74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il) Reynolds number: 200,000 Max Cl/Cd: 78.88 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74130wp2mod-il-200000-n5.txt Download as CSV file: xf-fx74130wp2mod-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: 74-130 WP2 MOD
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1635 0.09201 0.08772 -0.0972 0.8478 0.0250
-9.750 -0.1622 0.08853 0.08428 -0.1000 0.8459 0.0263
-9.500 -0.1600 0.08521 0.08099 -0.1024 0.8437 0.0266
-9.250 -0.1598 0.08151 0.07732 -0.1055 0.8412 0.0271
-9.000 -0.1594 0.07758 0.07341 -0.1084 0.8386 0.0272
-8.750 -0.1612 0.07329 0.06913 -0.1121 0.8363 0.0272
-8.500 -0.1656 0.06954 0.06534 -0.1144 0.8340 0.0273
-8.250 -0.1740 0.06649 0.06225 -0.1148 0.8313 0.0273
-8.000 -0.1796 0.06351 0.05921 -0.1148 0.8285 0.0273
-7.750 -0.1809 0.06050 0.05609 -0.1148 0.8259 0.0274
-7.500 -0.1795 0.05753 0.05299 -0.1145 0.8234 0.0274
-7.250 -0.1844 0.05014 0.04554 -0.1139 0.8212 0.0176
-7.000 -0.1819 0.04698 0.04224 -0.1132 0.8186 0.0167
-6.750 -0.1767 0.04375 0.03882 -0.1123 0.8147 0.0158
-6.500 -0.1690 0.04015 0.03495 -0.1112 0.8112 0.0148
-6.250 -0.1596 0.03559 0.02994 -0.1094 0.8084 0.0135
-6.000 -0.1438 0.03165 0.02538 -0.1074 0.8063 0.0124
-5.500 -0.1061 0.02766 0.02073 -0.1055 0.8009 0.0121
-5.250 -0.0857 0.02549 0.01822 -0.1046 0.7984 0.0122
-5.000 -0.0637 0.02332 0.01569 -0.1038 0.7961 0.0123
-4.750 -0.0398 0.02161 0.01371 -0.1033 0.7941 0.0127
-4.500 -0.0147 0.02037 0.01228 -0.1029 0.7923 0.0132
-4.250 0.0095 0.01979 0.01161 -0.1026 0.7897 0.0148
-4.000 0.0340 0.01916 0.01087 -0.1022 0.7868 0.0164
-3.750 0.0587 0.01825 0.00987 -0.1017 0.7842 0.0170
-3.500 0.0834 0.01744 0.00897 -0.1011 0.7819 0.0175
-3.250 0.1084 0.01676 0.00820 -0.1007 0.7798 0.0181
-3.000 0.1333 0.01608 0.00741 -0.1003 0.7779 0.0191
-2.750 0.1560 0.01564 0.00695 -0.0997 0.7741 0.0215
-2.500 0.1810 0.01532 0.00655 -0.0993 0.7710 0.0260
-2.250 0.2060 0.01480 0.00614 -0.0990 0.7684 0.0574
-2.000 0.2258 0.01328 0.00581 -0.0989 0.7661 0.3695
-1.750 0.2342 0.01252 0.00648 -0.0940 0.7639 0.7674
-1.500 0.2534 0.01291 0.00684 -0.0918 0.7594 0.8152
-1.250 0.2680 0.01323 0.00717 -0.0879 0.7558 0.8498
-1.000 0.2848 0.01337 0.00725 -0.0846 0.7531 0.8706
-0.750 0.3084 0.01335 0.00713 -0.0833 0.7511 0.8802
-0.500 0.3304 0.01341 0.00713 -0.0824 0.7468 0.8872
-0.250 0.3546 0.01341 0.00706 -0.0818 0.7429 0.8913
0.000 0.3810 0.01335 0.00693 -0.0816 0.7400 0.8945
0.250 0.4092 0.01326 0.00675 -0.0818 0.7377 0.8975
0.500 0.4336 0.01329 0.00675 -0.0815 0.7331 0.9007
0.750 0.4593 0.01328 0.00671 -0.0814 0.7288 0.9033
1.000 0.4865 0.01321 0.00659 -0.0815 0.7258 0.9053
1.250 0.5152 0.01312 0.00646 -0.0818 0.7235 0.9072
1.500 0.5377 0.01322 0.00658 -0.0812 0.7178 0.9097
1.750 0.5644 0.01320 0.00656 -0.0813 0.7139 0.9117
2.000 0.5931 0.01313 0.00646 -0.0817 0.7110 0.9137
2.250 0.6188 0.01318 0.00654 -0.0817 0.7063 0.9157
2.500 0.6441 0.01320 0.00659 -0.0816 0.7013 0.9175
2.750 0.6718 0.01314 0.00653 -0.0818 0.6980 0.9193
3.000 0.6980 0.01315 0.00658 -0.0817 0.6941 0.9212
