FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-147 AIRFOIL (fx63147-il) Reynolds number: 200,000 Max Cl/Cd: 68.55 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63147-il-200000.txt Download as CSV file: xf-fx63147-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3122 0.08927 0.08648 -0.0395 1.0001 0.0499
-9.000 -0.4035 0.08515 0.08209 -0.0502 1.0001 0.0449
-8.750 -0.4315 0.07986 0.07684 -0.0525 1.0001 0.0447
-8.000 -0.4809 0.07043 0.06738 -0.0540 0.9922 0.0455
-7.750 -0.4638 0.06570 0.06254 -0.0600 0.9848 0.0474
-7.500 -0.4542 0.06030 0.05667 -0.0664 0.9721 0.0518
-7.250 -0.4454 0.05442 0.05052 -0.0698 0.9622 0.0545
-7.000 -0.4213 0.05181 0.04797 -0.0713 0.9552 0.0579
-6.500 -0.3787 0.04453 0.04021 -0.0759 0.9383 0.0693
-6.250 -0.3493 0.04077 0.03590 -0.0793 0.9332 0.0784
-6.000 -0.3260 0.03792 0.03305 -0.0798 0.9231 0.0816
-5.750 -0.2834 0.02969 0.02307 -0.0785 0.9195 0.0350
-5.500 -0.2559 0.02605 0.01935 -0.0785 0.9115 0.0309
-5.250 -0.2174 0.02341 0.01617 -0.0793 0.9071 0.0271
-5.000 -0.1776 0.02127 0.01389 -0.0810 0.9043 0.0260
-4.750 -0.1476 0.01977 0.01228 -0.0809 0.8947 0.0254
-4.500 -0.1067 0.01826 0.01070 -0.0830 0.8901 0.0251
-4.250 -0.0724 0.01711 0.00953 -0.0842 0.8802 0.0254
-4.000 -0.0261 0.01592 0.00828 -0.0880 0.8740 0.0264
-3.500 0.0511 0.01436 0.00650 -0.0928 0.8498 0.0335
-3.250 0.0863 0.01229 0.00543 -0.0961 0.8364 0.2672
-3.000 0.1185 0.01080 0.00541 -0.0980 0.8226 0.6234
-2.750 0.1407 0.01136 0.00612 -0.0952 0.8083 0.7157
-2.500 0.1675 0.01193 0.00655 -0.0938 0.7943 0.7440
-2.250 0.1933 0.01253 0.00699 -0.0923 0.7804 0.7630
-2.000 0.2119 0.01340 0.00776 -0.0886 0.7667 0.7789
-1.750 0.2299 0.01422 0.00847 -0.0850 0.7536 0.7934
-1.500 0.2471 0.01502 0.00919 -0.0808 0.7417 0.8037
-1.250 0.2667 0.01589 0.00995 -0.0769 0.7312 0.8192
-1.000 0.2903 0.01625 0.01018 -0.0749 0.7209 0.8287
-0.750 0.3127 0.01630 0.01013 -0.0743 0.7100 0.8387
-0.500 0.3381 0.01636 0.01007 -0.0732 0.7007 0.8423
-0.250 0.3621 0.01642 0.01003 -0.0723 0.6910 0.8489
0.000 0.3845 0.01645 0.00998 -0.0712 0.6818 0.8562
0.250 0.4114 0.01648 0.00988 -0.0709 0.6737 0.8611
0.500 0.4309 0.01648 0.00984 -0.0697 0.6643 0.8690
0.750 0.4581 0.01645 0.00970 -0.0693 0.6564 0.8727
1.000 0.4786 0.01645 0.00967 -0.0680 0.6472 0.8797
1.250 0.5032 0.01644 0.00958 -0.0674 0.6399 0.8855
1.500 0.5261 0.01640 0.00952 -0.0664 0.6315 0.8910
1.750 0.5482 0.01646 0.00950 -0.0657 0.6246 0.8974
2.000 0.5719 0.01635 0.00939 -0.0648 0.6166 0.9014
2.250 0.5993 0.01638 0.00933 -0.0649 0.6103 0.9066
2.500 0.6165 0.01635 0.00935 -0.0631 0.6027 0.9129
2.750 0.6455 0.01632 0.00925 -0.0635 0.5962 0.9163
3.000 0.6646 0.01631 0.00927 -0.0621 0.5886 0.9210
