FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 200,000 Max Cl/Cd: 70.81 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61147-il-200000.txt Download as CSV file: xf-fx61147-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-147 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3865 0.08999 0.08681 -0.0519 1.0000 0.0495
-9.250 -0.4112 0.08424 0.08110 -0.0552 1.0000 0.0497
-9.000 -0.4309 0.08055 0.07744 -0.0551 1.0000 0.0496
-8.750 -0.4562 0.07786 0.07478 -0.0536 1.0000 0.0495
-8.500 -0.4739 0.07547 0.07245 -0.0511 1.0000 0.0492
-8.250 -0.5085 0.07382 0.07081 -0.0486 0.9994 0.0493
-8.000 -0.5006 0.06800 0.06434 -0.0632 0.9867 0.0503
-7.750 -0.4924 0.05870 0.05513 -0.0668 0.9812 0.0522
-7.500 -0.4628 0.05593 0.05247 -0.0694 0.9771 0.0559
-7.250 -0.3783 0.03425 0.03055 -0.0810 0.9526 0.0669
-7.000 -0.3543 0.03047 0.02663 -0.0838 0.9466 0.0709
-6.750 -0.3349 0.02603 0.02174 -0.0872 0.9384 0.0801
-6.500 -0.3525 0.03281 0.02707 -0.0846 0.9499 0.0369
-6.250 -0.3245 0.02798 0.02166 -0.0853 0.9418 0.0326
-6.000 -0.2851 0.02494 0.01816 -0.0873 0.9379 0.0319
-5.750 -0.2479 0.02353 0.01666 -0.0893 0.9324 0.0349
-5.500 -0.2119 0.02196 0.01486 -0.0906 0.9258 0.0372
-5.250 -0.1700 0.02051 0.01322 -0.0927 0.9226 0.0389
-5.000 -0.1399 0.01859 0.01141 -0.0932 0.9149 0.0436
-4.750 -0.0990 0.01745 0.01023 -0.0956 0.9097 0.0490
-4.500 -0.0588 0.01601 0.00883 -0.0985 0.9030 0.0576
-4.250 -0.0145 0.01471 0.00752 -0.1024 0.8952 0.0736
-4.000 0.0364 0.01133 0.00632 -0.1104 0.8877 0.5385
-3.750 0.0773 0.01165 0.00667 -0.1118 0.8772 0.6130
-3.500 0.1123 0.01222 0.00713 -0.1119 0.8626 0.6427
-3.250 0.1422 0.01297 0.00780 -0.1107 0.8464 0.6608
-3.000 0.1661 0.01390 0.00866 -0.1079 0.8283 0.6775
-2.750 0.1905 0.01462 0.00928 -0.1055 0.8105 0.6907
-2.500 0.2210 0.01480 0.00927 -0.1057 0.7931 0.7015
-2.250 0.2465 0.01501 0.00933 -0.1044 0.7764 0.7056
-2.000 0.2766 0.01504 0.00916 -0.1049 0.7602 0.7137
-1.750 0.3023 0.01511 0.00908 -0.1042 0.7447 0.7183
-1.500 0.3271 0.01521 0.00905 -0.1033 0.7298 0.7230
-1.250 0.3575 0.01517 0.00883 -0.1043 0.7156 0.7308
-1.000 0.3801 0.01526 0.00883 -0.1028 0.7024 0.7341
-0.750 0.4057 0.01532 0.00878 -0.1023 0.6899 0.7391
-0.500 0.4360 0.01530 0.00861 -0.1033 0.6780 0.7457
-0.250 0.4599 0.01539 0.00860 -0.1022 0.6675 0.7490
0.000 0.4851 0.01543 0.00857 -0.1018 0.6564 0.7538
0.250 0.5157 0.01544 0.00847 -0.1029 0.6456 0.7601
0.500 0.5396 0.01550 0.00845 -0.1019 0.6366 0.7631
0.750 0.5647 0.01554 0.00846 -0.1014 0.6269 0.7672
1.000 0.5950 0.01560 0.00843 -0.1024 0.6178 0.7727
1.250 0.6216 0.01564 0.00840 -0.1023 0.6097 0.7763
1.500 0.6454 0.01569 0.00845 -0.1015 0.6009 0.7799
1.750 0.6745 0.01580 0.00847 -0.1020 0.5936 0.7842
