FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-147 AIRFOIL (fx63147-il) Reynolds number: 500,000 Max Cl/Cd: 84.43 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63147-il-500000.txt Download as CSV file: xf-fx63147-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2737 0.11716 0.11513 -0.0385 1.0001 0.0176
-11.500 -0.2810 0.11245 0.11044 -0.0400 1.0001 0.0179
-11.250 -0.2877 0.10796 0.10597 -0.0411 1.0001 0.0180
-11.000 -0.2928 0.10368 0.10171 -0.0420 1.0000 0.0180
-10.750 -0.2935 0.09787 0.09592 -0.0445 0.9991 0.0182
-10.500 -0.2856 0.09415 0.09220 -0.0463 0.9979 0.0185
-10.250 -0.2793 0.08966 0.08772 -0.0491 0.9967 0.0188
-10.000 -0.2748 0.08474 0.08279 -0.0521 0.9956 0.0191
-9.750 -0.2718 0.07895 0.07701 -0.0560 0.9945 0.0193
-9.500 -0.2739 0.07257 0.07063 -0.0600 0.9925 0.0195
-9.250 -0.2815 0.06441 0.06249 -0.0659 0.9900 0.0197
-9.000 -0.3101 0.05223 0.05020 -0.0767 0.9869 0.0194
-8.750 -0.3290 0.04534 0.04318 -0.0821 0.9819 0.0193
-8.500 -0.3408 0.04034 0.03804 -0.0851 0.9750 0.0195
-8.250 -0.3497 0.03648 0.03403 -0.0860 0.9644 0.0197
-8.000 -0.3481 0.03232 0.02968 -0.0873 0.9551 0.0201
-7.750 -0.3408 0.02786 0.02497 -0.0885 0.9486 0.0209
-7.500 -0.3372 0.02496 0.02142 -0.0870 0.9361 0.0225
-7.250 -0.3315 0.01938 0.01569 -0.0870 0.9285 0.0233
-7.000 -0.3100 0.01709 0.01332 -0.0877 0.9211 0.0240
-6.750 -0.2863 0.01503 0.01108 -0.0885 0.9124 0.0252
-5.750 -0.1972 0.01824 0.01243 -0.0907 0.8972 0.0183
-5.500 -0.1534 0.01584 0.00975 -0.0931 0.8895 0.0144
-5.250 -0.1094 0.01457 0.00842 -0.0965 0.8774 0.0138
-5.000 -0.0671 0.01342 0.00719 -0.0997 0.8624 0.0134
-4.750 -0.0312 0.01261 0.00625 -0.1017 0.8434 0.0132
-4.500 -0.0029 0.01205 0.00557 -0.1021 0.8220 0.0130
-4.250 0.0235 0.01162 0.00501 -0.1020 0.8019 0.0130
-4.000 0.0487 0.01128 0.00454 -0.1017 0.7832 0.0131
-3.750 0.0737 0.01103 0.00416 -0.1013 0.7656 0.0133
-3.500 0.0984 0.01084 0.00384 -0.1008 0.7482 0.0137
-3.250 0.1234 0.01066 0.00355 -0.1004 0.7318 0.0146
-3.000 0.1492 0.01052 0.00329 -0.1001 0.7171 0.0169
-2.750 0.1750 0.01031 0.00304 -0.0999 0.7036 0.0320
-2.500 0.2017 0.01014 0.00289 -0.0999 0.6910 0.0644
-2.250 0.2292 0.00959 0.00268 -0.1007 0.6793 0.1781
-2.000 0.2624 0.00867 0.00244 -0.1032 0.6681 0.3920
-1.750 0.3042 0.00792 0.00230 -0.1075 0.6571 0.5883
-1.500 0.3362 0.00779 0.00255 -0.1084 0.6467 0.7047
-1.250 0.3630 0.00797 0.00276 -0.1080 0.6377 0.7379
-1.000 0.3897 0.00817 0.00290 -0.1077 0.6285 0.7545
-0.750 0.4162 0.00836 0.00306 -0.1072 0.6194 0.7667
-0.250 0.4638 0.00902 0.00365 -0.1048 0.6024 0.7929
0.000 0.4801 0.00941 0.00401 -0.1018 0.5954 0.7981
0.250 0.5043 0.00964 0.00423 -0.1008 0.5879 0.8048
0.500 0.5303 0.00982 0.00434 -0.1004 0.5811 0.8094
0.750 0.5521 0.00999 0.00451 -0.0989 0.5746 0.8119
1.000 0.5751 0.01017 0.00466 -0.0978 0.5680 0.8151
1.250 0.6020 0.01031 0.00476 -0.0976 0.5618 0.8189
1.500 0.6343 0.01037 0.00479 -0.0989 0.5546 0.8235
1.750 0.6557 0.01054 0.00491 -0.0975 0.5481 0.8254
2.000 0.6776 0.01065 0.00505 -0.0961 0.5411 0.8277
2.250 0.7011 0.01082 0.00517 -0.0952 0.5348 0.8306
2.500 0.7280 0.01090 0.00527 -0.0951 0.5283 0.8338
2.750 0.7598 0.01101 0.00530 -0.0964 0.5191 0.8377
3.000 0.7826 0.01105 0.00533 -0.0954 0.5058 0.8399
3.250 0.8035 0.01113 0.00539 -0.0940 0.4926 0.8417