3.250 0.7222 0.01324 0.00674 -0.0815 0.6888 0.9232
3.500 0.7502 0.01322 0.00675 -0.0818 0.6852 0.9249
3.750 0.7780 0.01321 0.00677 -0.0821 0.6816 0.9270
4.000 0.8016 0.01334 0.00698 -0.0817 0.6758 0.9298
4.250 0.8290 0.01334 0.00707 -0.0819 0.6721 0.9316
4.500 0.8580 0.01331 0.00708 -0.0824 0.6690 0.9333
4.750 0.8805 0.01347 0.00735 -0.0818 0.6628 0.9359
5.000 0.9087 0.01344 0.00738 -0.0821 0.6580 0.9381
5.250 0.9338 0.01345 0.00750 -0.0818 0.6500 0.9410
5.500 0.9611 0.01329 0.00738 -0.0817 0.6389 0.9440
5.750 0.9860 0.01318 0.00729 -0.0812 0.6236 0.9472
6.000 1.0107 0.01315 0.00729 -0.0807 0.6072 0.9507
6.250 1.0350 0.01320 0.00730 -0.0801 0.5878 0.9548
6.500 1.0562 0.01339 0.00753 -0.0791 0.5651 0.9603
6.750 1.0766 0.01366 0.00778 -0.0781 0.5359 0.9684
7.250 1.0982 0.01475 0.00858 -0.0732 0.4346 1.0000
7.500 1.0869 0.01616 0.00955 -0.0676 0.3617 1.0000
7.750 1.0781 0.01789 0.01093 -0.0632 0.3011 1.0000
8.000 1.0733 0.01967 0.01242 -0.0597 0.2462 1.0000
8.250 1.0708 0.02149 0.01396 -0.0568 0.1944 1.0000
8.500 1.0703 0.02328 0.01552 -0.0542 0.1467 1.0000
8.750 1.0722 0.02501 0.01702 -0.0520 0.1070 1.0000
9.000 1.0763 0.02663 0.01849 -0.0501 0.0777 1.0000
9.250 1.0826 0.02815 0.01992 -0.0484 0.0577 1.0000
9.500 1.0897 0.02966 0.02137 -0.0468 0.0449 1.0000
9.750 1.0986 0.03106 0.02280 -0.0454 0.0363 1.0000
10.000 1.1071 0.03252 0.02429 -0.0441 0.0296 1.0000
10.250 1.1148 0.03407 0.02585 -0.0428 0.0237 1.0000
10.500 1.1239 0.03555 0.02743 -0.0416 0.0203 1.0000
10.750 1.1316 0.03718 0.02913 -0.0403 0.0173 1.0000
11.000 1.1350 0.03924 0.03129 -0.0388 0.0149 1.0000
11.250 1.1446 0.04080 0.03298 -0.0379 0.0130 1.0000
11.500 1.1543 0.04237 0.03462 -0.0370 0.0110 1.0000
11.750 1.1584 0.04452 0.03685 -0.0359 0.0100 1.0000
12.000 1.1628 0.04674 0.03919 -0.0348 0.0094 1.0000
12.250 1.1697 0.04877 0.04138 -0.0338 0.0089 1.0000
12.500 1.1765 0.05088 0.04363 -0.0329 0.0084 1.0000
12.750 1.1837 0.05302 0.04591 -0.0320 0.0081 1.0000
13.000 1.1911 0.05521 0.04825 -0.0312 0.0077 1.0000
13.250 1.1983 0.05749 0.05068 -0.0305 0.0074 1.0000
13.500 1.2049 0.05989 0.05324 -0.0299 0.0071 1.0000
13.750 1.2103 0.06246 0.05597 -0.0294 0.0069 1.0000
14.000 1.2149 0.06523 0.05896 -0.0290 0.0067 1.0000
14.250 1.2176 0.06826 0.06218 -0.0286 0.0066 1.0000
14.500 1.2181 0.07161 0.06573 -0.0284 0.0065 1.0000
14.750 1.2167 0.07534 0.06968 -0.0284 0.0064 1.0000
15.000 1.2119 0.07962 0.07418 -0.0287 0.0063 1.0000
15.250 1.2062 0.08408 0.07888 -0.0292 0.0063 1.0000
15.500 1.1968 0.08922 0.08427 -0.0301 0.0062 1.0000
15.750 1.1863 0.09465 0.08995 -0.0315 0.0062 1.0000
16.000 1.1735 0.10067 0.09621 -0.0335 0.0062 1.0000
16.250 1.1590 0.10718 0.10294 -0.0360 0.0061 1.0000
16.500 1.1445 0.11399 0.10998 -0.0391 0.0061 1.0000
16.750 1.1298 0.12122 0.11742 -0.0428 0.0061 1.0000
17.000 1.1145 0.12899 0.12540 -0.0471 0.0062 1.0000
17.250 1.0993 0.13739 0.13400 -0.0522 0.0062 1.0000
17.500 1.0813 0.14729 0.14412 -0.0586 0.0063 1.0000
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Polar data table (+)
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