74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il) Reynolds number: 200,000 Max Cl/Cd: 82.13 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74130wp2mod-il-200000.txt Download as CSV file: xf-fx74130wp2mod-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1456 0.09154 0.08792 -0.1080 0.9355 0.0380
-9.750 -0.1420 0.08795 0.08434 -0.1138 0.9314 0.0387
-9.500 -0.1396 0.08451 0.08091 -0.1176 0.9275 0.0389
-9.250 -0.1407 0.08062 0.07703 -0.1219 0.9226 0.0390
-9.000 -0.1453 0.07675 0.07311 -0.1260 0.9181 0.0391
-8.750 -0.1545 0.07399 0.07031 -0.1271 0.9135 0.0391
-8.500 -0.1638 0.07181 0.06806 -0.1268 0.9088 0.0392
-8.250 -0.1532 0.06526 0.06165 -0.1266 0.9073 0.0410
-8.000 -0.1515 0.06296 0.05932 -0.1260 0.9038 0.0420
-7.750 -0.1527 0.06057 0.05690 -0.1257 0.8994 0.0428
-7.500 -0.1539 0.05814 0.05441 -0.1253 0.8943 0.0437
-7.250 -0.1525 0.05552 0.05167 -0.1250 0.8901 0.0452
-7.000 -0.1510 0.05301 0.04904 -0.1244 0.8860 0.0471
-6.750 -0.1485 0.05101 0.04676 -0.1234 0.8811 0.0505
-6.500 -0.1466 0.05061 0.04577 -0.1211 0.8767 0.0523
-6.250 -0.1370 0.04481 0.04011 -0.1214 0.8744 0.0544
-6.000 -0.1279 0.04308 0.03839 -0.1200 0.8698 0.0563
-5.750 -0.1152 0.04125 0.03640 -0.1188 0.8658 0.0605
-5.500 -0.1022 0.03906 0.03372 -0.1175 0.8625 0.0676
-5.250 -0.0847 0.03694 0.03162 -0.1169 0.8596 0.0710
-5.000 -0.0754 0.03596 0.03025 -0.1146 0.8538 0.0813
-4.750 -0.0552 0.03383 0.02813 -0.1142 0.8506 0.0862
-4.500 -0.0332 0.03209 0.02617 -0.1139 0.8481 0.0995
-4.250 -0.0015 0.02719 0.02012 -0.1096 0.8443 0.0369
-4.000 0.0180 0.02532 0.01800 -0.1080 0.8393 0.0340
-3.750 0.0453 0.02419 0.01661 -0.1075 0.8363 0.0361
-3.500 0.0749 0.02281 0.01502 -0.1073 0.8343 0.0363
-3.250 0.0930 0.02208 0.01422 -0.1055 0.8289 0.0359
-3.000 0.1154 0.02126 0.01332 -0.1044 0.8245 0.0361
-2.750 0.1423 0.02041 0.01241 -0.1039 0.8218 0.0375
-2.500 0.1700 0.01951 0.01145 -0.1037 0.8197 0.0406
-2.250 0.1831 0.01936 0.01130 -0.1015 0.8118 0.0497
-2.000 0.1876 0.01641 0.01106 -0.0976 0.8083 0.6829
-1.750 0.1980 0.01716 0.01192 -0.0912 0.8060 0.8376
-1.500 0.1925 0.01790 0.01272 -0.0836 0.7969 0.8708
-1.250 0.2004 0.01805 0.01279 -0.0774 0.7939 0.9022
-1.000 0.3002 0.01835 0.01288 -0.0879 0.7955 0.9541
-0.750 0.3591 0.01812 0.01246 -0.0941 0.7942 0.9611
-0.500 0.4062 0.01789 0.01208 -0.0981 0.7927 0.9661
-0.250 0.4294 0.01815 0.01231 -0.0981 0.7855 0.9723
0.000 0.4696 0.01800 0.01207 -0.1011 0.7824 0.9756
0.250 0.5062 0.01782 0.01181 -0.1031 0.7801 0.9789
0.500 0.5393 0.01766 0.01158 -0.1044 0.7782 0.9819
0.750 0.5622 0.01804 0.01198 -0.1047 0.7701 0.9859
1.000 0.5974 0.01787 0.01176 -0.1065 0.7673 0.9883
1.250 0.6318 0.01766 0.01151 -0.1080 0.7652 0.9905
1.500 0.6524 0.01807 0.01196 -0.1077 0.7578 0.9940
1.750 0.6843 0.01800 0.01189 -0.1090 0.7545 0.9960
