FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-163 AIRFOIL (fx61163-il) Reynolds number: 100,000 Max Cl/Cd: 50.02 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61163-il-100000-n5.txt Download as CSV file: xf-fx61163-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-163 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4180 0.09408 0.08919 -0.0530 1.0001 0.0230
-11.000 -0.4330 0.08602 0.08113 -0.0579 1.0001 0.0224
-10.750 -0.4541 0.07865 0.07373 -0.0624 1.0001 0.0220
-10.500 -0.4770 0.07257 0.06757 -0.0655 1.0001 0.0216
-10.250 -0.5000 0.06762 0.06254 -0.0670 1.0001 0.0213
-10.000 -0.5219 0.06365 0.05849 -0.0671 1.0001 0.0211
-9.750 -0.5438 0.06046 0.05522 -0.0658 1.0001 0.0209
-9.500 -0.5673 0.05808 0.05279 -0.0630 1.0001 0.0208
-9.250 -0.5777 0.05449 0.04902 -0.0634 0.9914 0.0206
-9.000 -0.5702 0.04954 0.04364 -0.0668 0.9639 0.0203
-8.750 -0.5548 0.04505 0.03865 -0.0696 0.9411 0.0201
-8.500 -0.5302 0.04105 0.03413 -0.0725 0.9225 0.0201
-8.250 -0.5000 0.03763 0.03024 -0.0754 0.9060 0.0202
-8.000 -0.4666 0.03475 0.02691 -0.0779 0.8900 0.0205
-7.750 -0.4323 0.03232 0.02413 -0.0799 0.8738 0.0209
-7.500 -0.3982 0.03030 0.02180 -0.0813 0.8578 0.0215
-7.250 -0.3664 0.02865 0.01990 -0.0820 0.8422 0.0222
-6.750 -0.3108 0.02629 0.01716 -0.0820 0.8137 0.0255
-6.500 -0.2872 0.02529 0.01612 -0.0817 0.8014 0.0273
-6.250 -0.2639 0.02439 0.01513 -0.0813 0.7906 0.0290
-6.000 -0.2404 0.02353 0.01411 -0.0810 0.7811 0.0310
-5.750 -0.2182 0.02270 0.01314 -0.0808 0.7712 0.0334
-5.500 -0.1950 0.02186 0.01221 -0.0809 0.7630 0.0387
-5.250 -0.1715 0.02104 0.01132 -0.0810 0.7552 0.0497
-5.000 -0.1491 0.01988 0.01040 -0.0813 0.7484 0.0924
-4.750 -0.1349 0.01716 0.00966 -0.0827 0.7412 0.4395
-4.500 -0.1122 0.01835 0.01123 -0.0795 0.7354 0.5700
-4.250 -0.0876 0.02002 0.01281 -0.0766 0.7287 0.6146
-4.000 -0.0633 0.02123 0.01385 -0.0738 0.7235 0.6319
-3.750 -0.0352 0.02131 0.01370 -0.0741 0.7180 0.6430
-3.500 -0.0095 0.02147 0.01370 -0.0733 0.7123 0.6469
-3.250 0.0193 0.02139 0.01338 -0.0739 0.7076 0.6538
-3.000 0.0464 0.02137 0.01321 -0.0740 0.7024 0.6596
-2.750 0.0724 0.02145 0.01316 -0.0735 0.6972 0.6642
-2.250 0.1285 0.02132 0.01272 -0.0744 0.6879 0.6752
-2.000 0.1546 0.02134 0.01265 -0.0742 0.6829 0.6795
-1.750 0.1860 0.02116 0.01228 -0.0759 0.6785 0.6868
-1.500 0.2116 0.02123 0.01227 -0.0753 0.6744 0.6896
-1.250 0.2371 0.02127 0.01227 -0.0750 0.6693 0.6933
-1.000 0.2662 0.02121 0.01210 -0.0758 0.6649 0.6984
-0.750 0.2964 0.02114 0.01189 -0.0768 0.6613 0.7028
-0.500 0.3210 0.02121 0.01197 -0.0763 0.6563 0.7057
-0.250 0.3476 0.02123 0.01195 -0.0763 0.6515 0.7093
0.000 0.3783 0.02118 0.01179 -0.0775 0.6475 0.7140
0.250 0.4062 0.02119 0.01177 -0.0779 0.6428 0.7178
0.500 0.4312 0.02127 0.01186 -0.0776 0.6377 0.7206
0.750 0.4588 0.02129 0.01184 -0.0778 0.6334 0.7239
1.000 0.4885 0.02132 0.01181 -0.0786 0.6292 0.7281
1.250 0.5165 0.02138 0.01191 -0.0793 0.6239 0.7320
1.500 0.5424 0.02145 0.01198 -0.0791 0.6194 0.7345
