -0.7374 0.01404 0.00728 0.0007 1.0000 0.2236
-6.250 -0.7229 0.01329 0.00681 0.0024 1.0000 0.2660
-6.000 -0.6833 0.01246 0.00637 -0.0011 0.9722 0.3402
-5.750 -0.6361 0.01206 0.00613 -0.0054 0.9401 0.3996
-5.500 -0.5951 0.01196 0.00605 -0.0080 0.9050 0.4370
-5.250 -0.5618 0.01205 0.00605 -0.0088 0.8758 0.4611
-5.000 -0.5344 0.01218 0.00601 -0.0084 0.8515 0.4794
-4.750 -0.5087 0.01229 0.00597 -0.0077 0.8324 0.4952
-4.500 -0.4833 0.01241 0.00598 -0.0069 0.8163 0.5092
-4.250 -0.4576 0.01253 0.00604 -0.0062 0.8015 0.5222
-4.000 -0.4316 0.01263 0.00607 -0.0056 0.7874 0.5346
-3.750 -0.4058 0.01273 0.00607 -0.0049 0.7754 0.5471
-3.500 -0.3794 0.01281 0.00607 -0.0043 0.7658 0.5577
-3.250 -0.3529 0.01290 0.00609 -0.0037 0.7572 0.5678
-3.000 -0.3265 0.01299 0.00608 -0.0032 0.7484 0.5782
-2.750 -0.2993 0.01312 0.00614 -0.0028 0.7411 0.5866
-2.500 -0.2723 0.01319 0.00620 -0.0025 0.7328 0.5954
-2.250 -0.2458 0.01335 0.00623 -0.0021 0.7261 0.6059
-2.000 -0.2185 0.01338 0.00633 -0.0017 0.7184 0.6141
-1.750 -0.1917 0.01344 0.00632 -0.0014 0.7121 0.6232
-1.500 -0.1646 0.01346 0.00636 -0.0011 0.7058 0.6317
-1.250 -0.1373 0.01343 0.00632 -0.0009 0.6995 0.6385
-1.000 -0.1098 0.01346 0.00632 -0.0007 0.6940 0.6450
-0.750 -0.0825 0.01341 0.00629 -0.0006 0.6872 0.6515
-0.500 -0.0549 0.01342 0.00630 -0.0003 0.6816 0.6570
-0.250 -0.0276 0.01342 0.00627 -0.0002 0.6751 0.6637
0.000 0.0000 0.01339 0.00627 0.0000 0.6687 0.6687
0.250 0.0276 0.01342 0.00627 0.0002 0.6637 0.6751
0.500 0.0549 0.01342 0.00629 0.0003 0.6570 0.6816
0.750 0.0825 0.01341 0.00629 0.0006 0.6515 0.6872
1.000 0.1098 0.01346 0.00632 0.0007 0.6450 0.6940
1.250 0.1373 0.01343 0.00632 0.0009 0.6385 0.6995
1.500 0.1646 0.01346 0.00636 0.0011 0.6317 0.7058
1.750 0.1917 0.01344 0.00632 0.0014 0.6233 0.7121
2.000 0.2185 0.01337 0.00632 0.0018 0.6138 0.7183
2.250 0.2458 0.01335 0.00622 0.0021 0.6057 0.7260
2.500 0.2723 0.01319 0.00619 0.0025 0.5953 0.7328
2.750 0.2993 0.01312 0.00614 0.0028 0.5865 0.7411
3.000 0.3265 0.01299 0.00609 0.0032 0.5782 0.7485
3.250 0.3529 0.01290 0.00608 0.0037 0.5678 0.7572
3.500 0.3794 0.01281 0.00607 0.0043 0.5575 0.7659
3.750 0.4058 0.01273 0.00605 0.0050 0.5469 0.7754
4.000 0.4317 0.01264 0.00608 0.0056 0.5349 0.7874
4.250 0.4576 0.01253 0.00604 0.0062 0.5223 0.8015
4.500 0.4832 0.01240 0.00598 0.0069 0.5090 0.8163
4.750 0.5087 0.01229 0.00597 0.0077 0.4948 0.8324
5.000 0.5344 0.01218 0.00601 0.0084 0.4795 0.8514
5.250 0.5618 0.01205 0.00605 0.0088 0.4611 0.8758
5.500 0.5951 0.01196 0.00605 0.0080 0.4370 0.9050
