FX 84-W-218 (fx84w218-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 84-W-218 (fx84w218-il) Reynolds number: 50,000 Max Cl/Cd: 6.7 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w218-il-50000-n5.txt Download as CSV file: xf-fx84w218-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-218
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.2800 0.12539 0.11745 -0.0752 0.9707 0.1159
-13.500 -0.2728 0.12044 0.11245 -0.0794 0.9665 0.1183
-13.000 -0.3000 0.10471 0.09664 -0.0899 0.9570 0.1245
-12.750 -0.2804 0.10211 0.09400 -0.0928 0.9526 0.1275
-12.500 -0.3903 0.07957 0.07124 -0.1057 0.9486 0.1326
-12.250 -0.4991 0.06443 0.05559 -0.1132 0.9382 0.1335
-12.000 -0.5168 0.05997 0.05088 -0.1153 0.9311 0.1358
-11.750 -0.4991 0.05888 0.04981 -0.1157 0.9239 0.1390
-11.500 -0.5013 0.05587 0.04658 -0.1172 0.9178 0.1424
-11.250 -0.5232 0.05343 0.04389 -0.1151 0.9072 0.1449
-11.000 -0.5217 0.05130 0.04156 -0.1150 0.9009 0.1484
-10.750 -0.5139 0.05068 0.04096 -0.1133 0.8927 0.1516
-10.500 -0.5118 0.04936 0.03951 -0.1119 0.8853 0.1556
-10.250 -0.5223 0.04796 0.03784 -0.1089 0.8773 0.1593
-10.000 -0.5170 0.04738 0.03727 -0.1066 0.8694 0.1630
-9.750 -0.5019 0.04650 0.03635 -0.1058 0.8641 0.1681
-9.500 -0.5122 0.04593 0.03563 -0.1014 0.8553 0.1719
-9.250 -0.5093 0.04523 0.03485 -0.0987 0.8481 0.1766
-9.000 -0.4885 0.04450 0.03412 -0.0984 0.8436 0.1829
-8.750 -0.4956 0.04414 0.03361 -0.0940 0.8354 0.1877
-8.500 -0.4881 0.04368 0.03314 -0.0916 0.8285 0.1933
-8.250 -0.4704 0.04301 0.03243 -0.0907 0.8239 0.2011
-8.000 -0.4617 0.04248 0.03181 -0.0885 0.8182 0.2084
-7.750 -0.4651 0.04249 0.03187 -0.0842 0.8097 0.2136
-7.500 -0.4525 0.04187 0.03107 -0.0825 0.8045 0.2230
-7.250 -0.4270 0.04130 0.03059 -0.0825 0.8010 0.2333
-7.000 -0.4395 0.04142 0.03064 -0.0769 0.7918 0.2394
-6.750 -0.4282 0.04114 0.03043 -0.0748 0.7858 0.2485
-6.500 -0.4085 0.04060 0.02980 -0.0739 0.7818 0.2616
-6.250 -0.3828 0.04004 0.02926 -0.0738 0.7788 0.2762
-6.000 -0.4044 0.04050 0.02974 -0.0669 0.7678 0.2813
-5.750 -0.3885 0.04018 0.02945 -0.0653 0.7629 0.2954
-5.500 -0.3646 0.03972 0.02905 -0.0649 0.7595 0.3125
-5.250 -0.3715 0.03991 0.02926 -0.0601 0.7517 0.3230
-5.000 -0.3687 0.03988 0.02925 -0.0566 0.7447 0.3374
-4.750 -0.3482 0.03959 0.02902 -0.0556 0.7405 0.3574
-4.500 -0.3213 0.03922 0.02870 -0.0554 0.7377 0.3814
-4.250 -0.3379 0.03975 0.02934 -0.0493 0.7281 0.3916
-4.000 -0.3247 0.03972 0.02940 -0.0472 0.7226 0.4132
-3.750 -0.3013 0.03957 0.02931 -0.0463 0.7189 0.4400
-3.500 -0.2720 0.03943 0.02924 -0.0462 0.7163 0.4690
-3.250 -0.2898 0.04023 0.03011 -0.0402 0.7062 0.4830
-3.000 -0.2720 0.04037 0.03030 -0.0385 0.7012 0.5096
-2.750 -0.2454 0.04052 0.03052 -0.0376 0.6978 0.5365
-2.500 -0.2299 0.04092 0.03096 -0.0356 0.6930 0.5601
-2.250 -0.2328 0.04169 0.03177 -0.0316 0.6847 0.5790
-2.000 -0.2120 0.04204 0.03213 -0.0300 0.6801 0.6026
-1.750 -0.1846 0.04229 0.03235 -0.0291 0.6769 0.6262
-1.500 -0.1829 0.04309 0.03314 -0.0257 0.6698 0.6446
-1.250 -0.1739 0.04371 0.03375 -0.0231 0.6633 0.6641
-1.000 -0.1518 0.04404 0.03403 -0.0218 0.6591 0.6847
-0.750 -0.1235 0.04431 0.03424 -0.0209 0.6562 0.7039