3.250 0.6861 0.01634 0.00925 -0.0612 0.5818 0.9257
3.500 0.7096 0.01626 0.00922 -0.0606 0.5744 0.9290
3.750 0.7343 0.01625 0.00918 -0.0602 0.5673 0.9325
4.000 0.7535 0.01630 0.00924 -0.0589 0.5605 0.9371
4.250 0.7763 0.01626 0.00921 -0.0582 0.5533 0.9408
4.500 0.8033 0.01628 0.00924 -0.0583 0.5468 0.9445
4.750 0.8218 0.01629 0.00931 -0.0569 0.5395 0.9491
5.000 0.8471 0.01638 0.00934 -0.0567 0.5332 0.9521
5.250 0.8662 0.01625 0.00932 -0.0553 0.5237 0.9556
5.500 0.8869 0.01618 0.00924 -0.0542 0.5139 0.9593
5.750 0.9036 0.01610 0.00914 -0.0523 0.5038 0.9630
6.000 0.9209 0.01598 0.00909 -0.0506 0.4930 0.9663
6.250 0.9445 0.01596 0.00908 -0.0501 0.4838 0.9697
6.500 0.9626 0.01592 0.00907 -0.0486 0.4742 0.9735
6.750 0.9810 0.01588 0.00911 -0.0472 0.4633 0.9768
7.000 1.0053 0.01590 0.00916 -0.0470 0.4532 0.9801
7.250 1.0253 0.01592 0.00921 -0.0460 0.4427 0.9838
7.500 1.0462 0.01597 0.00936 -0.0453 0.4315 0.9875
7.750 1.0673 0.01604 0.00949 -0.0446 0.4198 0.9915
8.000 1.0883 0.01618 0.00965 -0.0439 0.4098 0.9950
8.250 1.1131 0.01633 0.00989 -0.0441 0.3977 0.9978
8.500 1.1256 0.01642 0.01008 -0.0418 0.3871 0.9999
8.750 1.1381 0.01663 0.01034 -0.0397 0.3763 0.9999
9.000 1.1539 0.01692 0.01068 -0.0383 0.3640 0.9999
9.250 1.1708 0.01731 0.01110 -0.0372 0.3503 0.9999
9.500 1.1892 0.01776 0.01164 -0.0365 0.3355 0.9999
9.750 1.2068 0.01830 0.01224 -0.0357 0.3189 0.9999
10.000 1.2242 0.01892 0.01293 -0.0351 0.3004 0.9999
10.250 1.2389 0.01973 0.01375 -0.0342 0.2793 0.9999
10.500 1.2492 0.02083 0.01481 -0.0331 0.2493 0.9999
10.750 1.2543 0.02235 0.01622 -0.0316 0.2168 0.9999
11.000 1.2553 0.02433 0.01804 -0.0302 0.1788 0.9999
11.250 1.2532 0.02675 0.02029 -0.0289 0.1418 0.9999
11.500 1.2493 0.02952 0.02292 -0.0280 0.1103 0.9999
11.750 1.2443 0.03261 0.02589 -0.0275 0.0865 0.9999
12.000 1.2408 0.03574 0.02898 -0.0273 0.0662 0.9999
12.250 1.2357 0.03917 0.03236 -0.0273 0.0571 0.9999
12.500 1.2361 0.04224 0.03554 -0.0278 0.0500 0.9999
12.750 1.2334 0.04570 0.03908 -0.0283 0.0455 0.9999
13.000 1.2344 0.04884 0.04234 -0.0290 0.0424 0.9999
13.250 1.2363 0.05194 0.04557 -0.0297 0.0398 0.9999
13.500 1.2357 0.05535 0.04906 -0.0306 0.0378 0.9999
13.750 1.2312 0.05927 0.05305 -0.0315 0.0361 0.9999
14.000 1.2323 0.06263 0.05653 -0.0325 0.0348 0.9999
14.250 1.2328 0.06606 0.06009 -0.0335 0.0336 0.9999
14.500 1.2327 0.06955 0.06369 -0.0345 0.0326 0.9999
14.750 1.2328 0.07313 0.06738 -0.0356 0.0316 0.9999
15.000 1.2320 0.07676 0.07110 -0.0366 0.0306 0.9999
15.250 1.2307 0.08043 0.07483 -0.0376 0.0296 0.9999
15.500 1.2290 0.08376 0.07817 -0.0380 0.0282 0.9999
15.750 1.2325 0.08719 0.08181 -0.0394 0.0270 0.9999
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