FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-147 AIRFOIL (fx63147-il) Reynolds number: 100,000 Max Cl/Cd: 47.61 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63147-il-100000.txt Download as CSV file: xf-fx63147-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3650 0.09810 0.09367 -0.0428 1.0001 0.1117
-8.750 -0.3920 0.09454 0.09026 -0.0450 1.0001 0.1154
-8.500 -0.4330 0.09079 0.08666 -0.0473 1.0001 0.1162
-8.250 -0.4679 0.08877 0.08475 -0.0452 1.0001 0.1163
-8.000 -0.4187 0.08591 0.08191 -0.0409 1.0001 0.1233
-7.750 -0.4466 0.08342 0.07955 -0.0394 1.0001 0.1246
-7.500 -0.4824 0.08183 0.07807 -0.0360 1.0001 0.1241
-7.250 -0.5148 0.08012 0.07644 -0.0332 1.0001 0.1242
-7.000 -0.5416 0.07821 0.07457 -0.0310 1.0001 0.1254
-6.750 -0.5333 0.07234 0.06854 -0.0387 0.9901 0.1351
-6.500 -0.5163 0.06735 0.06337 -0.0449 0.9785 0.1488
-5.500 -0.4005 0.04192 0.03508 -0.0605 0.9400 0.0657
-5.250 -0.3560 0.03780 0.03013 -0.0627 0.9343 0.0520
-5.000 -0.3235 0.03471 0.02681 -0.0639 0.9253 0.0493
-4.750 -0.2795 0.03182 0.02340 -0.0662 0.9200 0.0461
-4.500 -0.2452 0.02993 0.02118 -0.0667 0.9105 0.0448
-4.250 -0.2019 0.02806 0.01917 -0.0687 0.9052 0.0450
-4.000 -0.1713 0.02674 0.01784 -0.0688 0.8952 0.0462
-3.750 -0.1288 0.02527 0.01639 -0.0710 0.8899 0.0493
-3.500 -0.0989 0.02418 0.01532 -0.0715 0.8794 0.0556
-3.250 -0.0538 0.02260 0.01374 -0.0745 0.8747 0.0768
-3.000 -0.0518 0.01969 0.01403 -0.0689 0.8644 0.6466
-2.750 -0.0292 0.02144 0.01572 -0.0625 0.8587 0.7624
-2.500 -0.0169 0.02283 0.01699 -0.0560 0.8469 0.7935
-2.250 0.0233 0.02478 0.01874 -0.0513 0.8438 0.8379
-2.000 0.1334 0.02543 0.01899 -0.0610 0.8450 0.8803
-1.750 0.2037 0.02465 0.01793 -0.0689 0.8388 0.8913
-1.500 0.2634 0.02388 0.01692 -0.0751 0.8306 0.9025
-1.250 0.3039 0.02339 0.01624 -0.0778 0.8196 0.9132
-1.000 0.3593 0.02268 0.01531 -0.0834 0.8110 0.9223
-0.750 0.4025 0.02216 0.01464 -0.0867 0.7992 0.9318
-0.500 0.4384 0.02181 0.01417 -0.0888 0.7874 0.9420
-0.250 0.4728 0.02153 0.01376 -0.0906 0.7766 0.9508
0.000 0.5177 0.02101 0.01309 -0.0944 0.7665 0.9579
0.250 0.5466 0.02085 0.01286 -0.0953 0.7548 0.9657
0.500 0.5829 0.02060 0.01253 -0.0977 0.7443 0.9732
0.750 0.6262 0.02020 0.01201 -0.1013 0.7351 0.9800
1.000 0.6588 0.02004 0.01183 -0.1030 0.7236 0.9871
1.250 0.6944 0.01986 0.01159 -0.1054 0.7132 0.9928
1.500 0.7348 0.01958 0.01123 -0.1084 0.7042 0.9976
1.750 0.7590 0.01969 0.01137 -0.1086 0.6936 0.9999
2.000 0.7795 0.01987 0.01150 -0.1077 0.6850 0.9999
2.250 0.7987 0.02006 0.01169 -0.1067 0.6760 0.9999
2.500 0.8163 0.02035 0.01202 -0.1054 0.6675 0.9999
2.750 0.8377 0.02053 0.01218 -0.1046 0.6596 0.9999
3.000 0.8526 0.02088 0.01258 -0.1028 0.6508 0.9999
3.250 0.8760 0.02102 0.01268 -0.1023 0.6433 0.9999
3.500 0.8880 0.02145 0.01320 -0.1000 0.6343 0.9999
3.750 0.9132 0.02154 0.01327 -0.0998 0.6272 0.9999
4.000 0.9222 0.02201 0.01386 -0.0969 0.6177 0.9999
4.250 0.9497 0.02208 0.01388 -0.0970 0.6110 0.9999
4.500 0.9546 0.02267 0.01463 -0.0934 0.6019 0.9999
4.750 0.9824 0.02278 0.01470 -0.0936 0.5955 0.9999
