FX 76-MP-160 (fx76mp160-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 76-MP-160 (fx76mp160-il) Reynolds number: 500,000 Max Cl/Cd: 120.92 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76mp160-il-500000.txt Download as CSV file: xf-fx76mp160-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3257 0.03327 0.02870 -0.1915 0.8366 0.0308
-12.250 -0.3312 0.03101 0.02632 -0.1918 0.8336 0.0310
-12.000 -0.3378 0.02899 0.02417 -0.1909 0.8305 0.0311
-11.750 -0.3434 0.02753 0.02259 -0.1889 0.8276 0.0312
-11.500 -0.3445 0.02636 0.02129 -0.1869 0.8250 0.0313
-11.250 -0.3366 0.02527 0.02005 -0.1856 0.8227 0.0316
-11.000 -0.3258 0.02427 0.01892 -0.1845 0.8204 0.0317
-10.750 -0.3134 0.02334 0.01789 -0.1833 0.8187 0.0320
-10.500 -0.2987 0.02248 0.01693 -0.1822 0.8166 0.0323
-10.250 -0.2820 0.02165 0.01598 -0.1812 0.8143 0.0326
-10.000 -0.2633 0.02092 0.01513 -0.1805 0.8122 0.0331
-9.750 -0.2429 0.02025 0.01435 -0.1799 0.8104 0.0335
-9.500 -0.2212 0.01964 0.01362 -0.1795 0.8086 0.0338
-9.250 -0.1991 0.01897 0.01285 -0.1791 0.8069 0.0342
-9.000 -0.1772 0.01819 0.01203 -0.1788 0.8052 0.0348
-8.750 -0.1535 0.01772 0.01153 -0.1786 0.8035 0.0355
-8.500 -0.1303 0.01734 0.01112 -0.1782 0.8017 0.0362
-8.250 -0.1070 0.01688 0.01062 -0.1778 0.8002 0.0372
-8.000 -0.0834 0.01645 0.01013 -0.1773 0.7982 0.0382
-7.750 -0.0599 0.01592 0.00955 -0.1769 0.7960 0.0395
-7.500 -0.0362 0.01534 0.00900 -0.1766 0.7938 0.0412
-7.250 -0.0106 0.01495 0.00856 -0.1765 0.7919 0.0437
-7.000 0.0151 0.01447 0.00807 -0.1764 0.7899 0.0464
-6.750 0.0429 0.01422 0.00778 -0.1766 0.7880 0.0494
-6.500 0.0712 0.01401 0.00756 -0.1768 0.7861 0.0523
-6.250 0.0998 0.01399 0.00748 -0.1770 0.7840 0.0550
-6.000 0.1261 0.01386 0.00735 -0.1769 0.7822 0.0573
-5.750 0.1524 0.01374 0.00724 -0.1767 0.7805 0.0597
-5.500 0.1789 0.01362 0.00709 -0.1765 0.7785 0.0618
-5.250 0.2055 0.01342 0.00688 -0.1764 0.7762 0.0636
-5.000 0.2326 0.01315 0.00662 -0.1764 0.7736 0.0661
-4.750 0.2609 0.01295 0.00639 -0.1765 0.7714 0.0688
-4.500 0.2895 0.01270 0.00611 -0.1767 0.7693 0.0718
-4.250 0.3186 0.01246 0.00587 -0.1771 0.7675 0.0760
-4.000 0.3480 0.01231 0.00573 -0.1775 0.7654 0.0819
-3.750 0.3749 0.01223 0.00570 -0.1774 0.7631 0.0906
-3.500 0.4009 0.01209 0.00560 -0.1771 0.7606 0.1001
-3.250 0.4275 0.01197 0.00550 -0.1769 0.7580 0.1092
-3.000 0.4550 0.01181 0.00541 -0.1769 0.7554 0.1207
-2.750 0.4835 0.01169 0.00533 -0.1771 0.7530 0.1375
-2.500 0.5128 0.01153 0.00517 -0.1774 0.7505 0.1504
-2.250 0.5429 0.01136 0.00503 -0.1779 0.7482 0.1628
-2.000 0.5731 0.01130 0.00498 -0.1784 0.7457 0.1787
-1.750 0.5992 0.01126 0.00496 -0.1780 0.7428 0.1931
-1.500 0.6249 0.01111 0.00489 -0.1776 0.7394 0.2061
-1.000 0.6806 0.01081 0.00471 -0.1777 0.7330 0.2497
-0.750 0.7100 0.01062 0.00460 -0.1781 0.7303 0.2759
-0.500 0.7402 0.01045 0.00446 -0.1785 0.7273 0.3113
-0.250 0.7668 0.01030 0.00444 -0.1784 0.7237 0.3494
0.000 0.7919 0.01012 0.00441 -0.1779 0.7195 0.3924
0.250 0.8187 0.00987 0.00435 -0.1778 0.7156 0.4608
0.500 0.8459 0.00957 0.00430 -0.1778 0.7122 0.5638
0.750 0.8730 0.00936 0.00435 -0.1775 0.7091 0.6537
1.000 0.8991 0.00935 0.00441 -0.1770 0.7051 0.7021
1.250 0.9223 0.00935 0.00449 -0.1759 0.6999 0.7308
1.500 0.9480 0.00932 0.00446 -0.1754 0.6945 0.7500
1.750 0.9758 0.00929 0.00440 -0.1752 0.6896 0.7639
2.000 0.9997 0.00934 0.00447 -0.1743 0.6842 0.7753
2.250 1.0229 0.00937 0.00452 -0.1732 0.6778 0.7854
2.500 1.0483 0.00938 0.00451 -0.1726 0.6721 0.7958