3.500 0.8262 0.01123 0.00546 -0.0930 0.4819 0.8438
3.750 0.8508 0.01134 0.00555 -0.0925 0.4734 0.8459
4.000 0.8781 0.01142 0.00566 -0.0927 0.4651 0.8483
4.250 0.9071 0.01157 0.00576 -0.0933 0.4565 0.8514
4.500 0.9359 0.01166 0.00586 -0.0938 0.4455 0.8543
4.750 0.9556 0.01177 0.00596 -0.0922 0.4330 0.8563
5.000 0.9767 0.01192 0.00608 -0.0910 0.4188 0.8583
5.250 0.9989 0.01210 0.00623 -0.0901 0.4031 0.8605
5.500 1.0231 0.01230 0.00639 -0.0897 0.3868 0.8630
5.750 1.0489 0.01255 0.00657 -0.0897 0.3680 0.8655
6.000 1.0779 0.01282 0.00679 -0.0906 0.3523 0.8679
6.250 1.0993 0.01302 0.00697 -0.0896 0.3376 0.8695
6.500 1.1179 0.01326 0.00718 -0.0880 0.3219 0.8714
6.750 1.1365 0.01356 0.00744 -0.0865 0.3036 0.8735
7.000 1.1562 0.01393 0.00775 -0.0854 0.2824 0.8756
7.250 1.1765 0.01443 0.00814 -0.0845 0.2555 0.8780
7.500 1.1967 0.01509 0.00865 -0.0839 0.2240 0.8805
7.750 1.2131 0.01613 0.00942 -0.0828 0.1762 0.8829
8.000 1.2184 0.01717 0.01022 -0.0794 0.1321 0.8851
8.250 1.2249 0.01824 0.01109 -0.0764 0.0941 0.8873
8.750 1.2486 0.02001 0.01270 -0.0724 0.0549 0.8916
9.000 1.2648 0.02076 0.01348 -0.0713 0.0425 0.8937
9.250 1.2786 0.02177 0.01444 -0.0700 0.0326 0.8959
9.500 1.2931 0.02259 0.01530 -0.0688 0.0283 0.8978
9.750 1.3064 0.02324 0.01603 -0.0671 0.0263 0.8995
10.000 1.3183 0.02407 0.01695 -0.0654 0.0236 0.9012
10.250 1.3289 0.02507 0.01801 -0.0638 0.0214 0.9031
10.500 1.3416 0.02605 0.01906 -0.0627 0.0197 0.9050
10.750 1.3531 0.02722 0.02027 -0.0616 0.0179 0.9069
11.000 1.3644 0.02852 0.02162 -0.0608 0.0167 0.9089
11.250 1.3762 0.02993 0.02310 -0.0602 0.0160 0.9107
11.500 1.3836 0.03142 0.02469 -0.0591 0.0153 0.9123
11.750 1.3886 0.03311 0.02645 -0.0579 0.0145 0.9139
12.000 1.3930 0.03501 0.02843 -0.0569 0.0137 0.9156
12.250 1.3965 0.03714 0.03065 -0.0561 0.0130 0.9173
12.500 1.4022 0.03919 0.03281 -0.0556 0.0126 0.9190
12.750 1.4077 0.04138 0.03511 -0.0554 0.0122 0.9209
13.000 1.4118 0.04384 0.03769 -0.0553 0.0116 0.9226
13.250 1.4142 0.04662 0.04059 -0.0555 0.0111 0.9240
13.750 1.4103 0.05304 0.04725 -0.0556 0.0101 0.9263
14.000 1.4020 0.05689 0.05122 -0.0555 0.0097 0.9277
14.250 1.4018 0.05978 0.05423 -0.0554 0.0093 0.9293
14.500 1.4061 0.06220 0.05677 -0.0555 0.0088 0.9310
14.750 1.4076 0.06519 0.05987 -0.0558 0.0081 0.9325
15.000 1.4069 0.06848 0.06327 -0.0563 0.0075 0.9338
15.250 1.4059 0.07191 0.06678 -0.0569 0.0069 0.9350
15.500 1.4049 0.07544 0.07042 -0.0577 0.0065 0.9361
15.750 1.4046 0.07901 0.07411 -0.0586 0.0058 0.9371
16.000 1.4036 0.08270 0.07790 -0.0596 0.0053 0.9381
16.250 1.4042 0.08607 0.08135 -0.0604 0.0049 0.9391
16.500 1.4011 0.08966 0.08502 -0.0611 0.0046 0.9404
16.750 1.3960 0.09358 0.08904 -0.0618 0.0044 0.9419
17.000 1.3905 0.09772 0.09328 -0.0628 0.0043 0.9433
17.250 1.3850 0.10197 0.09763 -0.0640 0.0042 0.9446
17.500 1.3791 0.10637 0.10213 -0.0653 0.0041 0.9458
17.750 1.3732 0.11089 0.10675 -0.0669 0.0040 0.9469
18.000 1.3671 0.11551 0.11147 -0.0686 0.0039 0.9479
18.250 1.3609 0.12028 0.11635 -0.0705 0.0038 0.9489
18.500 1.3542 0.12512 0.12129 -0.0726 0.0037 0.9500
18.750 1.3479 0.13010 0.12637 -0.0749 0.0036 0.9509
19.000 1.3409 0.13507 0.13145 -0.0772 0.0036 0.9518
19.250 1.3335 0.13997 0.13645 -0.0794 0.0035 0.9531
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