2.000 0.7041 0.01585 0.00852 -0.1029 0.5849 0.7891
2.250 0.7292 0.01593 0.00854 -0.1023 0.5781 0.7921
2.500 0.7535 0.01598 0.00864 -0.1017 0.5698 0.7958
2.750 0.7837 0.01612 0.00870 -0.1025 0.5632 0.8001
3.000 0.8114 0.01618 0.00880 -0.1029 0.5548 0.8041
3.500 0.8617 0.01636 0.00901 -0.1021 0.5406 0.8107
3.750 0.8917 0.01651 0.00910 -0.1029 0.5341 0.8146
4.000 0.9197 0.01663 0.00929 -0.1034 0.5264 0.8182
4.250 0.9453 0.01673 0.00939 -0.1030 0.5201 0.8212
4.500 0.9700 0.01687 0.00961 -0.1026 0.5132 0.8247
4.750 0.9982 0.01702 0.00977 -0.1030 0.5064 0.8283
5.000 1.0277 0.01724 0.01004 -0.1038 0.4996 0.8318
5.250 1.0521 0.01735 0.01021 -0.1033 0.4929 0.8348
5.500 1.0786 0.01755 0.01043 -0.1033 0.4870 0.8381
5.750 1.1037 0.01771 0.01070 -0.1031 0.4795 0.8415
6.000 1.1344 0.01797 0.01093 -0.1040 0.4734 0.8450
6.250 1.1576 0.01813 0.01126 -0.1034 0.4659 0.8482
6.500 1.1841 0.01830 0.01143 -0.1033 0.4595 0.8514
6.750 1.2064 0.01845 0.01173 -0.1025 0.4508 0.8549
7.000 1.2340 0.01864 0.01193 -0.1028 0.4430 0.8585
7.250 1.2565 0.01876 0.01220 -0.1021 0.4337 0.8620
7.500 1.2779 0.01887 0.01238 -0.1010 0.4247 0.8653
7.750 1.3009 0.01898 0.01252 -0.1003 0.4154 0.8688
8.000 1.3217 0.01913 0.01284 -0.0993 0.4050 0.8729
8.250 1.3416 0.01923 0.01303 -0.0981 0.3934 0.8766
8.500 1.3583 0.01930 0.01317 -0.0962 0.3811 0.8804
8.750 1.3757 0.01944 0.01337 -0.0946 0.3683 0.8845
9.000 1.3942 0.01969 0.01369 -0.0933 0.3559 0.8890
9.250 1.4084 0.01990 0.01405 -0.0911 0.3434 0.8936
9.500 1.4217 0.02017 0.01446 -0.0888 0.3299 0.8986
9.750 1.4332 0.02055 0.01489 -0.0863 0.3140 0.9038
10.000 1.4388 0.02098 0.01537 -0.0828 0.2963 0.9103
10.250 1.4445 0.02161 0.01603 -0.0796 0.2736 0.9181
10.500 1.4443 0.02237 0.01678 -0.0755 0.2501 0.9281
10.750 1.4399 0.02338 0.01776 -0.0711 0.2240 0.9447
11.000 1.4362 0.02485 0.01914 -0.0678 0.1920 1.0000
11.250 1.4297 0.02723 0.02132 -0.0653 0.1558 1.0000
11.500 1.4208 0.03004 0.02396 -0.0630 0.1257 1.0000
11.750 1.4109 0.03319 0.02698 -0.0613 0.1015 1.0000
12.000 1.4021 0.03651 0.03023 -0.0601 0.0830 1.0000
12.250 1.3938 0.04003 0.03374 -0.0595 0.0697 1.0000
12.500 1.3865 0.04366 0.03739 -0.0592 0.0603 1.0000
12.750 1.3765 0.04778 0.04150 -0.0592 0.0537 1.0000
13.000 1.3730 0.05138 0.04521 -0.0596 0.0472 1.0000
13.250 1.3629 0.05586 0.04972 -0.0601 0.0424 1.0000
13.500 1.3584 0.05982 0.05378 -0.0608 0.0369 1.0000
13.750 1.3455 0.06499 0.05900 -0.0619 0.0329 1.0000
14.000 1.3373 0.06972 0.06384 -0.0630 0.0281 1.0000
14.250 1.3191 0.07590 0.07006 -0.0645 0.0255 1.0000
14.500 1.3138 0.08052 0.07481 -0.0657 0.0224 1.0000
14.750 1.3066 0.08544 0.07980 -0.0672 0.0205 1.0000
15.000 1.2965 0.09071 0.08510 -0.0686 0.0192 1.0000
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