-0.500 -0.1287 0.04546 0.03543 -0.0168 0.6476 0.7179
-0.250 -0.1147 0.04601 0.03594 -0.0147 0.6421 0.7353
0.000 -0.0917 0.04627 0.03612 -0.0135 0.6383 0.7538
0.250 -0.0630 0.04643 0.03621 -0.0127 0.6356 0.7714
0.500 -0.0747 0.04781 0.03764 -0.0083 0.6257 0.7852
0.750 -0.0565 0.04823 0.03801 -0.0067 0.6210 0.8019
1.000 -0.0317 0.04840 0.03811 -0.0057 0.6176 0.8195
1.500 -0.0141 0.05012 0.03981 -0.0016 0.6042 0.8498
1.750 0.0111 0.05049 0.04012 -0.0012 0.6002 0.8653
2.000 0.0425 0.05063 0.04019 -0.0015 0.5972 0.8808
2.250 0.0454 0.05206 0.04163 -0.0001 0.5884 0.8957
2.500 0.0750 0.05282 0.04236 -0.0015 0.5830 0.9081
2.750 0.1134 0.05324 0.04272 -0.0036 0.5794 0.9204
3.000 0.1575 0.05344 0.04285 -0.0064 0.5769 0.9321
3.250 0.1660 0.05568 0.04512 -0.0077 0.5661 0.9435
3.500 0.2081 0.05634 0.04574 -0.0113 0.5617 0.9531
3.750 0.2565 0.05671 0.04606 -0.0152 0.5587 0.9620
4.000 0.2727 0.05889 0.04827 -0.0177 0.5492 0.9721
4.250 0.3099 0.05976 0.04912 -0.0211 0.5438 0.9818
4.500 0.3542 0.06013 0.04946 -0.0247 0.5404 0.9917
5.000 0.3459 0.06225 0.05153 -0.0205 0.5257 1.0000
5.250 0.3550 0.06203 0.05123 -0.0181 0.5219 1.0000
5.500 0.3728 0.06168 0.05079 -0.0165 0.5194 1.0000
5.750 0.3412 0.06414 0.05322 -0.0124 0.5075 1.0000
6.000 0.3610 0.06438 0.05339 -0.0117 0.5035 1.0000
6.250 0.3886 0.06435 0.05329 -0.0115 0.5008 1.0000
6.500 0.3700 0.06728 0.05621 -0.0096 0.4893 1.0000
6.750 0.3934 0.06769 0.05657 -0.0095 0.4850 1.0000
7.000 0.4230 0.06776 0.05658 -0.0096 0.4822 1.0000
7.250 0.4077 0.07090 0.05974 -0.0083 0.4706 1.0000
7.500 0.4316 0.07141 0.06022 -0.0083 0.4663 1.0000
7.750 0.4623 0.07144 0.06020 -0.0084 0.4635 1.0000
8.000 0.4469 0.07489 0.06369 -0.0075 0.4517 1.0000
8.250 0.4716 0.07538 0.06416 -0.0075 0.4475 1.0000
8.500 0.5030 0.07533 0.06408 -0.0076 0.4448 1.0000
8.750 0.4863 0.07913 0.06791 -0.0069 0.4325 1.0000
9.000 0.5119 0.07954 0.06833 -0.0070 0.4286 1.0000
9.500 0.5249 0.08364 0.07246 -0.0066 0.4132 1.0000
9.750 0.5522 0.08387 0.07269 -0.0066 0.4096 1.0000
10.250 0.5629 0.08835 0.07723 -0.0065 0.3938 1.0000
10.500 0.5920 0.08838 0.07726 -0.0064 0.3908 1.0000
10.750 0.5772 0.09270 0.08165 -0.0066 0.3790 1.0000
11.000 0.6005 0.09324 0.08221 -0.0065 0.3747 1.0000
11.500 0.6110 0.09815 0.08719 -0.0069 0.3593 1.0000
11.750 0.6374 0.09831 0.08737 -0.0067 0.3558 1.0000
12.000 0.6255 0.10280 0.09192 -0.0074 0.3452 1.0000
12.250 0.6450 0.10367 0.09284 -0.0074 0.3401 1.0000
12.500 0.6736 0.10352 0.09271 -0.0072 0.3372 1.0000
12.750 0.6546 0.10902 0.09828 -0.0082 0.3253 1.0000
13.000 0.6787 0.10930 0.09860 -0.0081 0.3213 1.0000
13.250 0.6699 0.11379 0.10315 -0.0091 0.3118 1.0000
13.500 0.6849 0.11520 0.10461 -0.0093 0.3061 1.0000
13.750 0.7120 0.11502 0.10446 -0.0091 0.3030 1.0000
14.000 0.6942 0.12083 0.11034 -0.0107 0.2919 1.0000
14.250 0.7158 0.12131 0.11087 -0.0106 0.2876 1.0000
14.750 0.7218 0.12746 0.11713 -0.0124 0.2729 1.0000
15.000 0.7477 0.12724 0.11695 -0.0121 0.2696 1.0000
15.250 0.7314 0.13320 0.12297 -0.0142 0.2592 1.0000
15.500 0.7514 0.13378 0.12360 -0.0142 0.2548 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 84-W-218 (fx84w218-il)