FX 78-K-150/20 (fx78k150-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 78-K-150/20 (fx78k150-il) Reynolds number: 200,000 Max Cl/Cd: 46.22 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx78k150-il-200000.txt Download as CSV file: xf-fx78k150-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 78-K-150/20
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1148 0.10995 0.10551 -0.1131 0.8042 0.0501
-11.750 -0.1229 0.10690 0.10254 -0.1163 0.8028 0.0510
-11.500 -0.1287 0.10364 0.09934 -0.1189 0.8016 0.0513
-11.250 -0.1289 0.10025 0.09599 -0.1207 0.8004 0.0514
-11.000 -0.1210 0.09502 0.09078 -0.1197 0.7996 0.0527
-10.750 -0.1086 0.09279 0.08854 -0.1189 0.7983 0.0541
-10.500 -0.1020 0.09037 0.08613 -0.1190 0.7972 0.0559
-10.250 -0.1010 0.08754 0.08332 -0.1199 0.7960 0.0567
-10.000 -0.1024 0.08441 0.08022 -0.1208 0.7948 0.0578
-9.750 -0.1067 0.08112 0.07696 -0.1220 0.7934 0.0595
-9.500 -0.1368 0.07540 0.07133 -0.1280 0.7918 0.0631
-9.250 -0.1655 0.07129 0.06722 -0.1303 0.7902 0.0635
-9.000 -0.1830 0.06862 0.06457 -0.1291 0.7886 0.0635
-8.750 -0.2134 0.06731 0.06319 -0.1253 0.7868 0.0638
-8.500 -0.2345 0.06596 0.06168 -0.1221 0.7848 0.0641
-8.250 -0.2436 0.06374 0.05930 -0.1196 0.7828 0.0642
-8.000 -0.2813 0.04972 0.04474 -0.1150 0.7812 0.0404
-7.750 -0.2787 0.04578 0.04077 -0.1134 0.7799 0.0383
-7.500 -0.2812 0.04262 0.03731 -0.1102 0.7787 0.0367
-7.250 -0.2794 0.04014 0.03441 -0.1069 0.7776 0.0380
-7.000 -0.2761 0.03836 0.03227 -0.1039 0.7753 0.0390
-6.750 -0.2702 0.03673 0.03028 -0.1011 0.7726 0.0396
-6.250 -0.2514 0.03275 0.02568 -0.0965 0.7690 0.0422
-6.000 -0.2339 0.03235 0.02522 -0.0953 0.7673 0.0450
-5.750 -0.2139 0.03142 0.02404 -0.0940 0.7658 0.0482
-5.500 -0.1907 0.03052 0.02280 -0.0929 0.7645 0.0509
-5.250 -0.1673 0.02917 0.02136 -0.0923 0.7634 0.0557
-5.000 -0.1689 0.02991 0.02212 -0.0890 0.7597 0.0584
-4.750 -0.1635 0.03019 0.02233 -0.0861 0.7566 0.0617
-4.500 -0.1474 0.02972 0.02174 -0.0844 0.7542 0.0663
-4.250 -0.1287 0.02944 0.02148 -0.0832 0.7525 0.0722
-4.000 -0.1053 0.02918 0.02108 -0.0825 0.7512 0.0785
-3.750 -0.0816 0.02863 0.02059 -0.0819 0.7501 0.0873
-3.500 -0.1066 0.03001 0.02197 -0.0746 0.7444 0.0885
-3.250 -0.1277 0.03097 0.02290 -0.0673 0.7409 0.0894
-3.000 -0.1110 0.03075 0.02270 -0.0657 0.7386 0.0983
-2.750 -0.0795 0.03027 0.02225 -0.0662 0.7369 0.1150
-2.500 -0.0476 0.02981 0.02189 -0.0668 0.7357 0.1418
-2.250 -0.0178 0.02896 0.02151 -0.0670 0.7348 0.2345
-0.500 0.1751 0.03099 0.02544 -0.0652 0.7196 0.9596
-0.250 0.3210 0.03155 0.02579 -0.0875 0.7201 0.9780
0.000 0.4397 0.03137 0.02547 -0.1052 0.7204 0.9910
0.250 0.5103 0.03111 0.02512 -0.1137 0.7200 0.9985
