WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 74-080 (fx74080-il) Reynolds number: 100,000 Max Cl/Cd: 57.97 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74080-il-100000-n5.txt Download as CSV file: xf-fx74080-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 74-080
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2853 0.10200 0.09731 -0.0586 0.9721 0.0289
-8.250 -0.2730 0.09887 0.09419 -0.0639 0.9670 0.0295
-8.000 -0.2624 0.09571 0.09103 -0.0690 0.9607 0.0298
-7.750 -0.2499 0.09243 0.08777 -0.0756 0.9542 0.0301
-7.500 -0.2342 0.08848 0.08381 -0.0821 0.9485 0.0302
-7.250 -0.2180 0.08448 0.07977 -0.0877 0.9434 0.0303
-7.000 -0.2143 0.07920 0.07456 -0.0816 0.9426 0.0339
-6.750 -0.1955 0.07529 0.07062 -0.0873 0.9392 0.0390
-6.500 -0.1849 0.07212 0.06741 -0.0911 0.9322 0.0398
-6.250 -0.1517 0.06813 0.06318 -0.1053 0.9264 0.0432
-6.000 -0.1374 0.06524 0.06009 -0.1086 0.9195 0.0435
-5.750 -0.1274 0.05973 0.05470 -0.1090 0.9162 0.0447
-5.500 -0.1094 0.05594 0.05087 -0.1105 0.9136 0.0464
-5.250 -0.0959 0.05300 0.04784 -0.1114 0.9083 0.0479
-5.000 -0.0759 0.04960 0.04428 -0.1135 0.9038 0.0491
-4.750 -0.0400 0.04441 0.03860 -0.1172 0.9007 0.0288
-4.500 -0.0230 0.04122 0.03523 -0.1177 0.8964 0.0265
-4.250 -0.0025 0.03807 0.03169 -0.1181 0.8917 0.0245
-4.000 0.0264 0.03463 0.02783 -0.1195 0.8888 0.0227
-3.750 0.0587 0.03130 0.02396 -0.1210 0.8866 0.0211
-3.500 0.0779 0.02909 0.02128 -0.1194 0.8815 0.0203
-3.250 0.1040 0.02702 0.01875 -0.1192 0.8780 0.0202
-3.000 0.1343 0.02504 0.01631 -0.1196 0.8756 0.0204
-2.750 0.1660 0.02344 0.01435 -0.1203 0.8737 0.0217
-2.500 0.1868 0.02295 0.01362 -0.1191 0.8693 0.0283
-2.250 0.2117 0.02200 0.01239 -0.1182 0.8655 0.0303
-2.000 0.2391 0.02054 0.01086 -0.1181 0.8629 0.0327
-1.750 0.2685 0.01969 0.00990 -0.1185 0.8608 0.0369
-1.500 0.2891 0.01924 0.00924 -0.1171 0.8565 0.0477
-1.250 0.3114 0.01875 0.00887 -0.1162 0.8522 0.0912
-1.000 0.3461 0.01611 0.00876 -0.1170 0.8513 1.0000
-0.750 0.3755 0.01620 0.00853 -0.1174 0.8486 1.0000
-0.500 0.4070 0.01627 0.00835 -0.1183 0.8465 1.0000
-0.250 0.4205 0.01669 0.00862 -0.1159 0.8398 1.0000
0.000 0.4482 0.01683 0.00858 -0.1161 0.8365 1.0000
0.250 0.4789 0.01692 0.00852 -0.1169 0.8342 1.0000
0.500 0.4958 0.01732 0.00883 -0.1152 0.8282 1.0000
0.750 0.5216 0.01752 0.00895 -0.1150 0.8242 1.0000
1.000 0.5517 0.01763 0.00900 -0.1156 0.8216 1.0000
1.250 0.5711 0.01800 0.00934 -0.1144 0.8161 1.0000
1.500 0.5946 0.01828 0.00962 -0.1139 0.8115 1.0000
1.750 0.6241 0.01841 0.00975 -0.1144 0.8087 1.0000
2.250 0.6671 0.01909 0.01048 -0.1126 0.7983 1.0000
2.500 0.6970 0.01921 0.01066 -0.1131 0.7954 1.0000
2.750 0.7146 0.01967 0.01119 -0.1116 0.7889 1.0000
3.000 0.7394 0.01993 0.01165 -0.1113 0.7843 1.0000
3.250 0.7703 0.02002 0.01186 -0.1119 0.7816 1.0000
3.500 0.7837 0.02063 0.01259 -0.1097 0.7736 1.0000
3.750 0.8123 0.02077 0.01289 -0.1099 0.7698 1.0000
4.250 0.8562 0.02141 0.01395 -0.1081 0.7576 1.0000
4.500 0.8973 0.01858 0.01133 -0.1066 0.7255 1.0000
4.750 0.9194 0.01586 0.00790 -0.0997 0.5045 1.0000
5.000 0.8907 0.01899 0.00897 -0.0903 0.1951 1.0000
5.250 0.8822 0.02148 0.01040 -0.0846 0.0412 1.0000
5.500 0.8931 0.02263 0.01159 -0.0818 0.0274 1.0000
5.750 0.9048 0.02375 0.01291 -0.0790 0.0236 1.0000
6.000 0.9125 0.02516 0.01449 -0.0759 0.0213 1.0000
6.250 0.9169 0.02703 0.01646 -0.0723 0.0200 1.0000
6.500 0.9317 0.02854 0.01809 -0.0702 0.0190 1.0000
6.750 0.9528 0.02984 0.01952 -0.0690 0.0160 1.0000
7.000 0.9775 0.03140 0.02119 -0.0686 0.0129 1.0000
7.250 1.0214 0.03413 0.02412 -0.0707 0.0123 1.0000
7.500 1.0664 0.03757 0.02790 -0.0730 0.0121 1.0000
7.750 1.0970 0.04084 0.03156 -0.0730 0.0121 1.0000
8.000 1.1202 0.04433 0.03571 -0.0717 0.0126 1.0000
8.250 1.1360 0.04777 0.03963 -0.0695 0.0129 1.0000
8.500 1.1464 0.05131 0.04361 -0.0668 0.0134 1.0000
8.750 1.1524 0.05478 0.04749 -0.0637 0.0140 1.0000
9.000 1.1537 0.05833 0.05141 -0.0603 0.0144 1.0000
9.250 1.1512 0.06182 0.05523 -0.0568 0.0149 1.0000
9.500 1.1442 0.06492 0.05861 -0.0529 0.0152 1.0000
9.750 1.1330 0.06819 0.06212 -0.0490 0.0156 1.0000
10.000 1.1203 0.07141 0.06558 -0.0455 0.0159 1.0000
10.250 1.1058 0.07482 0.06919 -0.0427 0.0161 1.0000
10.500 1.0898 0.07850 0.07307 -0.0404 0.0164 1.0000
10.750 1.0726 0.08248 0.07724 -0.0389 0.0166 1.0000
11.000 1.0553 0.08670 0.08163 -0.0381 0.0167 1.0000
11.250 1.0371 0.09136 0.08644 -0.0382 0.0168 1.0000
11.500 1.0184 0.09653 0.09175 -0.0391 0.0169 1.0000
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Polar data table (+)
Polar graphs
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