FX 76-MP-160 (fx76mp160-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 76-MP-160 (fx76mp160-il) Reynolds number: 500,000 Max Cl/Cd: 109.31 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76mp160-il-500000-n5.txt Download as CSV file: xf-fx76mp160-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.3622 0.07606 0.07180 -0.1407 0.8188 0.0219
-15.000 -0.3919 0.06738 0.06297 -0.1473 0.8167 0.0218
-14.500 -0.4348 0.05328 0.04863 -0.1592 0.8124 0.0219
-14.000 -0.4598 0.04118 0.03623 -0.1706 0.8079 0.0217
-13.500 -0.4715 0.03134 0.02604 -0.1811 0.8030 0.0219
-13.250 -0.4726 0.02854 0.02313 -0.1831 0.8006 0.0220
-13.000 -0.4712 0.02658 0.02108 -0.1836 0.7980 0.0220
-12.750 -0.4716 0.02486 0.01928 -0.1831 0.7951 0.0221
-12.500 -0.4710 0.02359 0.01793 -0.1816 0.7927 0.0221
-12.250 -0.4696 0.02254 0.01679 -0.1799 0.7904 0.0223
-12.000 -0.4582 0.02166 0.01583 -0.1789 0.7885 0.0224
-11.750 -0.4439 0.02087 0.01495 -0.1781 0.7867 0.0227
-11.500 -0.4269 0.02017 0.01416 -0.1774 0.7851 0.0228
-11.250 -0.4080 0.01953 0.01344 -0.1769 0.7834 0.0231
-11.000 -0.3885 0.01893 0.01278 -0.1764 0.7821 0.0232
-10.750 -0.3680 0.01836 0.01215 -0.1759 0.7807 0.0234
-10.500 -0.3463 0.01783 0.01158 -0.1755 0.7792 0.0237
-10.250 -0.3238 0.01733 0.01103 -0.1751 0.7776 0.0240
-10.000 -0.3007 0.01687 0.01050 -0.1748 0.7760 0.0243
-9.750 -0.2768 0.01643 0.01001 -0.1746 0.7743 0.0246
-9.500 -0.2525 0.01602 0.00954 -0.1744 0.7725 0.0250
-9.250 -0.2277 0.01562 0.00909 -0.1742 0.7709 0.0254
-9.000 -0.2021 0.01527 0.00870 -0.1742 0.7694 0.0259
-8.750 -0.1760 0.01497 0.00836 -0.1742 0.7680 0.0266
-8.500 -0.1495 0.01468 0.00804 -0.1742 0.7666 0.0275
-8.250 -0.1226 0.01442 0.00774 -0.1743 0.7652 0.0287
-8.000 -0.0958 0.01417 0.00744 -0.1743 0.7638 0.0299
-7.750 -0.0694 0.01393 0.00719 -0.1742 0.7626 0.0316
-7.500 -0.0428 0.01371 0.00693 -0.1741 0.7609 0.0334
-7.250 -0.0161 0.01347 0.00667 -0.1741 0.7591 0.0348
-7.000 0.0107 0.01323 0.00640 -0.1740 0.7572 0.0362
-6.750 0.0378 0.01302 0.00615 -0.1740 0.7552 0.0379
-6.500 0.0652 0.01284 0.00592 -0.1740 0.7532 0.0392
-6.250 0.0923 0.01255 0.00561 -0.1741 0.7511 0.0408
-6.000 0.1200 0.01233 0.00536 -0.1742 0.7491 0.0423
-5.750 0.1481 0.01215 0.00513 -0.1743 0.7473 0.0437
-5.500 0.1765 0.01200 0.00494 -0.1745 0.7456 0.0448
-5.250 0.2043 0.01183 0.00478 -0.1746 0.7440 0.0463
-5.000 0.2312 0.01166 0.00464 -0.1746 0.7421 0.0484