2.750 1.0723 0.00943 0.00456 -0.1718 0.6659 0.8059
3.000 1.0940 0.00947 0.00462 -0.1705 0.6582 0.8142
3.250 1.1181 0.00950 0.00461 -0.1696 0.6512 0.8216
3.500 1.1383 0.00959 0.00473 -0.1680 0.6426 0.8300
3.750 1.1593 0.00966 0.00476 -0.1666 0.6332 0.8376
4.000 1.1780 0.00978 0.00487 -0.1647 0.6224 0.8456
4.250 1.1959 0.00989 0.00495 -0.1627 0.6112 0.8512
4.500 1.2104 0.01001 0.00506 -0.1600 0.5986 0.8587
4.750 1.2217 0.01015 0.00518 -0.1567 0.5862 0.8654
5.000 1.2327 0.01040 0.00536 -0.1534 0.5736 0.8731
5.250 1.2428 0.01065 0.00560 -0.1500 0.5596 0.8814
5.500 1.2530 0.01093 0.00586 -0.1467 0.5466 0.8905
5.750 1.2602 0.01128 0.00617 -0.1429 0.5323 0.9003
6.000 1.2671 0.01168 0.00653 -0.1392 0.5184 0.9106
6.250 1.2798 0.01209 0.00694 -0.1368 0.5054 0.9264
6.500 1.3034 0.01256 0.00740 -0.1369 0.4917 1.0000
6.750 1.3156 0.01316 0.00795 -0.1348 0.4772 1.0000
7.000 1.3291 0.01376 0.00851 -0.1329 0.4646 1.0000
7.250 1.3396 0.01451 0.00919 -0.1306 0.4523 1.0000
7.500 1.3517 0.01524 0.00987 -0.1286 0.4404 1.0000
7.750 1.3642 0.01599 0.01058 -0.1268 0.4284 1.0000
8.000 1.3747 0.01685 0.01138 -0.1247 0.4157 1.0000
8.250 1.3863 0.01770 0.01219 -0.1229 0.4014 1.0000
8.500 1.3973 0.01861 0.01304 -0.1210 0.3900 1.0000
8.750 1.4072 0.01960 0.01397 -0.1191 0.3786 1.0000
9.000 1.4213 0.02040 0.01476 -0.1177 0.3690 1.0000
9.250 1.4316 0.02141 0.01572 -0.1159 0.3572 1.0000
9.500 1.4467 0.02219 0.01650 -0.1148 0.3477 1.0000
9.750 1.4557 0.02332 0.01757 -0.1129 0.3363 1.0000
10.000 1.4696 0.02419 0.01844 -0.1117 0.3277 1.0000
10.250 1.4798 0.02529 0.01950 -0.1101 0.3193 1.0000
10.500 1.4935 0.02621 0.02043 -0.1089 0.3117 1.0000
10.750 1.5066 0.02717 0.02139 -0.1076 0.3035 1.0000
11.000 1.5172 0.02832 0.02251 -0.1062 0.2958 1.0000
11.250 1.5325 0.02919 0.02342 -0.1053 0.2884 1.0000
11.500 1.5428 0.03040 0.02460 -0.1039 0.2799 1.0000
11.750 1.5558 0.03143 0.02565 -0.1028 0.2733 1.0000
12.000 1.5665 0.03264 0.02686 -0.1015 0.2662 1.0000
12.250 1.5738 0.03413 0.02830 -0.1000 0.2589 1.0000
12.500 1.5891 0.03505 0.02929 -0.0992 0.2535 1.0000
12.750 1.5994 0.03635 0.03059 -0.0980 0.2460 1.0000
13.000 1.6066 0.03791 0.03214 -0.0967 0.2394 1.0000
13.250 1.6210 0.03894 0.03324 -0.0959 0.2329 1.0000
13.500 1.6288 0.04051 0.03478 -0.0947 0.2241 1.0000
13.750 1.6377 0.04203 0.03632 -0.0936 0.2174 1.0000
14.000 1.6454 0.04365 0.03793 -0.0925 0.2105 1.0000
14.250 1.6500 0.04554 0.03981 -0.0912 0.2040 1.0000
14.500 1.6615 0.04689 0.04123 -0.0905 0.1984 1.0000
14.750 1.6687 0.04860 0.04296 -0.0894 0.1921 1.0000
15.000 1.6725 0.05068 0.04504 -0.0883 0.1856 1.0000
15.250 1.6828 0.05219 0.04662 -0.0876 0.1788 1.0000
15.500 1.6851 0.05447 0.04887 -0.0866 0.1702 1.0000
15.750 1.6893 0.05659 0.05102 -0.0857 0.1634 1.0000
16.000 1.6906 0.05902 0.05344 -0.0847 0.1570 1.0000
16.250 1.6934 0.06137 0.05583 -0.0839 0.1517 1.0000
16.500 1.6984 0.06351 0.05802 -0.0833 0.1456 1.0000
16.750 1.6974 0.06632 0.06084 -0.0825 0.1398 1.0000
17.000 1.7008 0.06869 0.06326 -0.0819 0.1340 1.0000
17.250 1.7018 0.07137 0.06598 -0.0814 0.1275 1.0000
17.500 1.6992 0.07451 0.06912 -0.0809 0.1216 1.0000
17.750 1.6981 0.07753 0.07218 -0.0806 0.1164 1.0000
18.000 1.6938 0.08098 0.07564 -0.0803 0.1116 1.0000
18.250 1.6910 0.08431 0.07903 -0.0802 0.1074 1.0000
18.500 1.6929 0.08707 0.08187 -0.0802 0.1036 1.0000
18.750 1.6894 0.09058 0.08544 -0.0803 0.0995 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 76-MP-160 (fx76mp160-il)