0.500 0.4421 0.03388 0.02799 -0.1011 0.7083 1.0000
0.750 0.4744 0.03380 0.02784 -0.1020 0.7070 1.0000
1.000 0.5052 0.03373 0.02771 -0.1024 0.7061 1.0000
1.250 0.5367 0.03366 0.02760 -0.1029 0.7053 1.0000
1.500 0.4417 0.03582 0.02980 -0.0847 0.6925 1.0000
1.750 0.4565 0.03616 0.03011 -0.0829 0.6898 1.0000
2.000 0.5145 0.03574 0.02965 -0.0874 0.6908 1.0000
2.250 0.4426 0.03698 0.03090 -0.0727 0.6783 1.0000
2.500 0.3983 0.03808 0.03199 -0.0625 0.6686 1.0000
2.750 0.4184 0.03813 0.03202 -0.0613 0.6660 1.0000
3.000 0.4480 0.03806 0.03191 -0.0614 0.6645 1.0000
3.250 0.4816 0.03793 0.03176 -0.0620 0.6634 1.0000
3.500 0.4615 0.03919 0.03301 -0.0565 0.6525 1.0000
3.750 0.4917 0.03922 0.03304 -0.0569 0.6509 1.0000
4.000 0.4964 0.04022 0.03404 -0.0548 0.6435 1.0000
4.250 0.5184 0.04055 0.03437 -0.0545 0.6394 1.0000
4.500 0.5485 0.04061 0.03445 -0.0549 0.6375 1.0000
4.750 0.5811 0.04057 0.03443 -0.0556 0.6362 1.0000
5.000 0.6158 0.04041 0.03430 -0.0564 0.6353 1.0000
5.250 0.6096 0.04207 0.03598 -0.0538 0.6242 1.0000
5.500 0.6430 0.04190 0.03587 -0.0545 0.6227 1.0000
5.750 0.6777 0.04167 0.03568 -0.0553 0.6217 1.0000
6.000 0.6752 0.04333 0.03738 -0.0531 0.6108 1.0000
6.250 0.7077 0.04315 0.03726 -0.0537 0.6092 1.0000
6.500 0.7137 0.04453 0.03869 -0.0524 0.6004 1.0000
6.750 0.7402 0.04469 0.03894 -0.0526 0.5973 1.0000
7.000 0.7740 0.04433 0.03867 -0.0531 0.5956 1.0000
7.250 0.8072 0.04404 0.03848 -0.0538 0.5943 1.0000
7.500 0.8453 0.04312 0.03770 -0.0545 0.5929 1.0000
8.000 0.9818 0.03205 0.02696 -0.0570 0.5811 1.0000
8.250 1.0529 0.02278 0.01654 -0.0543 0.3889 1.0000
8.500 1.0294 0.02584 0.01911 -0.0497 0.3146 1.0000
8.750 0.9992 0.02961 0.02225 -0.0448 0.2197 1.0000
9.000 0.9682 0.03365 0.02552 -0.0404 0.1082 1.0000
9.250 0.9514 0.03708 0.02848 -0.0371 0.0492 1.0000
9.500 0.9562 0.03896 0.03040 -0.0356 0.0413 1.0000
9.750 0.9617 0.04084 0.03234 -0.0343 0.0379 1.0000
10.000 0.9612 0.04328 0.03487 -0.0326 0.0351 1.0000
10.250 0.9667 0.04523 0.03691 -0.0312 0.0329 1.0000
10.500 0.9743 0.04696 0.03870 -0.0301 0.0317 1.0000
10.750 0.9824 0.04864 0.04043 -0.0289 0.0306 1.0000
11.000 0.9883 0.05040 0.04212 -0.0274 0.0274 1.0000
11.250 1.0030 0.05120 0.04289 -0.0252 0.0263 1.0000
11.500 1.0238 0.05173 0.04346 -0.0241 0.0260 1.0000
11.750 1.0488 0.05210 0.04392 -0.0229 0.0255 1.0000
12.000 1.0858 0.05214 0.04406 -0.0217 0.0253 1.0000
12.250 1.1299 0.05281 0.04488 -0.0212 0.0252 1.0000
12.500 1.1737 0.05458 0.04689 -0.0211 0.0254 1.0000
12.750 1.1791 0.05636 0.04890 -0.0198 0.0239 1.0000
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Polar data table (+)
Polar graphs
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