FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-147 AIRFOIL (fx63147-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.27 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63147-il-1000000-n5.txt Download as CSV file: xf-fx63147-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3892 0.05499 0.05317 -0.0950 0.9835 0.0037
-9.750 -0.4177 0.04833 0.04634 -0.0969 0.9758 0.0037
-9.500 -0.4453 0.04308 0.04089 -0.0951 0.9642 0.0037
-9.250 -0.4851 0.03387 0.03122 -0.0918 0.9462 0.0040
-9.000 -0.4862 0.02846 0.02533 -0.0911 0.9339 0.0042
-8.750 -0.4630 0.02562 0.02214 -0.0928 0.9238 0.0043
-8.500 -0.4249 0.02297 0.01900 -0.0973 0.9133 0.0046
-8.250 -0.3764 0.02025 0.01589 -0.1038 0.9003 0.0046
-8.000 -0.3338 0.01814 0.01341 -0.1084 0.8722 0.0047
-7.750 -0.3098 0.01710 0.01207 -0.1084 0.8357 0.0048
-7.500 -0.2899 0.01640 0.01112 -0.1073 0.8053 0.0048
-7.250 -0.2705 0.01559 0.01014 -0.1061 0.7826 0.0049
-7.000 -0.2499 0.01496 0.00936 -0.1051 0.7634 0.0050
-6.750 -0.2287 0.01443 0.00872 -0.1042 0.7454 0.0052
-6.500 -0.2072 0.01392 0.00809 -0.1033 0.7294 0.0054
-6.250 -0.1855 0.01340 0.00745 -0.1023 0.7146 0.0054
-6.000 -0.1636 0.01291 0.00684 -0.1014 0.7008 0.0053
-5.750 -0.1412 0.01249 0.00630 -0.1006 0.6877 0.0052
-5.500 -0.1184 0.01209 0.00581 -0.0999 0.6749 0.0051
-5.250 -0.0950 0.01173 0.00536 -0.0992 0.6625 0.0051
-5.000 -0.0712 0.01141 0.00496 -0.0987 0.6503 0.0050
-4.750 -0.0471 0.01111 0.00458 -0.0983 0.6388 0.0050
-4.250 0.0031 0.01060 0.00393 -0.0977 0.6156 0.0049
-4.000 0.0289 0.01037 0.00364 -0.0975 0.6057 0.0049
-3.750 0.0554 0.01017 0.00338 -0.0975 0.5970 0.0049
-3.500 0.0825 0.00996 0.00313 -0.0976 0.5898 0.0049
-3.250 0.1098 0.00979 0.00291 -0.0977 0.5820 0.0050
-3.000 0.1375 0.00964 0.00272 -0.0979 0.5747 0.0050
-2.750 0.1653 0.00952 0.00255 -0.0980 0.5667 0.0050
-2.500 0.1936 0.00942 0.00240 -0.0983 0.5596 0.0051
-2.250 0.2218 0.00933 0.00227 -0.0986 0.5527 0.0053
-2.000 0.2502 0.00926 0.00216 -0.0989 0.5465 0.0054
-1.750 0.2787 0.00920 0.00207 -0.0992 0.5388 0.0058
-1.500 0.3071 0.00917 0.00199 -0.0995 0.5318 0.0063
-1.250 0.3361 0.00911 0.00193 -0.0999 0.5248 0.0132
-0.750 0.3943 0.00900 0.00186 -0.1009 0.5130 0.0422
-0.500 0.4238 0.00893 0.00183 -0.1014 0.5074 0.0672
-0.250 0.4542 0.00879 0.00181 -0.1024 0.5021 0.1236
0.000 0.5235 0.00713 0.00166 -0.1139 0.4959 0.6256
0.250 0.5588 0.00707 0.00174 -0.1158 0.4898 0.6827
0.500 0.5902 0.00710 0.00183 -0.1167 0.4838 0.7138
0.750 0.6197 0.00717 0.00190 -0.1172 0.4768 0.7252
1.000 0.6488 0.00727 0.00198 -0.1176 0.4700 0.7350
1.250 0.6783 0.00735 0.00205 -0.1180 0.4633 0.7460
1.500 0.7062 0.00749 0.00216 -0.1182 0.4501 0.7549
1.750 0.7335 0.00774 0.00226 -0.1183 0.4220 0.7623
2.000 0.7594 0.00799 0.00240 -0.1181 0.3967 0.7673
2.250 0.7869 0.00819 0.00253 -0.1182 0.3807 0.7728
2.500 0.8146 0.00841 0.00265 -0.1184 0.3617 0.7774
2.750 0.8404 0.00864 0.00281 -0.1182 0.3431 0.7805
3.000 0.8655 0.00898 0.00302 -0.1179 0.3150 0.7833
3.250 0.8883 0.00953 0.00331 -0.1172 0.2675 0.7861
3.500 0.9062 0.01051 0.00385 -0.1158 0.1845 0.7887
3.750 0.9239 0.01149 0.00444 -0.1144 0.1052 0.7911