-4.750 0.2585 0.01151 0.00451 -0.1745 0.7398 0.0501
-4.500 0.2859 0.01137 0.00438 -0.1745 0.7372 0.0528
-4.250 0.3136 0.01124 0.00425 -0.1745 0.7346 0.0560
-4.000 0.3415 0.01112 0.00413 -0.1745 0.7322 0.0605
-3.750 0.3697 0.01100 0.00399 -0.1746 0.7299 0.0639
-3.500 0.3981 0.01088 0.00384 -0.1748 0.7278 0.0674
-3.250 0.4269 0.01080 0.00373 -0.1750 0.7257 0.0703
-3.000 0.4539 0.01067 0.00365 -0.1749 0.7234 0.0749
-2.750 0.4810 0.01051 0.00360 -0.1749 0.7207 0.0862
-2.500 0.5083 0.01041 0.00352 -0.1748 0.7174 0.0996
-2.250 0.5359 0.01032 0.00343 -0.1747 0.7139 0.1067
-2.000 0.5638 0.01020 0.00334 -0.1748 0.7109 0.1142
-1.750 0.5920 0.01010 0.00326 -0.1749 0.7079 0.1256
-1.500 0.6191 0.01005 0.00323 -0.1748 0.7044 0.1380
-1.250 0.6459 0.01000 0.00320 -0.1746 0.7001 0.1441
-1.000 0.6730 0.00994 0.00316 -0.1744 0.6961 0.1526
-0.750 0.7004 0.00986 0.00312 -0.1744 0.6923 0.1628
-0.500 0.7278 0.00980 0.00306 -0.1743 0.6881 0.1772
-0.250 0.7538 0.00977 0.00308 -0.1740 0.6825 0.1909
0.000 0.7799 0.00973 0.00306 -0.1736 0.6764 0.1995
0.250 0.8062 0.00969 0.00303 -0.1733 0.6707 0.2127
0.500 0.8324 0.00963 0.00306 -0.1731 0.6656 0.2409
0.750 0.8584 0.00961 0.00309 -0.1728 0.6599 0.2598
1.000 0.8836 0.00955 0.00310 -0.1723 0.6531 0.2938
1.250 0.9085 0.00953 0.00313 -0.1718 0.6457 0.3245
1.500 0.9320 0.00949 0.00317 -0.1710 0.6359 0.3719
1.750 0.9553 0.00944 0.00324 -0.1703 0.6264 0.4282
2.000 0.9778 0.00939 0.00332 -0.1693 0.6159 0.4919
2.250 0.9994 0.00937 0.00343 -0.1682 0.6047 0.5593
2.500 1.0183 0.00938 0.00361 -0.1664 0.5926 0.6407
2.750 1.0373 0.00949 0.00380 -0.1647 0.5812 0.6927
3.000 1.0538 0.00967 0.00400 -0.1624 0.5696 0.7186
3.250 1.0678 0.00989 0.00417 -0.1596 0.5566 0.7378
3.500 1.0830 0.01010 0.00436 -0.1571 0.5437 0.7505
3.750 1.0954 0.01041 0.00461 -0.1541 0.5295 0.7599
4.250 1.1170 0.01112 0.00523 -0.1477 0.5035 0.7767
4.500 1.1282 0.01151 0.00557 -0.1447 0.4920 0.7846
4.750 1.1405 0.01189 0.00592 -0.1420 0.4785 0.7912
5.000 1.1525 0.01231 0.00631 -0.1393 0.4668 0.7988
5.250 1.1607 0.01285 0.00679 -0.1361 0.4541 0.8057
5.500 1.1728 0.01330 0.00724 -0.1335 0.4439 0.8126
5.750 1.1818 0.01389 0.00780 -0.1306 0.4334 0.8204
6.000 1.1943 0.01440 0.00832 -0.1283 0.4211 0.8266
6.250 1.2053 0.01502 0.00890 -0.1259 0.4095 0.8323
6.500 1.2157 0.01570 0.00954 -0.1235 0.3974 0.8382
6.750 1.2263 0.01641 0.01022 -0.1212 0.3859 0.8455
