FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-147 AIRFOIL (fx63147-il) Reynolds number: 200,000 Max Cl/Cd: 63.81 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63147-il-200000-n5.txt Download as CSV file: xf-fx63147-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4539 0.06447 0.06101 -0.0641 0.9969 0.0110
-9.000 -0.4612 0.05845 0.05479 -0.0698 0.9903 0.0110
-8.500 -0.4515 0.05326 0.04941 -0.0750 0.9733 0.0117
-8.250 -0.4515 0.04825 0.04411 -0.0764 0.9611 0.0117
-8.000 -0.4440 0.04533 0.04099 -0.0766 0.9497 0.0121
-7.750 -0.4366 0.04157 0.03692 -0.0764 0.9383 0.0123
-7.500 -0.4272 0.03693 0.03181 -0.0760 0.9281 0.0119
-7.250 -0.4140 0.03123 0.02517 -0.0750 0.9193 0.0111
-7.000 -0.3945 0.02898 0.02263 -0.0745 0.9091 0.0110
-6.750 -0.3655 0.02671 0.02005 -0.0755 0.9039 0.0109
-6.500 -0.3413 0.02490 0.01798 -0.0753 0.8938 0.0108
-6.250 -0.3079 0.02310 0.01590 -0.0767 0.8881 0.0108
-6.000 -0.2791 0.02166 0.01427 -0.0770 0.8778 0.0108
-5.750 -0.2442 0.02029 0.01273 -0.0785 0.8694 0.0108
-5.500 -0.2065 0.01905 0.01135 -0.0806 0.8604 0.0108
-5.250 -0.1679 0.01797 0.01014 -0.0831 0.8492 0.0109
-5.000 -0.1267 0.01701 0.00906 -0.0862 0.8372 0.0110
-4.750 -0.0878 0.01619 0.00813 -0.0889 0.8235 0.0113
-4.500 -0.0514 0.01556 0.00736 -0.0911 0.8087 0.0117
-4.250 -0.0185 0.01508 0.00673 -0.0924 0.7935 0.0122
-4.000 0.0118 0.01470 0.00619 -0.0932 0.7781 0.0130
-3.750 0.0408 0.01440 0.00572 -0.0936 0.7637 0.0142
-3.500 0.0687 0.01410 0.00528 -0.0939 0.7500 0.0168
-3.250 0.0950 0.01376 0.00489 -0.0939 0.7363 0.0246
-3.000 0.1210 0.01339 0.00460 -0.0939 0.7230 0.0686
-2.750 0.1450 0.01189 0.00414 -0.0952 0.7104 0.3301
-2.500 0.1745 0.01100 0.00399 -0.0966 0.6986 0.5293
-2.250 0.1964 0.01092 0.00427 -0.0950 0.6872 0.6356
-2.000 0.2150 0.01124 0.00470 -0.0922 0.6757 0.6988
-1.750 0.2384 0.01157 0.00498 -0.0908 0.6649 0.7321
-1.500 0.2599 0.01200 0.00533 -0.0887 0.6552 0.7524
-1.250 0.2802 0.01253 0.00580 -0.0863 0.6457 0.7711
-1.000 0.3052 0.01278 0.00594 -0.0855 0.6371 0.7802
-0.750 0.3292 0.01296 0.00602 -0.0845 0.6288 0.7844
-0.500 0.3580 0.01304 0.00599 -0.0849 0.6205 0.7913
-0.250 0.3826 0.01319 0.00603 -0.0842 0.6125 0.7949
0.000 0.4065 0.01332 0.00611 -0.0833 0.6047 0.7980
0.250 0.4325 0.01345 0.00615 -0.0829 0.5976 0.8024
0.500 0.4623 0.01352 0.00614 -0.0837 0.5900 0.8085
0.750 0.4841 0.01368 0.00625 -0.0822 0.5825 0.8113
1.000 0.5079 0.01380 0.00633 -0.0814 0.5750 0.8147
1.250 0.5347 0.01390 0.00637 -0.0814 0.5676 0.8194
1.500 0.5634 0.01399 0.00641 -0.0819 0.5607 0.8241
1.750 0.5858 0.01411 0.00651 -0.0807 0.5539 0.8265
2.000 0.6104 0.01422 0.00657 -0.0801 0.5479 0.8293
2.250 0.6367 0.01431 0.00667 -0.0800 0.5414 0.8325
2.500 0.6660 0.01441 0.00673 -0.0807 0.5354 0.8361
2.750 0.6952 0.01449 0.00680 -0.0814 0.5291 0.8391