4.000 0.9473 0.01196 0.00477 -0.1139 0.0784 0.7931
4.250 0.9711 0.01231 0.00506 -0.1133 0.0611 0.7949
4.500 0.9959 0.01257 0.00530 -0.1130 0.0536 0.7970
4.750 1.0186 0.01301 0.00566 -0.1123 0.0338 0.7994
5.000 1.0434 0.01329 0.00593 -0.1119 0.0292 0.8018
5.250 1.0689 0.01352 0.00617 -0.1117 0.0270 0.8039
5.500 1.0927 0.01387 0.00649 -0.1113 0.0165 0.8057
5.750 1.1167 0.01420 0.00680 -0.1109 0.0143 0.8074
6.000 1.1405 0.01448 0.00708 -0.1104 0.0130 0.8089
6.250 1.1637 0.01476 0.00739 -0.1097 0.0126 0.8105
6.500 1.1861 0.01507 0.00774 -0.1090 0.0120 0.8121
6.750 1.2066 0.01543 0.00813 -0.1079 0.0111 0.8139
7.000 1.2268 0.01580 0.00853 -0.1067 0.0103 0.8159
7.250 1.2476 0.01618 0.00894 -0.1058 0.0099 0.8180
7.500 1.2682 0.01658 0.00938 -0.1048 0.0095 0.8198
7.750 1.2893 0.01695 0.00976 -0.1039 0.0094 0.8214
8.000 1.3100 0.01734 0.01017 -0.1030 0.0092 0.8229
8.250 1.3290 0.01774 0.01061 -0.1018 0.0089 0.8243
8.500 1.3471 0.01816 0.01108 -0.1005 0.0085 0.8258
8.750 1.3649 0.01862 0.01157 -0.0991 0.0080 0.8273
9.000 1.3819 0.01911 0.01209 -0.0976 0.0075 0.8288
9.250 1.3975 0.01967 0.01268 -0.0960 0.0067 0.8303
9.500 1.4158 0.02014 0.01318 -0.0949 0.0059 0.8318
9.750 1.4288 0.02088 0.01391 -0.0931 0.0025 0.8334
10.000 1.4418 0.02167 0.01474 -0.0913 0.0020 0.8350
10.250 1.4547 0.02248 0.01561 -0.0896 0.0019 0.8365
10.500 1.4667 0.02339 0.01658 -0.0879 0.0017 0.8380
10.750 1.4776 0.02437 0.01763 -0.0861 0.0016 0.8394
11.000 1.4872 0.02545 0.01879 -0.0843 0.0016 0.8408
11.250 1.4964 0.02664 0.02005 -0.0826 0.0015 0.8421
11.500 1.5049 0.02793 0.02142 -0.0811 0.0014 0.8433
11.750 1.5124 0.02937 0.02294 -0.0796 0.0014 0.8447
12.000 1.5192 0.03097 0.02462 -0.0782 0.0013 0.8460
12.250 1.5253 0.03271 0.02645 -0.0771 0.0013 0.8475
12.500 1.5315 0.03454 0.02836 -0.0761 0.0013 0.8490
12.750 1.5367 0.03652 0.03043 -0.0753 0.0012 0.8504
13.000 1.5412 0.03867 0.03266 -0.0745 0.0012 0.8516
13.250 1.5449 0.04098 0.03506 -0.0740 0.0012 0.8527
13.500 1.5474 0.04345 0.03762 -0.0735 0.0012 0.8537
13.750 1.5487 0.04609 0.04035 -0.0730 0.0011 0.8549
14.000 1.5491 0.04890 0.04326 -0.0727 0.0011 0.8560
14.250 1.5487 0.05185 0.04632 -0.0725 0.0011 0.8570
14.500 1.5470 0.05499 0.04956 -0.0723 0.0011 0.8579
14.750 1.5449 0.05829 0.05296 -0.0723 0.0010 0.8588
15.000 1.5420 0.06170 0.05647 -0.0724 0.0010 0.8597
15.250 1.5382 0.06534 0.06022 -0.0726 0.0010 0.8606
15.500 1.5336 0.06907 0.06405 -0.0729 0.0010 0.8615
15.750 1.5288 0.07294 0.06803 -0.0734 0.0010 0.8624
16.000 1.5233 0.07696 0.07214 -0.0739 0.0010 0.8633
16.250 1.5169 0.08118 0.07647 -0.0746 0.0009 0.8642
16.500 1.5105 0.08541 0.08080 -0.0754 0.0009 0.8651
16.750 1.5034 0.08980 0.08529 -0.0763 0.0009 0.8659
17.000 1.4962 0.09431 0.08990 -0.0773 0.0009 0.8666
17.250 1.4888 0.09890 0.09459 -0.0785 0.0009 0.8672
17.500 1.4811 0.10356 0.09935 -0.0797 0.0009 0.8678
17.750 1.4732 0.10832 0.10421 -0.0812 0.0009 0.8683
18.000 1.4648 0.11318 0.10918 -0.0827 0.0008 0.8689
18.250 1.4560 0.11822 0.11432 -0.0845 0.0008 0.8696
18.500 1.4478 0.12310 0.11930 -0.0862 0.0008 0.8703
18.750 1.4389 0.12831 0.12462 -0.0883 0.0008 0.8709
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