5.000 0.9843 0.02344 0.01553 -0.0894 0.5866 0.9999
5.250 1.0115 0.02357 0.01565 -0.0895 0.5804 0.9999
5.500 1.0108 0.02432 0.01658 -0.0850 0.5721 0.9999
5.750 1.0371 0.02444 0.01669 -0.0848 0.5655 0.9999
6.000 1.0356 0.02513 0.01754 -0.0801 0.5570 0.9999
6.250 1.0648 0.02511 0.01753 -0.0803 0.5498 0.9999
6.500 1.0584 0.02587 0.01845 -0.0747 0.5414 0.9999
6.750 1.0903 0.02578 0.01835 -0.0753 0.5341 0.9999
7.000 1.0788 0.02655 0.01930 -0.0689 0.5256 0.9999
7.250 1.1056 0.02626 0.01902 -0.0684 0.5158 0.9999
7.500 1.1155 0.02621 0.01902 -0.0651 0.5052 0.9999
7.750 1.1150 0.02633 0.01923 -0.0601 0.4948 0.9999
8.000 1.1327 0.02598 0.01888 -0.0580 0.4835 0.9999
8.250 1.1562 0.02546 0.01832 -0.0568 0.4713 0.9999
8.500 1.1520 0.02570 0.01873 -0.0514 0.4610 0.9999
8.750 1.1642 0.02569 0.01881 -0.0489 0.4497 0.9999
9.000 1.1840 0.02554 0.01872 -0.0476 0.4379 0.9999
9.250 1.2061 0.02537 0.01858 -0.0466 0.4256 0.9999
9.500 1.2175 0.02558 0.01897 -0.0444 0.4132 0.9999
9.750 1.2294 0.02585 0.01941 -0.0423 0.4007 0.9999
10.000 1.2436 0.02612 0.01983 -0.0406 0.3878 0.9999
10.250 1.2572 0.02644 0.02028 -0.0390 0.3738 0.9999
10.500 1.2690 0.02687 0.02085 -0.0372 0.3587 0.9999
10.750 1.2776 0.02745 0.02157 -0.0352 0.3416 0.9999
11.000 1.2835 0.02822 0.02244 -0.0332 0.3227 0.9999
11.250 1.2871 0.02933 0.02366 -0.0312 0.3025 0.9999
11.500 1.2863 0.03087 0.02529 -0.0293 0.2791 0.9999
11.750 1.2812 0.03299 0.02745 -0.0277 0.2515 0.9999
12.000 1.2714 0.03581 0.03019 -0.0263 0.2214 0.9999
12.250 1.2570 0.03947 0.03373 -0.0255 0.1900 0.9999
12.500 1.2398 0.04379 0.03790 -0.0252 0.1628 0.9999
12.750 1.2221 0.04846 0.04243 -0.0253 0.1401 0.9999
13.000 1.2057 0.05320 0.04704 -0.0256 0.1225 0.9999
13.250 1.1928 0.05773 0.05148 -0.0259 0.1077 0.9999
13.500 1.1844 0.06176 0.05543 -0.0262 0.0965 0.9999
13.750 1.1822 0.06493 0.05851 -0.0259 0.0874 0.9999
14.000 1.1856 0.06747 0.06102 -0.0254 0.0800 0.9999
14.250 1.1949 0.06933 0.06290 -0.0246 0.0739 0.9999
14.500 1.2021 0.07162 0.06523 -0.0245 0.0692 0.9999
14.750 1.2155 0.07311 0.06667 -0.0236 0.0648 0.9999
15.000 1.2231 0.07557 0.06934 -0.0235 0.0616 0.9999
15.250 1.2330 0.07771 0.07153 -0.0234 0.0584 0.9999
15.500 1.2484 0.07929 0.07309 -0.0223 0.0544 0.9999
15.750 1.2435 0.08344 0.07757 -0.0237 0.0523 0.9999
16.000 1.2389 0.08755 0.08191 -0.0252 0.0496 0.9999
16.250 1.2405 0.09068 0.08502 -0.0263 0.0461 0.9999
16.500 1.2376 0.09474 0.08923 -0.0273 0.0435 0.9999
16.750 1.2273 0.09999 0.09479 -0.0297 0.0417 0.9999
17.000 1.2197 0.10500 0.10002 -0.0320 0.0396 0.9999
17.250 1.2223 0.10816 0.10315 -0.0331 0.0369 0.9999
17.500 1.2141 0.11349 0.10867 -0.0349 0.0355 0.9999
17.750 1.1978 0.12044 0.11593 -0.0388 0.0351 0.9999
18.000 1.1805 0.12784 0.12361 -0.0433 0.0349 0.9999
18.250 1.1621 0.13584 0.13187 -0.0485 0.0349 0.9999
18.500 1.1433 0.14423 0.14048 -0.0541 0.0350 0.9999
18.750 1.1239 0.15337 0.14981 -0.0606 0.0353 0.9999
19.000 1.1044 0.16297 0.15956 -0.0673 0.0357 0.9999
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