FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 74-130 WP1 (fx74130wp1-il) Reynolds number: 100,000 Max Cl/Cd: 39.76 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74130wp1-il-100000-n5.txt Download as CSV file: xf-fx74130wp1-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-130 WP1
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1819 0.11202 0.10669 -0.1020 0.9352 0.0469
-11.000 -0.1786 0.10863 0.10330 -0.1071 0.9321 0.0479
-10.750 -0.1743 0.10506 0.09972 -0.1113 0.9293 0.0482
-10.250 -0.0722 0.08656 0.08142 -0.1113 0.9096 0.0580
-9.750 -0.1423 0.09029 0.08494 -0.1165 0.9181 0.0516
-9.500 -0.1328 0.08741 0.08204 -0.1180 0.9158 0.0561
-9.250 -0.1338 0.08430 0.07897 -0.1196 0.9117 0.0575
-9.000 -0.1367 0.08071 0.07541 -0.1231 0.9073 0.0595
-8.750 -0.1333 0.07694 0.07164 -0.1255 0.9041 0.0586
-8.250 -0.1624 0.06632 0.06092 -0.1310 0.8930 0.0349
-8.000 -0.1665 0.06342 0.05798 -0.1308 0.8896 0.0338
-7.750 -0.1735 0.06075 0.05524 -0.1298 0.8857 0.0326
-7.500 -0.1842 0.05823 0.05264 -0.1275 0.8804 0.0313
-7.000 -0.1915 0.05059 0.04418 -0.1241 0.8728 0.0262
-6.750 -0.1973 0.04891 0.04241 -0.1203 0.8676 0.0259
-6.500 -0.1928 0.04638 0.03966 -0.1184 0.8639 0.0256
-6.250 -0.1820 0.04362 0.03661 -0.1173 0.8613 0.0252
-6.000 -0.1668 0.04091 0.03353 -0.1166 0.8595 0.0249
-5.750 -0.1731 0.04004 0.03249 -0.1114 0.8534 0.0248
-5.500 -0.1597 0.03786 0.02994 -0.1097 0.8501 0.0246
-5.250 -0.1390 0.03565 0.02731 -0.1090 0.8480 0.0246
-5.000 -0.1148 0.03359 0.02483 -0.1087 0.8464 0.0247
-4.750 -0.1001 0.03234 0.02323 -0.1065 0.8433 0.0250
-4.500 -0.0931 0.03166 0.02232 -0.1031 0.8385 0.0255
-4.250 -0.0709 0.03044 0.02084 -0.1022 0.8359 0.0271
-4.000 -0.0457 0.02937 0.01970 -0.1022 0.8340 0.0297
-3.750 -0.0180 0.02833 0.01852 -0.1022 0.8326 0.0313
-3.500 0.0098 0.02737 0.01744 -0.1021 0.8315 0.0331
-3.250 0.0075 0.02752 0.01754 -0.0972 0.8252 0.0341
-3.000 0.0266 0.02705 0.01698 -0.0958 0.8221 0.0370
-2.750 0.0511 0.02645 0.01638 -0.0956 0.8201 0.0437
-2.500 0.0782 0.02589 0.01571 -0.0956 0.8186 0.0507
-2.250 0.1060 0.02536 0.01521 -0.0958 0.8174 0.0749
-2.000 0.1013 0.02556 0.01567 -0.0907 0.8104 0.1161
-1.750 0.1029 0.02367 0.01616 -0.0862 0.8073 0.6273
-1.500 0.1082 0.02444 0.01712 -0.0797 0.8047 0.8102
-1.250 0.1100 0.02489 0.01756 -0.0720 0.8028 0.8679
-1.000 0.0879 0.02558 0.01831 -0.0623 0.7943 0.8966
-0.750 0.1340 0.02600 0.01856 -0.0631 0.7940 0.9589
-0.500 0.1727 0.02616 0.01849 -0.0658 0.7924 0.9631
-0.250 0.2073 0.02626 0.01840 -0.0677 0.7908 0.9661
0.000 0.2412 0.02633 0.01831 -0.0693 0.7894 0.9687
0.500 0.2774 0.02717 0.01899 -0.0682 0.7797 0.9774
0.750 0.3083 0.02732 0.01904 -0.0694 0.7775 0.9797
1.000 0.3406 0.02741 0.01904 -0.0708 0.7757 0.9819
1.250 0.3717 0.02752 0.01908 -0.0719 0.7739 0.9842
1.500 0.3805 0.02826 0.01982 -0.0703 0.7658 0.9902
1.750 0.4105 0.02840 0.01991 -0.0713 0.7633 0.9931
2.000 0.4422 0.02847 0.01995 -0.0724 0.7614 0.9956