3.000 0.7179 0.01459 0.00691 -0.0804 0.5227 0.8412
3.250 0.7413 0.01472 0.00703 -0.0796 0.5165 0.8438
3.500 0.7659 0.01482 0.00717 -0.0791 0.5093 0.8471
3.750 0.7937 0.01496 0.00727 -0.0795 0.5030 0.8505
4.000 0.8244 0.01507 0.00742 -0.0805 0.4955 0.8536
4.250 0.8467 0.01519 0.00756 -0.0795 0.4892 0.8555
4.500 0.8699 0.01530 0.00772 -0.0788 0.4828 0.8577
4.750 0.8937 0.01542 0.00786 -0.0782 0.4748 0.8600
5.000 0.9180 0.01553 0.00801 -0.0778 0.4642 0.8625
5.250 0.9425 0.01567 0.00814 -0.0776 0.4505 0.8654
5.500 0.9693 0.01584 0.00831 -0.0779 0.4357 0.8683
5.750 0.9885 0.01598 0.00845 -0.0764 0.4242 0.8702
6.000 1.0085 0.01614 0.00864 -0.0751 0.4124 0.8723
6.250 1.0292 0.01633 0.00886 -0.0740 0.3988 0.8748
6.500 1.0507 0.01656 0.00909 -0.0732 0.3838 0.8774
6.750 1.0729 0.01683 0.00936 -0.0727 0.3686 0.8802
7.000 1.0956 0.01717 0.00968 -0.0723 0.3516 0.8827
7.250 1.1107 0.01747 0.00999 -0.0703 0.3347 0.8847
7.500 1.1284 0.01783 0.01035 -0.0689 0.3169 0.8867
7.750 1.1469 0.01824 0.01077 -0.0677 0.3001 0.8889
8.000 1.1648 0.01873 0.01126 -0.0665 0.2822 0.8916
8.250 1.1825 0.01935 0.01185 -0.0655 0.2599 0.8941
8.500 1.1988 0.02016 0.01258 -0.0645 0.2333 0.8964
8.750 1.2102 0.02097 0.01333 -0.0625 0.2066 0.8984
9.000 1.2166 0.02199 0.01424 -0.0599 0.1788 0.9005
9.250 1.2243 0.02304 0.01524 -0.0576 0.1536 0.9030
9.500 1.2301 0.02433 0.01645 -0.0554 0.1302 0.9058
9.750 1.2392 0.02558 0.01768 -0.0538 0.1088 0.9082
10.000 1.2470 0.02706 0.01913 -0.0525 0.0929 0.9103
10.250 1.2528 0.02851 0.02060 -0.0509 0.0787 0.9122
10.500 1.2538 0.03021 0.02228 -0.0487 0.0619 0.9143
10.750 1.2561 0.03198 0.02408 -0.0471 0.0537 0.9167
11.000 1.2610 0.03374 0.02591 -0.0460 0.0435 0.9191
11.250 1.2637 0.03588 0.02808 -0.0451 0.0349 0.9212
11.500 1.2665 0.03820 0.03044 -0.0446 0.0313 0.9231
11.750 1.2702 0.04059 0.03291 -0.0444 0.0286 0.9247
12.000 1.2745 0.04255 0.03501 -0.0437 0.0267 0.9267
12.250 1.2773 0.04468 0.03728 -0.0430 0.0245 0.9289
12.500 1.2792 0.04710 0.03982 -0.0426 0.0227 0.9310
12.750 1.2805 0.04972 0.04257 -0.0425 0.0214 0.9329
13.000 1.2837 0.05230 0.04529 -0.0426 0.0203 0.9346
13.250 1.2863 0.05505 0.04817 -0.0429 0.0191 0.9362
13.500 1.2877 0.05798 0.05121 -0.0433 0.0179 0.9377
13.750 1.2874 0.06107 0.05439 -0.0436 0.0169 0.9392
14.000 1.2855 0.06410 0.05754 -0.0436 0.0163 0.9411
14.250 1.2836 0.06724 0.06081 -0.0438 0.0159 0.9433
14.500 1.2816 0.07051 0.06420 -0.0441 0.0154 0.9453
14.750 1.2798 0.07399 0.06780 -0.0448 0.0150 0.9471
15.000 1.2773 0.07760 0.07154 -0.0456 0.0146 0.9488
15.250 1.2746 0.08142 0.07549 -0.0465 0.0143 0.9503
15.750 1.2652 0.08929 0.08361 -0.0483 0.0136 0.9536
16.000 1.2587 0.09346 0.08789 -0.0492 0.0132 0.9554
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