FX 76-MP-160 (fx76mp160-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 76-MP-160 (fx76mp160-il) Reynolds number: 200,000 Max Cl/Cd: 76.28 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76mp160-il-200000.txt Download as CSV file: xf-fx76mp160-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 76-MP-160
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 0.1034 0.10547 0.10108 -0.1490 0.9232 0.0736
-11.750 0.1119 0.10284 0.09844 -0.1510 0.9197 0.0757
-11.500 0.0894 0.09890 0.09452 -0.1579 0.9152 0.0783
-11.250 0.1167 0.09601 0.09160 -0.1578 0.9133 0.0789
-11.000 0.1379 0.09348 0.08903 -0.1593 0.9112 0.0798
-10.750 0.1533 0.09115 0.08667 -0.1608 0.9088 0.0812
-10.500 0.1578 0.08913 0.08467 -0.1609 0.9054 0.0830
-10.000 0.1449 0.08259 0.07818 -0.1656 0.8975 0.0874
-9.750 -0.0927 0.04744 0.04282 -0.1810 0.8815 0.0559
-9.500 -0.1094 0.04534 0.04063 -0.1797 0.8772 0.0556
-9.250 -0.1345 0.04358 0.03875 -0.1764 0.8723 0.0554
-9.000 -0.1581 0.04239 0.03746 -0.1716 0.8660 0.0552
-8.750 -0.1686 0.03929 0.03399 -0.1703 0.8613 0.0551
-8.500 -0.1643 0.03612 0.03034 -0.1703 0.8584 0.0552
-8.250 -0.1941 0.03667 0.03084 -0.1617 0.8497 0.0552
-8.000 -0.1926 0.03505 0.02887 -0.1593 0.8455 0.0555
-7.750 -0.1720 0.03300 0.02646 -0.1598 0.8432 0.0565
-7.500 -0.1406 0.03206 0.02551 -0.1612 0.8419 0.0580
-7.250 -0.1084 0.03091 0.02418 -0.1627 0.8406 0.0603
-7.000 -0.1686 0.03290 0.02628 -0.1483 0.8281 0.0591
-6.750 -0.1419 0.03176 0.02482 -0.1489 0.8260 0.0615
-6.500 -0.1079 0.03038 0.02324 -0.1507 0.8246 0.0643
-6.250 -0.0686 0.02936 0.02208 -0.1530 0.8236 0.0684
-6.000 -0.0929 0.03015 0.02280 -0.1446 0.8132 0.0690
-5.750 -0.0679 0.02939 0.02202 -0.1445 0.8096 0.0727
-5.500 -0.0366 0.02889 0.02139 -0.1454 0.8076 0.0771
-5.250 -0.0017 0.02827 0.02078 -0.1468 0.8062 0.0810
-5.000 0.0366 0.02784 0.02023 -0.1487 0.8052 0.0856
-4.750 0.0761 0.02733 0.01975 -0.1508 0.8043 0.0899
-4.500 0.0855 0.02775 0.02013 -0.1480 0.7997 0.0931
-4.250 0.1426 0.02678 0.01912 -0.1530 0.8012 0.0997
-3.750 0.1460 0.02751 0.01976 -0.1446 0.7865 0.1064
-3.500 0.1910 0.02675 0.01907 -0.1474 0.7857 0.1163
-3.250 0.2050 0.02697 0.01938 -0.1454 0.7806 0.1226
-3.000 0.2623 0.02614 0.01851 -0.1501 0.7820 0.1386
-2.750 0.3171 0.02508 0.01753 -0.1545 0.7834 0.1570
-2.500 0.2717 0.02680 0.01923 -0.1430 0.7676 0.1546
-2.250 0.3151 0.02616 0.01871 -0.1454 0.7669 0.1732
-2.000 0.2918 0.02773 0.02028 -0.1379 0.7535 0.1761
-1.750 0.3272 0.02728 0.01985 -0.1389 0.7511 0.1958
-1.500 0.3668 0.02664 0.01931 -0.1407 0.7496 0.2175
-1.250 0.4079 0.02604 0.01878 -0.1426 0.7486 0.2443
-1.000 0.4496 0.02540 0.01829 -0.1448 0.7478 0.2771
-0.750 0.4279 0.02707 0.02000 -0.1376 0.7344 0.2852
-0.500 0.4647 0.02642 0.01952 -0.1388 0.7321 0.3318
-0.250 0.5075 0.02535 0.01878 -0.1409 0.7310 0.4194
0.000 0.5472 0.02422 0.01826 -0.1423 0.7302 0.5806
0.250 0.5832 0.02350 0.01790 -0.1422 0.7292 0.7159
0.500 0.6211 0.02309 0.01748 -0.1429 0.7282 0.7671
0.750 0.6608 0.02265 0.01701 -0.1440 0.7273 0.8027
1.000 0.6972 0.02211 0.01647 -0.1443 0.7264 0.8270
1.250 0.6630 0.02342 0.01786 -0.1340 0.7113 0.8403
1.500 0.6986 0.02267 0.01708 -0.1342 0.7102 0.8630
1.750 0.7358 0.02182 0.01621 -0.1346 0.7092 0.8837
2.000 0.7770 0.02089 0.01525 -0.1358 0.7083 0.9016
2.250 0.8194 0.02000 0.01431 -0.1374 0.7074 0.9191
2.500 0.7933 0.02092 0.01534 -0.1285 0.6930 0.9433
2.750 0.8530 0.01996 0.01435 -0.1337 0.6921 1.0000
3.000 0.9029 0.01924 0.01356 -0.1373 0.6907 1.0000
