FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: FX 63-147 AIRFOIL (fx63147-il) Reynolds number: 500,000 Max Cl/Cd: 84.5 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63147-il-500000-n5.txt Download as CSV file: xf-fx63147-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4131 0.05720 0.05478 -0.0822 0.9883 0.0064
-9.500 -0.4234 0.05211 0.04954 -0.0865 0.9828 0.0063
-9.250 -0.4371 0.04701 0.04425 -0.0883 0.9744 0.0063
-8.750 -0.4622 0.03772 0.03443 -0.0860 0.9483 0.0062
-8.500 -0.4655 0.03323 0.02955 -0.0841 0.9355 0.0063
-8.250 -0.4573 0.02978 0.02574 -0.0832 0.9249 0.0062
-8.000 -0.4380 0.02654 0.02209 -0.0838 0.9174 0.0063
-7.750 -0.4138 0.02402 0.01919 -0.0846 0.9081 0.0063
-7.500 -0.3796 0.02188 0.01665 -0.0870 0.9006 0.0065
-7.250 -0.3424 0.01959 0.01409 -0.0902 0.8907 0.0069
-7.000 -0.2971 0.01802 0.01227 -0.0944 0.8784 0.0070
-6.750 -0.2462 0.01664 0.01059 -0.0996 0.8625 0.0068
-6.500 -0.2076 0.01576 0.00949 -0.1022 0.8398 0.0067
-6.250 -0.1791 0.01513 0.00867 -0.1027 0.8158 0.0066
-6.000 -0.1548 0.01461 0.00798 -0.1023 0.7954 0.0066
-5.750 -0.1321 0.01416 0.00740 -0.1015 0.7760 0.0066
-5.500 -0.1102 0.01371 0.00683 -0.1006 0.7584 0.0066
-5.250 -0.0883 0.01329 0.00631 -0.0998 0.7426 0.0066
-5.000 -0.0659 0.01292 0.00584 -0.0990 0.7279 0.0065
-4.750 -0.0433 0.01256 0.00537 -0.0983 0.7139 0.0066
-4.500 -0.0202 0.01224 0.00496 -0.0976 0.7004 0.0066
-4.250 0.0034 0.01196 0.00458 -0.0971 0.6873 0.0066
-4.000 0.0277 0.01172 0.00425 -0.0966 0.6747 0.0066
-3.750 0.0527 0.01151 0.00395 -0.0963 0.6627 0.0067
-3.500 0.0779 0.01133 0.00368 -0.0959 0.6508 0.0068
-3.250 0.1035 0.01119 0.00344 -0.0957 0.6390 0.0069
-3.000 0.1295 0.01107 0.00324 -0.0955 0.6282 0.0071
-2.750 0.1563 0.01096 0.00306 -0.0955 0.6191 0.0074
-2.500 0.1831 0.01087 0.00291 -0.0954 0.6108 0.0077
-2.250 0.2106 0.01076 0.00278 -0.0956 0.6029 0.0088
-2.000 0.2381 0.01070 0.00267 -0.0957 0.5950 0.0174
-1.750 0.2660 0.01062 0.00258 -0.0959 0.5869 0.0220
-1.500 0.2939 0.01047 0.00249 -0.0963 0.5793 0.0607
-1.250 0.3328 0.00913 0.00222 -0.1006 0.5720 0.3878
-1.000 0.3767 0.00843 0.00212 -0.1052 0.5644 0.5772
-0.750 0.4115 0.00826 0.00223 -0.1070 0.5565 0.6624
-0.500 0.4392 0.00835 0.00246 -0.1069 0.5488 0.7227
-0.250 0.4677 0.00847 0.00258 -0.1071 0.5414 0.7453
0.000 0.4949 0.00864 0.00272 -0.1069 0.5348 0.7599
0.250 0.5215 0.00877 0.00284 -0.1066 0.5291 0.7673
0.500 0.5499 0.00888 0.00291 -0.1068 0.5231 0.7732
0.750 0.5790 0.00899 0.00297 -0.1072 0.5177 0.7782
1.000 0.6051 0.00910 0.00309 -0.1069 0.5122 0.7816
1.250 0.6323 0.00921 0.00318 -0.1068 0.5064 0.7849
1.500 0.6607 0.00933 0.00326 -0.1070 0.5005 0.7890
1.750 0.6906 0.00943 0.00334 -0.1077 0.4933 0.7930
2.000 0.7158 0.00958 0.00346 -0.1072 0.4868 0.7952
2.250 0.7425 0.00968 0.00357 -0.1070 0.4806 0.7974
2.500 0.7687 0.00983 0.00368 -0.1068 0.4726 0.7999
2.750 0.7951 0.00999 0.00379 -0.1067 0.4572 0.8025
3.000 0.8219 0.01018 0.00387 -0.1068 0.4331 0.8050
3.250 0.8495 0.01041 0.00397 -0.1071 0.4123 0.8076
3.500 0.8744 0.01060 0.00412 -0.1067 0.3990 0.8092
3.750 0.8993 0.01078 0.00431 -0.1062 0.3881 0.8111
4.000 0.9240 0.01099 0.00448 -0.1058 0.3761 0.8132
