FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=0
| Details | Polar file |
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Airfoil: FX 63-147 AIRFOIL (fx63147-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.63 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63147-il-1000000.txt Download as CSV file: xf-fx63147-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3848 0.13860 0.13691 -0.0309 1.0001 0.0068
-12.750 -0.3817 0.13546 0.13378 -0.0316 1.0001 0.0068
-12.500 -0.3795 0.13202 0.13035 -0.0324 1.0001 0.0069
-12.250 -0.3773 0.12869 0.12703 -0.0331 1.0001 0.0070
-12.000 -0.3761 0.12512 0.12348 -0.0339 1.0001 0.0071
-11.750 -0.3754 0.12153 0.11990 -0.0347 1.0001 0.0072
-11.500 -0.3756 0.11779 0.11617 -0.0355 1.0001 0.0073
-11.250 -0.3765 0.11397 0.11238 -0.0363 1.0001 0.0074
-11.000 -0.3784 0.11005 0.10847 -0.0372 1.0001 0.0075
-10.750 -0.3813 0.10599 0.10443 -0.0380 1.0001 0.0076
-9.500 -0.3809 0.06605 0.06448 -0.0755 0.9931 0.0079
-9.250 -0.3951 0.05776 0.05605 -0.0841 0.9882 0.0078
-9.000 -0.4030 0.05081 0.04890 -0.0905 0.9846 0.0080
-7.000 -0.2425 0.00948 0.00578 -0.1030 0.9005 0.0160
-6.750 -0.2075 0.00736 0.00308 -0.1060 0.8822 0.0187
-6.500 -0.1762 0.00630 0.00190 -0.1077 0.8594 0.0194
-6.250 -0.1524 0.00557 0.00096 -0.1075 0.8349 0.0200
-6.000 -0.1302 0.00494 0.00008 -0.1066 0.8130 0.0206
-5.750 -0.1080 0.00448 -0.00059 -0.1057 0.7938 0.0215
-5.500 -0.0884 0.01264 0.00702 -0.1068 0.8086 0.0111
-5.250 -0.0694 0.01167 0.00598 -0.1052 0.7878 0.0106
-5.000 -0.0495 0.01105 0.00524 -0.1038 0.7680 0.0101
-4.750 -0.0289 0.01048 0.00454 -0.1026 0.7497 0.0096
-4.500 -0.0062 0.01011 0.00405 -0.1018 0.7320 0.0092
-4.250 0.0176 0.00987 0.00370 -0.1012 0.7147 0.0090
-4.000 0.0423 0.00967 0.00341 -0.1007 0.6994 0.0088
-3.750 0.0677 0.00950 0.00315 -0.1004 0.6859 0.0087
-3.250 0.1206 0.00919 0.00269 -0.1002 0.6614 0.0086
-3.000 0.1478 0.00909 0.00252 -0.1002 0.6501 0.0086
-2.750 0.1749 0.00902 0.00238 -0.1002 0.6395 0.0087
-2.500 0.2028 0.00896 0.00226 -0.1003 0.6291 0.0089
-2.250 0.2308 0.00890 0.00217 -0.1005 0.6200 0.0097
-2.000 0.2587 0.00887 0.00210 -0.1007 0.6107 0.0139
-1.750 0.2876 0.00882 0.00203 -0.1011 0.6013 0.0198
-1.500 0.3159 0.00876 0.00197 -0.1014 0.5926 0.0343
-1.250 0.3451 0.00865 0.00191 -0.1019 0.5839 0.0646
-1.000 0.3841 0.00774 0.00174 -0.1057 0.5760 0.3189
-0.750 0.4404 0.00669 0.00162 -0.1135 0.5676 0.6162
-0.500 0.4769 0.00659 0.00170 -0.1157 0.5608 0.6871
-0.250 0.5086 0.00663 0.00182 -0.1166 0.5539 0.7273
0.000 0.5379 0.00675 0.00195 -0.1169 0.5475 0.7519
0.250 0.5680 0.00684 0.00202 -0.1175 0.5411 0.7625
0.500 0.5948 0.00699 0.00215 -0.1173 0.5341 0.7712
0.750 0.6248 0.00707 0.00220 -0.1179 0.5276 0.7766
1.000 0.6516 0.00718 0.00230 -0.1177 0.5205 0.7812
1.250 0.6790 0.00730 0.00242 -0.1176 0.5144 0.7866
1.500 0.7079 0.00746 0.00251 -0.1179 0.5038 0.7925
1.750 0.7327 0.00762 0.00263 -0.1173 0.4885 0.7963
2.000 0.7583 0.00777 0.00275 -0.1169 0.4749 0.7998
2.250 0.7854 0.00792 0.00286 -0.1168 0.4657 0.8037
2.500 0.8140 0.00809 0.00298 -0.1172 0.4552 0.8074
2.750 0.8403 0.00821 0.00308 -0.1169 0.4440 0.8099
3.000 0.8656 0.00837 0.00320 -0.1165 0.4297 0.8118
3.250 0.8904 0.00861 0.00334 -0.1160 0.4109 0.8139
3.500 0.9161 0.00884 0.00350 -0.1158 0.3897 0.8160