1.750 0.5708 0.02150 0.01199 -0.0793 0.6159 0.7375
2.000 0.5966 0.02164 0.01220 -0.0795 0.6102 0.7412
2.250 0.6272 0.02170 0.01227 -0.0807 0.6052 0.7452
2.500 0.6552 0.02173 0.01229 -0.0809 0.6013 0.7477
2.750 0.6788 0.02190 0.01256 -0.0804 0.5953 0.7504
3.000 0.7055 0.02199 0.01271 -0.0805 0.5899 0.7536
3.250 0.7361 0.02202 0.01271 -0.0813 0.5858 0.7569
3.500 0.7637 0.02223 0.01303 -0.0821 0.5792 0.7606
3.750 0.7888 0.02232 0.01321 -0.0817 0.5741 0.7629
4.000 0.8165 0.02238 0.01329 -0.0818 0.5700 0.7656
4.250 0.8399 0.02263 0.01370 -0.0815 0.5630 0.7687
4.500 0.8689 0.02270 0.01382 -0.0821 0.5579 0.7720
4.750 0.8971 0.02288 0.01410 -0.0827 0.5518 0.7755
5.000 0.9206 0.02300 0.01435 -0.0821 0.5451 0.7779
5.250 0.9478 0.02301 0.01441 -0.0821 0.5398 0.7806
5.500 0.9706 0.02327 0.01486 -0.0817 0.5318 0.7837
5.750 1.0004 0.02328 0.01491 -0.0823 0.5264 0.7870
6.000 1.0247 0.02357 0.01539 -0.0823 0.5177 0.7903
6.250 1.0514 0.02347 0.01537 -0.0820 0.5112 0.7927
6.500 1.0718 0.02372 0.01582 -0.0811 0.5012 0.7955
6.750 1.0967 0.02380 0.01602 -0.0809 0.4928 0.7987
7.000 1.1226 0.02387 0.01620 -0.0808 0.4835 0.8020
7.250 1.1463 0.02409 0.01660 -0.0806 0.4725 0.8051
7.500 1.1680 0.02421 0.01685 -0.0797 0.4624 0.8077
7.750 1.1914 0.02427 0.01700 -0.0791 0.4525 0.8108
8.000 1.2121 0.02452 0.01740 -0.0783 0.4398 0.8142
8.250 1.2336 0.02477 0.01776 -0.0776 0.4258 0.8177
8.500 1.2531 0.02505 0.01815 -0.0766 0.4108 0.8207
8.750 1.2695 0.02539 0.01856 -0.0750 0.3951 0.8237
9.000 1.2840 0.02588 0.01914 -0.0734 0.3783 0.8273
9.250 1.2970 0.02651 0.01985 -0.0716 0.3608 0.8313
9.500 1.3078 0.02720 0.02062 -0.0696 0.3452 0.8351
9.750 1.3165 0.02802 0.02154 -0.0674 0.3293 0.8387
10.000 1.3224 0.02912 0.02268 -0.0652 0.3099 0.8427
10.250 1.3251 0.03054 0.02413 -0.0631 0.2880 0.8471
10.500 1.3232 0.03231 0.02589 -0.0609 0.2653 0.8515
10.750 1.3193 0.03443 0.02800 -0.0590 0.2424 0.8564
11.000 1.3144 0.03698 0.03049 -0.0578 0.2211 0.8615
11.250 1.3102 0.03958 0.03311 -0.0566 0.2014 0.8664
11.500 1.3053 0.04236 0.03590 -0.0557 0.1843 0.8716
11.750 1.3009 0.04532 0.03886 -0.0551 0.1689 0.8772
12.000 1.2955 0.04824 0.04184 -0.0543 0.1548 0.8830
12.250 1.2900 0.05133 0.04497 -0.0538 0.1414 0.8901
12.500 1.2836 0.05442 0.04811 -0.0531 0.1296 0.8984
12.750 1.2766 0.05760 0.05135 -0.0525 0.1190 0.9089
13.250 1.2574 0.06362 0.05754 -0.0504 0.1013 0.9896
13.500 1.2539 0.06754 0.06150 -0.0514 0.0917 0.9999
13.750 1.2474 0.07176 0.06571 -0.0523 0.0834 0.9999
14.000 1.2438 0.07575 0.06977 -0.0533 0.0745 0.9999
14.250 1.2390 0.07995 0.07405 -0.0544 0.0673 0.9999
14.500 1.2320 0.08450 0.07860 -0.0557 0.0615 0.9999
14.750 1.2282 0.08866 0.08284 -0.0568 0.0560 0.9999
15.000 1.2219 0.09327 0.08750 -0.0582 0.0510 0.9999
15.250 1.2170 0.09774 0.09203 -0.0597 0.0463 0.9999
15.500 1.2128 0.10223 0.09663 -0.0613 0.0415 0.9999
15.750 1.2058 0.10721 0.10163 -0.0632 0.0377 0.9999
16.000 1.2023 0.11174 0.10629 -0.0650 0.0337 0.9999
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