5.750 0.6360 0.01206 0.00613 0.0054 0.3999 0.9401
6.000 0.6833 0.01246 0.00637 0.0011 0.3401 0.9722
6.250 0.7229 0.01330 0.00681 -0.0024 0.2658 1.0000
6.500 0.7373 0.01405 0.00728 -0.0007 0.2234 1.0000
6.750 0.7540 0.01482 0.00782 0.0008 0.1910 1.0000
7.000 0.7714 0.01561 0.00846 0.0021 0.1664 1.0000
7.250 0.7874 0.01656 0.00925 0.0037 0.1458 1.0000
7.500 0.8047 0.01741 0.01002 0.0051 0.1276 1.0000
7.750 0.8209 0.01837 0.01085 0.0066 0.1148 1.0000
8.000 0.8406 0.01903 0.01155 0.0077 0.1060 1.0000
8.250 0.8566 0.02007 0.01248 0.0092 0.0998 1.0000
8.500 0.8768 0.02073 0.01323 0.0103 0.0953 1.0000
8.750 0.8958 0.02145 0.01397 0.0115 0.0911 1.0000
9.000 0.9131 0.02250 0.01493 0.0127 0.0874 1.0000
9.250 0.9325 0.02334 0.01585 0.0138 0.0846 1.0000
9.500 0.9520 0.02419 0.01677 0.0149 0.0821 1.0000
9.750 0.9712 0.02508 0.01771 0.0159 0.0796 1.0000
10.000 0.9903 0.02603 0.01868 0.0169 0.0775 1.0000
10.250 1.0105 0.02742 0.02005 0.0176 0.0748 1.0000
10.500 1.0301 0.02890 0.02166 0.0184 0.0728 1.0000
10.750 1.0471 0.02994 0.02286 0.0195 0.0710 1.0000
11.000 1.0643 0.03120 0.02427 0.0206 0.0692 1.0000
11.250 1.0789 0.03237 0.02557 0.0219 0.0670 1.0000
11.500 1.0919 0.03334 0.02658 0.0232 0.0646 1.0000
12.000 1.1092 0.03647 0.02987 0.0263 0.0594 1.0000
12.250 1.1112 0.03748 0.03107 0.0286 0.0575 1.0000
12.500 1.1138 0.03844 0.03214 0.0301 0.0552 1.0000
12.750 1.1187 0.03975 0.03352 0.0312 0.0533 1.0000
13.000 1.1262 0.04097 0.03471 0.0318 0.0512 1.0000
13.250 1.1289 0.04379 0.03763 0.0325 0.0490 1.0000
13.500 1.1245 0.04575 0.03981 0.0329 0.0477 1.0000
13.750 1.1214 0.04803 0.04228 0.0328 0.0460 1.0000
14.000 1.1192 0.05034 0.04471 0.0324 0.0441 1.0000
14.250 1.1200 0.05254 0.04698 0.0319 0.0424 1.0000
14.500 1.1239 0.05452 0.04890 0.0315 0.0403 1.0000
14.750 1.1087 0.05956 0.05414 0.0307 0.0387 1.0000
15.000 1.0965 0.06340 0.05821 0.0288 0.0376 1.0000
15.250 1.0841 0.06774 0.06276 0.0266 0.0363 1.0000
15.500 1.0731 0.07218 0.06737 0.0243 0.0350 1.0000
15.750 1.0639 0.07662 0.07192 0.0219 0.0334 1.0000
16.000 1.0736 0.07812 0.07326 0.0209 0.0311 1.0000
16.250 1.0611 0.08348 0.07872 0.0186 0.0303 1.0000
16.500 1.0346 0.09165 0.08712 0.0139 0.0297 1.0000
16.750 1.0108 0.09992 0.09562 0.0090 0.0295 1.0000
17.000 0.9801 0.11003 0.10593 0.0030 0.0297 1.0000
17.250 0.9429 0.12219 0.11828 -0.0044 0.0300 1.0000
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Polar data table (+)
Polar graphs
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