FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-147 AIRFOIL (fx63147-il) Reynolds number: 50,000 Max Cl/Cd: 27.46 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63147-il-50000-n5.txt Download as CSV file: xf-fx63147-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-147 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3606 0.10410 0.09727 -0.0491 1.0001 0.0384
-9.750 -0.3674 0.09944 0.09271 -0.0506 1.0001 0.0373
-9.500 -0.3969 0.08962 0.08295 -0.0577 1.0001 0.0346
-9.250 -0.4043 0.08616 0.07956 -0.0578 1.0001 0.0343
-9.000 -0.4168 0.08270 0.07617 -0.0578 1.0001 0.0340
-8.750 -0.4334 0.07958 0.07312 -0.0570 1.0001 0.0337
-8.500 -0.4543 0.07697 0.07056 -0.0551 1.0001 0.0335
-8.250 -0.4781 0.07492 0.06858 -0.0520 1.0001 0.0333
-8.000 -0.4993 0.07264 0.06632 -0.0493 1.0001 0.0331
-7.750 -0.5180 0.07027 0.06394 -0.0465 1.0001 0.0329
-7.500 -0.5341 0.06791 0.06152 -0.0437 1.0001 0.0326
-7.250 -0.5478 0.06547 0.05899 -0.0410 1.0001 0.0324
-7.000 -0.5392 0.06125 0.05446 -0.0432 0.9934 0.0320
-6.750 -0.5204 0.05669 0.04946 -0.0465 0.9832 0.0315
-6.500 -0.4983 0.05248 0.04475 -0.0492 0.9734 0.0312
-6.250 -0.4751 0.04884 0.04062 -0.0511 0.9631 0.0313
-6.000 -0.4489 0.04566 0.03692 -0.0527 0.9532 0.0319
-5.750 -0.4182 0.04275 0.03347 -0.0544 0.9446 0.0330
-5.500 -0.3868 0.04025 0.03042 -0.0555 0.9354 0.0341
-5.250 -0.3570 0.03812 0.02801 -0.0563 0.9260 0.0355
-5.000 -0.3209 0.03624 0.02593 -0.0578 0.9191 0.0369
-4.750 -0.2917 0.03477 0.02426 -0.0576 0.9090 0.0384
-4.500 -0.2548 0.03338 0.02266 -0.0583 0.9026 0.0407
-4.250 -0.2258 0.03233 0.02137 -0.0577 0.8924 0.0433
-4.000 -0.1974 0.03117 0.02017 -0.0580 0.8829 0.0477
-3.750 -0.1651 0.02998 0.01887 -0.0590 0.8747 0.0581
-3.500 -0.1408 0.02876 0.01777 -0.0591 0.8638 0.0877
-3.250 -0.1253 0.02521 0.01633 -0.0594 0.8555 0.3719
-3.000 -0.1210 0.02651 0.01901 -0.0481 0.8459 0.6958
-2.750 -0.1032 0.02884 0.02111 -0.0406 0.8359 0.7862
-2.500 -0.0621 0.03009 0.02194 -0.0387 0.8300 0.8337
-2.250 -0.0316 0.03008 0.02158 -0.0386 0.8203 0.8523
-2.000 0.0155 0.02974 0.02084 -0.0418 0.8139 0.8635
-1.750 0.0469 0.02950 0.02031 -0.0426 0.8037 0.8744
-1.500 0.0888 0.02909 0.01958 -0.0451 0.7972 0.8848
-1.250 0.1173 0.02891 0.01917 -0.0456 0.7863 0.8950
-1.000 0.1611 0.02851 0.01849 -0.0487 0.7790 0.9024
-0.750 0.1882 0.02833 0.01812 -0.0489 0.7690 0.9118
-0.500 0.2292 0.02803 0.01762 -0.0518 0.7600 0.9188
-0.250 0.2665 0.02774 0.01712 -0.0538 0.7519 0.9265
0.000 0.3023 0.02756 0.01681 -0.0559 0.7417 0.9331
0.250 0.3413 0.02726 0.01631 -0.0582 0.7343 0.9393
0.750 0.4065 0.02707 0.01592 -0.0612 0.7145 0.9519
1.000 0.4495 0.02684 0.01557 -0.0645 0.7060 0.9564
1.250 0.4761 0.02690 0.01557 -0.0650 0.6964 0.9625
1.500 0.5170 0.02668 0.01527 -0.0679 0.6890 0.9663
1.750 0.5424 0.02684 0.01542 -0.0683 0.6788 0.9716
2.000 0.5776 0.02677 0.01527 -0.0701 0.6716 0.9758