3.250 0.9546 0.01852 0.01277 -0.1413 0.6893 1.0000
3.500 0.9447 0.01929 0.01358 -0.1353 0.6769 1.0000
3.750 0.9918 0.01850 0.01272 -0.1383 0.6740 1.0000
4.000 1.0443 0.01767 0.01183 -0.1423 0.6713 1.0000
4.250 1.0522 0.01798 0.01214 -0.1391 0.6619 1.0000
4.500 1.0879 0.01756 0.01168 -0.1403 0.6560 1.0000
4.750 1.1385 0.01685 0.01090 -0.1440 0.6518 1.0000
5.000 1.1430 0.01726 0.01134 -0.1402 0.6410 1.0000
5.250 1.1836 0.01683 0.01083 -0.1422 0.6345 1.0000
5.500 1.2004 0.01700 0.01100 -0.1404 0.6242 1.0000
5.750 1.2326 0.01679 0.01072 -0.1411 0.6148 1.0000
6.000 1.2446 0.01711 0.01103 -0.1385 0.6026 1.0000
6.250 1.2795 0.01689 0.01070 -0.1396 0.5921 1.0000
6.500 1.2927 0.01723 0.01102 -0.1373 0.5790 1.0000
6.750 1.3119 0.01752 0.01125 -0.1360 0.5666 1.0000
7.000 1.3418 0.01759 0.01118 -0.1363 0.5547 1.0000
7.250 1.3478 0.01822 0.01182 -0.1331 0.5404 1.0000
7.500 1.3636 0.01869 0.01223 -0.1314 0.5271 1.0000
7.750 1.3864 0.01901 0.01240 -0.1307 0.5143 1.0000
8.000 1.3950 0.01972 0.01310 -0.1280 0.5005 1.0000
8.250 1.4068 0.02040 0.01373 -0.1259 0.4872 1.0000
8.500 1.4236 0.02097 0.01419 -0.1245 0.4745 1.0000
8.750 1.4293 0.02186 0.01510 -0.1217 0.4614 1.0000
9.000 1.4432 0.02257 0.01575 -0.1200 0.4501 1.0000
9.250 1.4559 0.02333 0.01645 -0.1182 0.4387 1.0000
9.500 1.4663 0.02422 0.01734 -0.1163 0.4275 1.0000
9.750 1.4795 0.02501 0.01805 -0.1146 0.4161 1.0000
10.000 1.4859 0.02607 0.01916 -0.1123 0.4047 1.0000
10.250 1.4998 0.02688 0.01985 -0.1109 0.3944 1.0000
10.500 1.5060 0.02801 0.02103 -0.1087 0.3836 1.0000
10.750 1.5216 0.02881 0.02173 -0.1075 0.3740 1.0000
11.000 1.5276 0.03002 0.02304 -0.1054 0.3643 1.0000
11.250 1.5438 0.03082 0.02371 -0.1043 0.3552 1.0000
11.500 1.5476 0.03218 0.02521 -0.1022 0.3460 1.0000
11.750 1.5594 0.03318 0.02615 -0.1008 0.3374 1.0000
12.000 1.5667 0.03446 0.02750 -0.0991 0.3288 1.0000
12.250 1.5764 0.03562 0.02863 -0.0976 0.3204 1.0000
12.500 1.5872 0.03678 0.02978 -0.0963 0.3124 1.0000
12.750 1.5930 0.03824 0.03132 -0.0946 0.3040 1.0000
13.000 1.6075 0.03921 0.03220 -0.0936 0.2963 1.0000
13.250 1.6109 0.04090 0.03405 -0.0919 0.2889 1.0000
13.500 1.6186 0.04233 0.03550 -0.0906 0.2817 1.0000
13.750 1.6282 0.04368 0.03685 -0.0894 0.2749 1.0000
14.000 1.6337 0.04536 0.03864 -0.0881 0.2678 1.0000
14.250 1.6437 0.04670 0.03990 -0.0870 0.2608 1.0000
14.500 1.6487 0.04851 0.04183 -0.0858 0.2539 1.0000
14.750 1.6526 0.05042 0.04382 -0.0846 0.2467 1.0000
15.000 1.6625 0.05184 0.04514 -0.0836 0.2393 1.0000
15.250 1.6612 0.05432 0.04782 -0.0824 0.2325 1.0000
15.500 1.6634 0.05651 0.05004 -0.0813 0.2253 1.0000
15.750 1.6658 0.05875 0.05232 -0.0804 0.2182 1.0000
16.000 1.6656 0.06132 0.05498 -0.0795 0.2112 1.0000
16.250 1.6724 0.06312 0.05665 -0.0787 0.2042 1.0000
16.500 1.6694 0.06618 0.05992 -0.0780 0.1980 1.0000
16.750 1.6699 0.06884 0.06265 -0.0774 0.1915 1.0000
17.000 1.6747 0.07100 0.06477 -0.0768 0.1853 1.0000
17.250 1.6711 0.07431 0.06828 -0.0765 0.1792 1.0000
17.500 1.6697 0.07736 0.07137 -0.0762 0.1732 1.0000
17.750 1.6694 0.08027 0.07430 -0.0760 0.1673 1.0000
18.000 1.6649 0.08389 0.07805 -0.0760 0.1613 1.0000
18.250 1.6635 0.08700 0.08112 -0.0760 0.1554 1.0000
18.500 1.6603 0.09051 0.08474 -0.0762 0.1498 1.0000
18.750 1.6552 0.09437 0.08874 -0.0767 0.1442 1.0000
19.000 1.6535 0.09759 0.09190 -0.0770 0.1386 1.0000
19.250 1.6481 0.10161 0.09608 -0.0777 0.1337 1.0000
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Polar data table (+)
Polar graphs
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