7.000 1.2377 0.01715 0.01092 -0.1191 0.3770 0.8512
7.500 1.2680 0.01840 0.01221 -0.1162 0.3582 0.8696
7.750 1.2842 0.01903 0.01286 -0.1149 0.3497 0.8851
8.000 1.3050 0.01978 0.01365 -0.1149 0.3380 0.9078
8.500 1.3410 0.02164 0.01544 -0.1144 0.3156 1.0000
8.750 1.3571 0.02238 0.01617 -0.1134 0.3068 1.0000
9.000 1.3689 0.02338 0.01712 -0.1119 0.2975 1.0000
9.250 1.3850 0.02413 0.01788 -0.1109 0.2880 1.0000
9.500 1.3977 0.02512 0.01882 -0.1095 0.2786 1.0000
9.750 1.4099 0.02614 0.01981 -0.1082 0.2689 1.0000
10.000 1.4218 0.02720 0.02083 -0.1068 0.2611 1.0000
10.250 1.4368 0.02808 0.02172 -0.1058 0.2558 1.0000
10.500 1.4516 0.02899 0.02265 -0.1049 0.2499 1.0000
10.750 1.4641 0.03006 0.02371 -0.1037 0.2434 1.0000
11.000 1.4780 0.03104 0.02470 -0.1027 0.2380 1.0000
11.250 1.4934 0.03193 0.02562 -0.1018 0.2319 1.0000
11.500 1.5047 0.03315 0.02683 -0.1006 0.2240 1.0000
11.750 1.5173 0.03427 0.02795 -0.0996 0.2187 1.0000
12.000 1.5298 0.03541 0.02910 -0.0986 0.2129 1.0000
12.250 1.5399 0.03677 0.03046 -0.0974 0.2075 1.0000
12.500 1.5512 0.03804 0.03174 -0.0964 0.2026 1.0000
12.750 1.5643 0.03918 0.03292 -0.0956 0.1969 1.0000
13.000 1.5745 0.04056 0.03431 -0.0945 0.1914 1.0000
13.250 1.5827 0.04216 0.03591 -0.0934 0.1858 1.0000
13.500 1.5945 0.04344 0.03723 -0.0925 0.1773 1.0000
13.750 1.6002 0.04528 0.03903 -0.0913 0.1679 1.0000
14.000 1.6057 0.04716 0.04089 -0.0902 0.1597 1.0000
14.250 1.6117 0.04902 0.04274 -0.0891 0.1542 1.0000
14.500 1.6206 0.05065 0.04443 -0.0883 0.1494 1.0000
14.750 1.6284 0.05240 0.04622 -0.0875 0.1442 1.0000
15.000 1.6326 0.05452 0.04834 -0.0865 0.1385 1.0000
15.250 1.6395 0.05642 0.05028 -0.0857 0.1332 1.0000
15.500 1.6427 0.05867 0.05253 -0.0849 0.1243 1.0000
15.750 1.6429 0.06131 0.05517 -0.0840 0.1171 1.0000
16.000 1.6440 0.06388 0.05774 -0.0832 0.1114 1.0000
16.250 1.6465 0.06638 0.06028 -0.0826 0.1079 1.0000
16.500 1.6515 0.06859 0.06255 -0.0821 0.1039 1.0000
16.750 1.6532 0.07122 0.06523 -0.0816 0.0996 1.0000
17.000 1.6517 0.07427 0.06830 -0.0811 0.0948 1.0000
17.250 1.6543 0.07688 0.07099 -0.0808 0.0907 1.0000
17.500 1.6532 0.07998 0.07410 -0.0805 0.0847 1.0000
17.750 1.6502 0.08336 0.07752 -0.0804 0.0804 1.0000
18.000 1.6474 0.08676 0.08095 -0.0804 0.0765 1.0000
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Polar graphs
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