4.250 0.9489 0.01123 0.00467 -0.1054 0.3611 0.8155
4.500 0.9732 0.01155 0.00490 -0.1050 0.3391 0.8177
4.750 0.9970 0.01198 0.00517 -0.1047 0.3074 0.8200
5.000 1.0204 0.01251 0.00550 -0.1044 0.2712 0.8223
5.250 1.0400 0.01317 0.00593 -0.1033 0.2281 0.8239
5.500 1.0533 0.01412 0.00656 -0.1011 0.1686 0.8255
5.750 1.0677 0.01496 0.00717 -0.0991 0.1229 0.8272
6.000 1.0837 0.01562 0.00771 -0.0973 0.0928 0.8290
6.250 1.1024 0.01611 0.00815 -0.0959 0.0769 0.8310
6.500 1.1218 0.01662 0.00861 -0.0948 0.0610 0.8332
6.750 1.1435 0.01706 0.00904 -0.0941 0.0539 0.8355
7.000 1.1640 0.01765 0.00959 -0.0934 0.0359 0.8377
7.250 1.1837 0.01813 0.01007 -0.0924 0.0329 0.8392
7.500 1.2019 0.01860 0.01056 -0.0910 0.0299 0.8405
7.750 1.2206 0.01904 0.01106 -0.0898 0.0268 0.8418
8.000 1.2349 0.01972 0.01175 -0.0879 0.0163 0.8435
8.250 1.2491 0.02044 0.01246 -0.0861 0.0143 0.8454
8.500 1.2657 0.02105 0.01312 -0.0848 0.0130 0.8472
8.750 1.2828 0.02167 0.01380 -0.0836 0.0126 0.8490
9.000 1.2997 0.02233 0.01452 -0.0825 0.0122 0.8508
9.250 1.3161 0.02305 0.01531 -0.0814 0.0119 0.8525
9.500 1.3311 0.02385 0.01618 -0.0802 0.0116 0.8540
9.750 1.3433 0.02469 0.01711 -0.0785 0.0112 0.8552
10.000 1.3546 0.02564 0.01816 -0.0768 0.0109 0.8567
10.250 1.3650 0.02670 0.01931 -0.0752 0.0106 0.8583
10.500 1.3737 0.02798 0.02068 -0.0736 0.0100 0.8599
10.750 1.3818 0.02941 0.02220 -0.0722 0.0095 0.8614
11.000 1.3940 0.03056 0.02342 -0.0713 0.0093 0.8630
11.250 1.4058 0.03181 0.02475 -0.0706 0.0089 0.8645
11.500 1.4165 0.03323 0.02626 -0.0699 0.0083 0.8662
11.750 1.4266 0.03480 0.02791 -0.0693 0.0075 0.8678
12.000 1.4344 0.03648 0.02966 -0.0686 0.0067 0.8691
12.250 1.4433 0.03808 0.03137 -0.0679 0.0059 0.8703
12.500 1.4486 0.04010 0.03345 -0.0673 0.0031 0.8715
12.750 1.4510 0.04249 0.03590 -0.0667 0.0029 0.8727
13.000 1.4521 0.04508 0.03857 -0.0662 0.0027 0.8740
13.250 1.4527 0.04782 0.04142 -0.0659 0.0025 0.8755
13.500 1.4532 0.05067 0.04437 -0.0657 0.0024 0.8769
13.750 1.4533 0.05366 0.04745 -0.0656 0.0023 0.8782
14.000 1.4530 0.05676 0.05066 -0.0657 0.0022 0.8793
14.250 1.4519 0.06002 0.05402 -0.0659 0.0021 0.8804
14.500 1.4504 0.06338 0.05749 -0.0662 0.0021 0.8815
14.750 1.4486 0.06692 0.06114 -0.0667 0.0020 0.8824
15.000 1.4455 0.07048 0.06482 -0.0671 0.0020 0.8832
15.250 1.4414 0.07423 0.06869 -0.0675 0.0020 0.8841
15.500 1.4371 0.07804 0.07262 -0.0680 0.0019 0.8851
15.750 1.4325 0.08198 0.07669 -0.0687 0.0019 0.8860
16.000 1.4274 0.08603 0.08085 -0.0694 0.0019 0.8870
16.250 1.4216 0.09025 0.08520 -0.0703 0.0018 0.8880
16.500 1.4161 0.09450 0.08958 -0.0713 0.0018 0.8888
16.750 1.4100 0.09891 0.09410 -0.0724 0.0018 0.8897
17.000 1.4041 0.10338 0.09869 -0.0737 0.0017 0.8905
17.250 1.3978 0.10790 0.10333 -0.0751 0.0017 0.8913
17.500 1.3915 0.11251 0.10805 -0.0766 0.0017 0.8922
17.750 1.3852 0.11723 0.11289 -0.0784 0.0017 0.8930
18.000 1.3786 0.12204 0.11782 -0.0802 0.0017 0.8938
18.250 1.3719 0.12698 0.12288 -0.0823 0.0016 0.8945
18.500 1.3658 0.13173 0.12774 -0.0844 0.0016 0.8953
18.750 1.3589 0.13686 0.13298 -0.0868 0.0016 0.8961
19.000 1.3523 0.14190 0.13813 -0.0893 0.0016 0.8970
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