2.000 0.7176 0.01784 0.01172 -0.1104 0.7523 0.9978
2.250 0.7499 0.01775 0.01163 -0.1116 0.7500 0.9996
2.500 0.7563 0.01837 0.01231 -0.1086 0.7414 1.0000
2.750 0.7806 0.01824 0.01222 -0.1081 0.7389 1.0000
3.000 0.8065 0.01810 0.01209 -0.1078 0.7370 1.0000
3.250 0.8026 0.01899 0.01306 -0.1030 0.7278 1.0000
3.500 0.8266 0.01887 0.01297 -0.1025 0.7253 1.0000
3.750 0.8531 0.01870 0.01283 -0.1023 0.7236 1.0000
4.000 0.8405 0.01973 0.01394 -0.0960 0.7140 1.0000
4.250 0.8657 0.01953 0.01382 -0.0955 0.7118 1.0000
4.500 0.8836 0.01946 0.01381 -0.0938 0.7078 1.0000
4.750 0.8838 0.01972 0.01412 -0.0891 0.7001 1.0000
5.000 0.9165 0.01917 0.01364 -0.0897 0.6980 1.0000
5.250 0.9120 0.01961 0.01415 -0.0844 0.6897 1.0000
5.500 0.9542 0.01846 0.01310 -0.0861 0.6861 1.0000
5.750 0.9944 0.01724 0.01195 -0.0874 0.6805 1.0000
6.000 1.0245 0.01633 0.01112 -0.0872 0.6718 1.0000
6.250 1.0504 0.01560 0.01047 -0.0863 0.6606 1.0000
6.500 1.0791 0.01486 0.00983 -0.0859 0.6471 1.0000
6.750 1.1093 0.01419 0.00916 -0.0858 0.6294 1.0000
7.000 1.1298 0.01412 0.00916 -0.0844 0.6095 1.0000
7.250 1.1542 0.01406 0.00910 -0.0837 0.5873 1.0000
7.500 1.1712 0.01426 0.00930 -0.0819 0.5588 1.0000
7.750 1.1804 0.01467 0.00969 -0.0788 0.5183 1.0000
8.000 1.1764 0.01541 0.01021 -0.0736 0.4501 1.0000
8.250 1.1556 0.01716 0.01138 -0.0666 0.3625 1.0000
8.500 1.1360 0.01949 0.01322 -0.0610 0.2883 1.0000
8.750 1.1184 0.02210 0.01535 -0.0563 0.2136 1.0000
9.000 1.1027 0.02488 0.01760 -0.0522 0.1389 1.0000
9.250 1.0921 0.02754 0.01985 -0.0488 0.0895 1.0000
9.500 1.0890 0.02980 0.02192 -0.0461 0.0676 1.0000
9.750 1.0888 0.03192 0.02400 -0.0439 0.0551 1.0000
10.000 1.0943 0.03367 0.02578 -0.0422 0.0456 1.0000
10.250 1.0987 0.03556 0.02772 -0.0405 0.0377 1.0000
10.500 1.0980 0.03799 0.03013 -0.0383 0.0327 1.0000
10.750 1.1079 0.03966 0.03193 -0.0369 0.0283 1.0000
11.000 1.1165 0.04142 0.03368 -0.0357 0.0246 1.0000
11.250 1.1304 0.04334 0.03571 -0.0342 0.0218 1.0000
11.500 1.1509 0.04486 0.03737 -0.0332 0.0200 1.0000
11.750 1.1749 0.04653 0.03921 -0.0325 0.0187 1.0000
12.000 1.1995 0.04857 0.04145 -0.0319 0.0180 1.0000
12.250 1.2224 0.05122 0.04439 -0.0313 0.0177 1.0000
12.500 1.2390 0.05474 0.04829 -0.0302 0.0178 1.0000
12.750 1.2424 0.05914 0.05316 -0.0286 0.0184 1.0000
13.000 1.2360 0.06392 0.05835 -0.0267 0.0190 1.0000
13.250 1.2249 0.06880 0.06358 -0.0251 0.0197 1.0000
13.500 1.2097 0.07383 0.06891 -0.0239 0.0203 1.0000
13.750 1.1923 0.07899 0.07434 -0.0231 0.0208 1.0000
14.000 1.1739 0.08428 0.07987 -0.0230 0.0212 1.0000
14.250 1.1541 0.08993 0.08573 -0.0234 0.0215 1.0000
14.500 1.1333 0.09610 0.09210 -0.0245 0.0219 1.0000
14.750 0.9592 0.09592 0.09256 -0.0205 0.0207 1.0000
15.000 0.9355 0.10183 0.09865 -0.0234 0.0210 1.0000
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