WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il) Reynolds number: 100,000 Max Cl/Cd: 1.21 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w258-il-100000.txt Download as CSV file: xf-fx77w258-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-W-258 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6053 0.09281 0.08645 -0.0507 0.6248 0.0756
-14.250 -0.6329 0.08617 0.07963 -0.0536 0.6236 0.0750
-14.000 -0.6652 0.07971 0.07293 -0.0558 0.6226 0.0742
-13.750 -0.7005 0.07364 0.06656 -0.0572 0.6218 0.0733
-13.500 -0.7304 0.06857 0.06116 -0.0577 0.6205 0.0728
-13.250 -0.7469 0.06489 0.05719 -0.0575 0.6184 0.0729
-13.000 -0.7576 0.06181 0.05383 -0.0571 0.6162 0.0732
-12.750 -0.7645 0.05904 0.05079 -0.0565 0.6138 0.0736
-12.500 -0.7680 0.05645 0.04798 -0.0558 0.6109 0.0741
-12.250 -0.7687 0.05411 0.04539 -0.0549 0.6078 0.0746
-12.000 -0.7701 0.05216 0.04317 -0.0534 0.6049 0.0751
-11.750 -0.7705 0.05041 0.04108 -0.0517 0.6022 0.0757
-11.500 -0.7441 0.04912 0.03981 -0.0519 0.5988 0.0771
-11.250 -0.7217 0.04802 0.03864 -0.0518 0.5961 0.0784
-11.000 -0.7040 0.04680 0.03725 -0.0513 0.5939 0.0796
-10.750 -0.6851 0.04543 0.03572 -0.0510 0.5916 0.0809
-10.500 -0.6617 0.04417 0.03432 -0.0510 0.5891 0.0821
-10.250 -0.6277 0.04329 0.03357 -0.0519 0.5864 0.0839
-10.000 -0.6005 0.04243 0.03267 -0.0521 0.5840 0.0862
-9.750 -0.5744 0.04157 0.03170 -0.0521 0.5818 0.0887
-9.500 -0.5446 0.04094 0.03116 -0.0525 0.5796 0.0921
-9.250 -0.5181 0.04026 0.03040 -0.0525 0.5778 0.0959
-9.000 -0.4895 0.03973 0.02987 -0.0526 0.5760 0.1006
-8.750 -0.4572 0.03931 0.02956 -0.0527 0.5743 0.1060
-8.500 -0.4280 0.03899 0.02937 -0.0527 0.5727 0.1122
-8.250 -0.4020 0.03867 0.02923 -0.0527 0.5706 0.1191
-8.000 -0.3800 0.03840 0.02911 -0.0524 0.5684 0.1269
-7.750 -0.3608 0.03814 0.02901 -0.0519 0.5667 0.1368
-7.500 -0.3449 0.03780 0.02890 -0.0510 0.5651 0.1502
-7.250 -0.3340 0.03738 0.02874 -0.0496 0.5634 0.1671
-7.000 -0.3289 0.03688 0.02848 -0.0476 0.5616 0.1920
-6.750 -0.3321 0.03615 0.02814 -0.0448 0.5601 0.2244
-6.500 -0.3366 0.03509 0.02756 -0.0427 0.5588 0.2821
-6.250 -0.3382 0.03424 0.02742 -0.0405 0.5577 0.3772
-6.000 -0.3057 0.03712 0.03109 -0.0360 0.5560 0.4866
-5.750 -0.2698 0.03964 0.03357 -0.0340 0.5541 0.5262
-5.500 -0.2569 0.04034 0.03413 -0.0337 0.5526 0.5589
-5.250 -0.2374 0.04233 0.03616 -0.0338 0.5506 0.5783
-5.000 -0.2074 0.04589 0.03979 -0.0330 0.5484 0.5858
-4.750 -0.1932 0.04826 0.04218 -0.0327 0.5474 0.6012
-4.500 -0.1871 0.05056 0.04450 -0.0326 0.5469 0.6177
-4.250 -0.1722 0.05445 0.04847 -0.0312 0.5469 0.6231
-4.000 -0.1782 0.05677 0.05079 -0.0306 0.5487 0.6381
-3.750 -0.2095 0.06337 0.05762 -0.0309 0.5725 0.6413
-3.500 -0.3800 0.06725 0.06192 -0.0313 0.6278 0.6377
-3.250 -0.3673 0.06939 0.06403 -0.0267 0.6217 0.6450
-3.000 -0.3406 0.07148 0.06600 -0.0254 0.6185 0.6600
-2.750 -0.3141 0.07445 0.06891 -0.0218 0.6166 0.6698
-2.500 -0.3362 0.07419 0.06861 -0.0194 0.6037 0.6801
-2.250 -0.3204 0.07613 0.07052 -0.0146 0.5992 0.6880
-2.000 -0.2911 0.07802 0.07228 -0.0135 0.5966 0.7028
-1.750 -0.3089 0.07886 0.07313 -0.0085 0.5875 0.7084
-1.500 -0.2921 0.07973 0.07389 -0.0082 0.5807 0.7229
-1.250 -0.2762 0.08120 0.07533 -0.0033 0.5775 0.7307
-1.000 -0.2451 0.08296 0.07695 -0.0032 0.5754 0.7460
-0.750 -0.2725 0.08315 0.07719 0.0020 0.5662 0.7508
-0.500 -0.2596 0.08407 0.07803 0.0037 0.5605 0.7635
-0.250 -0.2446 0.08499 0.07889 0.0071 0.5574 0.7736
0.000 -0.2174 0.08656 0.08035 0.0073 0.5554 0.7870
0.250 -0.1944 0.08814 0.08187 0.0105 0.5541 0.7972
0.500 -0.1583 0.09083 0.08444 0.0092 0.5532 0.8114
0.750 -0.2126 0.08831 0.08199 0.0138 0.5388 0.8129
1.000 -0.1965 0.08911 0.08274 0.0172 0.5362 0.8225
1.250 -0.1621 0.09101 0.08451 0.0152 0.5343 0.8330
1.500 -0.1345 0.09259 0.08602 0.0169 0.5332 0.8390
1.750 -0.1782 0.09126 0.08475 0.0202 0.5204 0.8415
2.000 -0.1549 0.09227 0.08567 0.0195 0.5171 0.8453
2.250 -0.1241 0.09374 0.08705 0.0176 0.5149 0.8477
2.500 -0.0878 0.09583 0.08903 0.0152 0.5134 0.8497
2.750 -0.0471 0.09866 0.09176 0.0122 0.5124 0.8517
3.000 -0.0940 0.09740 0.09058 0.0139 0.5003 0.8535
3.250 -0.0712 0.09860 0.09172 0.0128 0.4970 0.8559
3.500 -0.0473 0.09989 0.09295 0.0126 0.4948 0.8584
3.750 -0.0186 0.10176 0.09476 0.0117 0.4933 0.8612
4.000 0.0171 0.10443 0.09735 0.0098 0.4923 0.8633
4.250 0.0590 0.10803 0.10087 0.0072 0.4915 0.8646
4.500 -0.0011 0.10524 0.09819 0.0095 0.4783 0.8650
4.750 0.0265 0.10693 0.09983 0.0077 0.4754 0.8660
5.000 0.0595 0.10913 0.10196 0.0055 0.4734 0.8669
5.250 0.0979 0.11207 0.10484 0.0029 0.4722 0.8679
5.500 0.1404 0.11588 0.10859 0.0000 0.4713 0.8689
5.750 0.0841 0.11370 0.10652 0.0017 0.4594 0.8692
6.000 0.1091 0.11547 0.10825 -0.0001 0.4561 0.8700
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