3.750 0.9420 0.00910 0.00366 -0.1157 0.3677 0.8181
4.000 0.9685 0.00937 0.00382 -0.1157 0.3484 0.8202
4.250 0.9955 0.00964 0.00400 -0.1158 0.3281 0.8223
4.500 1.0203 0.00998 0.00422 -0.1156 0.3025 0.8240
4.750 1.0407 0.01049 0.00454 -0.1144 0.2631 0.8257
5.000 1.0597 0.01110 0.00493 -0.1130 0.2224 0.8275
5.250 1.0759 0.01193 0.00548 -0.1112 0.1678 0.8296
5.500 1.0920 0.01279 0.00607 -0.1094 0.1164 0.8317
5.750 1.1109 0.01348 0.00658 -0.1081 0.0801 0.8337
6.000 1.1320 0.01401 0.00699 -0.1072 0.0588 0.8356
6.250 1.1563 0.01435 0.00731 -0.1069 0.0495 0.8373
6.500 1.1761 0.01490 0.00777 -0.1058 0.0328 0.8390
6.750 1.1954 0.01521 0.00809 -0.1044 0.0274 0.8405
7.000 1.2118 0.01568 0.00854 -0.1026 0.0166 0.8421
7.250 1.2310 0.01608 0.00894 -0.1013 0.0155 0.8436
7.500 1.2510 0.01648 0.00936 -0.1001 0.0144 0.8454
7.750 1.2712 0.01688 0.00978 -0.0991 0.0137 0.8473
8.000 1.2913 0.01729 0.01023 -0.0980 0.0131 0.8493
8.250 1.3112 0.01774 0.01071 -0.0970 0.0127 0.8510
8.500 1.3310 0.01821 0.01123 -0.0961 0.0125 0.8526
8.750 1.3499 0.01871 0.01177 -0.0950 0.0121 0.8540
9.000 1.3658 0.01924 0.01237 -0.0934 0.0117 0.8555
9.250 1.3801 0.01986 0.01306 -0.0915 0.0110 0.8570
9.500 1.3924 0.02062 0.01389 -0.0895 0.0102 0.8586
9.750 1.4033 0.02149 0.01483 -0.0873 0.0095 0.8602
10.000 1.4222 0.02190 0.01527 -0.0864 0.0092 0.8617
10.250 1.4391 0.02246 0.01586 -0.0853 0.0087 0.8633
10.500 1.4553 0.02310 0.01653 -0.0842 0.0080 0.8649
10.750 1.4703 0.02386 0.01733 -0.0831 0.0074 0.8664
11.000 1.4833 0.02477 0.01827 -0.0818 0.0069 0.8678
11.250 1.4974 0.02562 0.01917 -0.0806 0.0065 0.8693
11.500 1.5102 0.02650 0.02012 -0.0794 0.0054 0.8707
11.750 1.5177 0.02781 0.02142 -0.0777 0.0032 0.8722
12.000 1.5240 0.02932 0.02300 -0.0761 0.0029 0.8736
12.250 1.5297 0.03100 0.02475 -0.0747 0.0027 0.8750
12.500 1.5353 0.03280 0.02664 -0.0736 0.0025 0.8765
12.750 1.5405 0.03474 0.02866 -0.0726 0.0024 0.8779
13.000 1.5449 0.03683 0.03084 -0.0718 0.0023 0.8794
13.250 1.5479 0.03917 0.03328 -0.0711 0.0022 0.8809
13.500 1.5500 0.04171 0.03591 -0.0706 0.0021 0.8821
13.750 1.5512 0.04437 0.03868 -0.0702 0.0021 0.8832
14.000 1.5515 0.04717 0.04158 -0.0698 0.0021 0.8844
14.250 1.5499 0.05019 0.04471 -0.0695 0.0020 0.8855
14.500 1.5474 0.05336 0.04800 -0.0693 0.0020 0.8867
14.750 1.5438 0.05676 0.05151 -0.0692 0.0020 0.8879
15.000 1.5399 0.06024 0.05510 -0.0692 0.0020 0.8891
15.250 1.5348 0.06401 0.05899 -0.0694 0.0019 0.8901
15.500 1.5295 0.06784 0.06293 -0.0697 0.0019 0.8911
15.750 1.5233 0.07189 0.06708 -0.0702 0.0019 0.8921
16.000 1.5166 0.07607 0.07137 -0.0708 0.0019 0.8930
16.250 1.5089 0.08051 0.07593 -0.0716 0.0019 0.8938
16.500 1.5013 0.08496 0.08048 -0.0724 0.0019 0.8946
16.750 1.4926 0.08961 0.08524 -0.0734 0.0018 0.8954
17.000 1.4842 0.09433 0.09007 -0.0746 0.0018 0.8961
17.250 1.4755 0.09917 0.09502 -0.0759 0.0018 0.8967
17.500 1.4666 0.10406 0.10001 -0.0773 0.0018 0.8975
17.750 1.4578 0.10896 0.10503 -0.0788 0.0018 0.8985
18.000 1.4482 0.11403 0.11021 -0.0804 0.0018 0.8993
18.250 1.4385 0.11922 0.11550 -0.0822 0.0018 0.9000
18.500 1.4300 0.12416 0.12055 -0.0841 0.0018 0.9008
18.750 1.4204 0.12951 0.12601 -0.0863 0.0018 0.9015
19.000 1.4109 0.13474 0.13135 -0.0885 0.0018 0.9022
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