2.250 0.6062 0.02692 0.01543 -0.0711 0.6618 0.9804
2.500 0.6368 0.02701 0.01552 -0.0723 0.6538 0.9850
2.750 0.6690 0.02709 0.01561 -0.0738 0.6450 0.9893
3.000 0.6960 0.02732 0.01586 -0.0745 0.6362 0.9940
3.250 0.7306 0.02735 0.01593 -0.0762 0.6283 0.9973
3.500 0.7467 0.02777 0.01641 -0.0750 0.6193 0.9999
3.750 0.7674 0.02795 0.01659 -0.0740 0.6124 0.9999
4.000 0.7688 0.02860 0.01732 -0.0700 0.6038 0.9999
4.250 0.7880 0.02882 0.01755 -0.0688 0.5971 0.9999
4.500 0.7864 0.02952 0.01834 -0.0644 0.5888 0.9999
4.750 0.8027 0.02981 0.01870 -0.0627 0.5822 0.9999
5.000 0.7994 0.03053 0.01950 -0.0580 0.5742 0.9999
5.250 0.8117 0.03088 0.01991 -0.0556 0.5673 0.9999
5.500 0.8079 0.03159 0.02069 -0.0509 0.5595 0.9999
5.750 0.8155 0.03201 0.02119 -0.0479 0.5523 0.9999
6.000 0.8137 0.03268 0.02194 -0.0436 0.5447 0.9999
6.250 0.8206 0.03323 0.02256 -0.0407 0.5371 0.9999
6.500 0.8285 0.03390 0.02333 -0.0382 0.5298 0.9999
6.750 0.8361 0.03467 0.02423 -0.0358 0.5219 0.9999
7.000 0.8516 0.03536 0.02502 -0.0347 0.5149 0.9999
7.250 0.8598 0.03642 0.02622 -0.0330 0.5066 0.9999
7.500 0.8781 0.03721 0.02715 -0.0324 0.4995 0.9999
7.750 0.8890 0.03840 0.02851 -0.0314 0.4910 0.9999
8.000 0.8980 0.03975 0.03001 -0.0303 0.4819 0.9999
8.250 0.9265 0.03993 0.03035 -0.0305 0.4744 0.9999
8.500 0.9235 0.04220 0.03279 -0.0290 0.4635 0.9999
8.750 0.9641 0.04159 0.03238 -0.0299 0.4579 0.9999
9.000 0.9513 0.04478 0.03574 -0.0283 0.4461 0.9999
9.250 1.0038 0.04313 0.03430 -0.0294 0.4414 0.9999
9.500 0.9884 0.04655 0.03788 -0.0279 0.4288 0.9999
9.750 0.9813 0.04966 0.04115 -0.0272 0.4166 0.9999
10.000 1.0463 0.04606 0.03782 -0.0276 0.4110 0.9999
10.250 1.0312 0.04967 0.04159 -0.0266 0.3978 0.9999
10.500 1.0223 0.05311 0.04520 -0.0263 0.3848 0.9999
10.750 1.0255 0.05534 0.04760 -0.0261 0.3724 0.9999
11.000 1.0491 0.05499 0.04745 -0.0254 0.3607 0.9999
11.250 1.0794 0.05370 0.04639 -0.0245 0.3480 0.9999
11.500 1.0953 0.05412 0.04698 -0.0239 0.3338 0.9999
11.750 1.1003 0.05585 0.04887 -0.0236 0.3190 0.9999
12.000 1.0986 0.05852 0.05170 -0.0236 0.3034 0.9999
12.250 1.0955 0.06141 0.05473 -0.0239 0.2865 0.9999
12.500 1.0920 0.06445 0.05790 -0.0243 0.2682 0.9999
12.750 1.0968 0.06625 0.05978 -0.0244 0.2477 0.9999
13.000 1.0982 0.06870 0.06228 -0.0246 0.2281 0.9999
13.250 1.0945 0.07215 0.06579 -0.0254 0.2087 0.9999
13.500 1.0954 0.07465 0.06819 -0.0256 0.1874 0.9999
13.750 1.0902 0.07846 0.07197 -0.0266 0.1684 0.9999
14.000 1.0843 0.08250 0.07599 -0.0277 0.1506 0.9999
14.250 1.0787 0.08649 0.07989 -0.0288 0.1353 0.9999
14.500 1.0734 0.09057 0.08393 -0.0300 0.1224 0.9999
14.750 1.0699 0.09462 0.08797 -0.0312 0.1114 0.9999
15.000 1.0664 0.09862 0.09192 -0.0325 0.1019 0.9999
15.250 1.0638 0.10266 0.09597 -0.0339 0.0934 0.9999
15.500 1.0627 0.10646 0.09983 -0.0350 0.0863 0.9999
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