2.500 0.4542 0.02915 0.02062 -0.0663 0.7494 1.0000
2.750 0.4811 0.02915 0.02061 -0.0664 0.7473 1.0000
3.000 0.4786 0.02978 0.02124 -0.0624 0.7384 1.0000
3.250 0.5060 0.02986 0.02134 -0.0627 0.7354 1.0000
3.500 0.5378 0.02987 0.02136 -0.0636 0.7334 1.0000
3.750 0.5439 0.03057 0.02209 -0.0612 0.7242 1.0000
4.000 0.5746 0.03061 0.02217 -0.0620 0.7213 1.0000
4.250 0.6053 0.03063 0.02227 -0.0629 0.7184 1.0000
4.500 0.6176 0.03125 0.02294 -0.0614 0.7094 1.0000
4.750 0.6514 0.03112 0.02288 -0.0625 0.7068 1.0000
5.000 0.6649 0.03173 0.02355 -0.0613 0.6975 1.0000
5.250 0.6981 0.03154 0.02349 -0.0622 0.6940 1.0000
5.750 0.7482 0.03171 0.02388 -0.0621 0.6808 1.0000
6.250 0.8016 0.03152 0.02398 -0.0622 0.6667 1.0000
6.500 0.8215 0.03168 0.02426 -0.0614 0.6562 1.0000
6.750 0.8601 0.03061 0.02337 -0.0622 0.6514 1.0000
7.000 0.8802 0.03052 0.02343 -0.0611 0.6388 1.0000
7.250 0.9029 0.03013 0.02322 -0.0601 0.6251 1.0000
7.500 0.9275 0.02955 0.02280 -0.0592 0.6092 1.0000
7.750 0.9412 0.02978 0.02316 -0.0574 0.5837 1.0000
8.000 0.9662 0.02904 0.02250 -0.0562 0.5492 1.0000
8.250 1.0222 0.02571 0.01865 -0.0564 0.4444 1.0000
8.500 1.0290 0.02674 0.01899 -0.0534 0.3442 1.0000
8.750 1.0288 0.02853 0.02029 -0.0505 0.2674 1.0000
9.000 1.0299 0.03043 0.02174 -0.0481 0.1974 1.0000
9.250 1.0337 0.03229 0.02320 -0.0461 0.1376 1.0000
9.500 1.0402 0.03404 0.02468 -0.0445 0.0984 1.0000
9.750 1.0480 0.03573 0.02626 -0.0430 0.0753 1.0000
10.000 1.0563 0.03741 0.02789 -0.0415 0.0624 1.0000
10.250 1.0659 0.03902 0.02959 -0.0402 0.0550 1.0000
10.500 1.0721 0.04092 0.03148 -0.0387 0.0498 1.0000
10.750 1.0830 0.04247 0.03321 -0.0376 0.0451 1.0000
11.000 1.0924 0.04418 0.03500 -0.0365 0.0411 1.0000
11.250 1.0995 0.04624 0.03706 -0.0352 0.0386 1.0000
11.500 1.1134 0.04780 0.03884 -0.0342 0.0359 1.0000
11.750 1.1264 0.04946 0.04066 -0.0334 0.0328 1.0000
12.000 1.1383 0.05126 0.04252 -0.0326 0.0305 1.0000
12.250 1.1569 0.05325 0.04457 -0.0319 0.0286 1.0000
12.500 1.1738 0.05512 0.04674 -0.0313 0.0266 1.0000
12.750 1.1856 0.05720 0.04905 -0.0306 0.0244 1.0000
13.000 1.1959 0.05945 0.05148 -0.0299 0.0230 1.0000
13.250 1.2067 0.06201 0.05419 -0.0293 0.0220 1.0000
13.500 1.2177 0.06541 0.05773 -0.0288 0.0209 1.0000
13.750 1.2164 0.06870 0.06148 -0.0277 0.0202 1.0000
14.000 1.2122 0.07236 0.06552 -0.0268 0.0194 1.0000
14.250 1.2053 0.07636 0.06987 -0.0262 0.0187 1.0000
14.500 1.1962 0.08063 0.07445 -0.0259 0.0181 1.0000
14.750 1.1849 0.08531 0.07942 -0.0261 0.0177 1.0000
15.000 1.1712 0.09051 0.08491 -0.0267 0.0175 1.0000
15.250 1.1554 0.09625 0.09093 -0.0279 0.0174 1.0000
15.500 1.1373 0.10262 0.09758 -0.0299 0.0173 1.0000
15.750 1.1175 0.10976 0.10497 -0.0329 0.0174 1.0000
16.000 1.0959 0.11781 0.11326 -0.0370 0.0175 1.0000
16.250 1.0725 0.12708 0.12275 -0.0425 0.0177 1.0000
16.500 1.0470 0.13803 0.13385 -0.0495 0.0181 1.0000
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