MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MA409 (smoothed) (ma409sm-il) Reynolds number: 100,000 Max Cl/Cd: 62.45 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409sm-il-100000-n5.txt Download as CSV file: xf-ma409sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MA409 (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4249 0.11017 0.10490 -0.0222 1.0000 0.0465
-9.000 -0.4249 0.10743 0.10222 -0.0242 1.0000 0.0498
-8.750 -0.4315 0.10525 0.10018 -0.0278 1.0000 0.0512
-8.500 -0.3406 0.08854 0.08374 -0.0299 1.0000 0.0367
-8.250 -0.3410 0.08490 0.08015 -0.0297 1.0000 0.0347
-8.000 -0.4220 0.09293 0.08791 -0.0269 1.0000 0.0364
-7.750 -0.4241 0.08983 0.08487 -0.0265 1.0000 0.0342
-7.500 -0.4300 0.08663 0.08176 -0.0265 1.0000 0.0324
-7.000 -0.4337 0.07638 0.07164 -0.0344 1.0000 0.0276
-6.750 -0.4305 0.07250 0.06779 -0.0361 1.0000 0.0272
-6.500 -0.4249 0.06823 0.06354 -0.0386 1.0000 0.0268
-6.250 -0.4163 0.06345 0.05874 -0.0421 1.0000 0.0265
-6.000 -0.4038 0.05793 0.05315 -0.0465 1.0000 0.0261
-5.750 -0.3860 0.05124 0.04631 -0.0522 1.0000 0.0257
-5.500 -0.3624 0.04311 0.03782 -0.0590 1.0000 0.0253
-5.250 -0.3336 0.03549 0.02952 -0.0650 1.0000 0.0252
-5.000 -0.3032 0.02998 0.02320 -0.0686 1.0000 0.0257
-4.750 -0.2731 0.02638 0.01884 -0.0704 1.0000 0.0269
-4.500 -0.2448 0.02404 0.01604 -0.0715 1.0000 0.0298
-4.250 -0.2178 0.02260 0.01435 -0.0720 1.0000 0.0326
-4.000 -0.1885 0.02092 0.01231 -0.0725 1.0000 0.0352
-3.750 -0.1591 0.01958 0.01058 -0.0728 1.0000 0.0385
-3.500 -0.1309 0.01866 0.00962 -0.0733 1.0000 0.0460
-3.250 -0.1017 0.01776 0.00857 -0.0738 1.0000 0.0548
-3.000 -0.0736 0.01716 0.00795 -0.0741 1.0000 0.0702
-2.750 -0.0452 0.01660 0.00735 -0.0745 1.0000 0.0914
-2.500 -0.0177 0.01620 0.00702 -0.0748 1.0000 0.1231
-2.250 0.0190 0.01589 0.00677 -0.0770 0.9961 0.1639
-2.000 0.0555 0.01564 0.00660 -0.0791 0.9920 0.2071
-1.750 0.0918 0.01542 0.00648 -0.0812 0.9871 0.2534
-1.500 0.1303 0.01523 0.00638 -0.0837 0.9828 0.3066
-1.250 0.1646 0.01502 0.00630 -0.0852 0.9759 0.3643
-1.000 0.2032 0.01478 0.00623 -0.0876 0.9707 0.4359
-0.750 0.2367 0.01441 0.00616 -0.0888 0.9634 0.5295
-0.500 0.2651 0.01329 0.00602 -0.0880 0.9568 1.0000
-0.250 0.2981 0.01334 0.00591 -0.0890 0.9475 1.0000
0.000 0.3343 0.01337 0.00582 -0.0907 0.9400 1.0000
0.250 0.3696 0.01339 0.00574 -0.0922 0.9318 1.0000
0.500 0.4026 0.01340 0.00569 -0.0931 0.9225 1.0000
0.750 0.4404 0.01335 0.00559 -0.0949 0.9155 1.0000
1.000 0.4716 0.01333 0.00555 -0.0954 0.9046 1.0000
1.250 0.5029 0.01330 0.00553 -0.0958 0.8933 1.0000
1.500 0.5347 0.01324 0.00549 -0.0963 0.8815 1.0000
1.750 0.5663 0.01318 0.00544 -0.0966 0.8688 1.0000
2.000 0.5975 0.01311 0.00541 -0.0969 0.8544 1.0000
2.250 0.6287 0.01304 0.00542 -0.0970 0.8385 1.0000
2.500 0.6605 0.01296 0.00538 -0.0973 0.8212 1.0000
2.750 0.6900 0.01294 0.00541 -0.0971 0.7998 1.0000
3.000 0.7205 0.01291 0.00542 -0.0970 0.7766 1.0000
3.250 0.7499 0.01294 0.00553 -0.0967 0.7495 1.0000
3.500 0.7784 0.01303 0.00564 -0.0962 0.7185 1.0000
3.750 0.8063 0.01318 0.00578 -0.0956 0.6841 1.0000
4.000 0.8327 0.01342 0.00600 -0.0948 0.6459 1.0000
4.250 0.8580 0.01374 0.00627 -0.0938 0.6047 1.0000
4.500 0.8796 0.01428 0.00657 -0.0920 0.5350 1.0000
4.750 0.8962 0.01520 0.00690 -0.0896 0.4310 1.0000
5.000 0.9135 0.01619 0.00742 -0.0877 0.3333 1.0000
5.250 0.9295 0.01755 0.00812 -0.0859 0.2145 1.0000
5.500 0.9432 0.01956 0.00926 -0.0840 0.0846 1.0000
5.750 0.9608 0.02113 0.01056 -0.0824 0.0512 1.0000
6.250 0.9991 0.02362 0.01335 -0.0793 0.0366 1.0000
6.500 1.0167 0.02498 0.01476 -0.0778 0.0314 1.0000
6.750 1.0342 0.02647 0.01639 -0.0760 0.0291 1.0000
7.000 1.0531 0.02802 0.01811 -0.0744 0.0274 1.0000
7.250 1.0731 0.02980 0.02003 -0.0729 0.0260 1.0000
7.500 1.0944 0.03179 0.02220 -0.0717 0.0248 1.0000
7.750 1.1155 0.03386 0.02451 -0.0705 0.0234 1.0000
8.000 1.1335 0.03621 0.02696 -0.0695 0.0214 1.0000
8.250 1.1512 0.03895 0.03005 -0.0680 0.0199 1.0000
8.500 1.1675 0.04179 0.03334 -0.0662 0.0194 1.0000
8.750 1.1799 0.04498 0.03701 -0.0640 0.0190 1.0000
9.000 1.1879 0.04845 0.04096 -0.0615 0.0187 1.0000
9.250 1.1915 0.05213 0.04511 -0.0588 0.0185 1.0000
9.500 1.1903 0.05595 0.04936 -0.0559 0.0184 1.0000
9.750 1.1843 0.05984 0.05364 -0.0529 0.0183 1.0000
10.000 1.1731 0.06357 0.05771 -0.0497 0.0183 1.0000
10.250 1.1573 0.06723 0.06163 -0.0467 0.0183 1.0000
10.500 1.1395 0.07118 0.06582 -0.0446 0.0184 1.0000
10.750 1.1202 0.07565 0.07052 -0.0438 0.0185 1.0000
11.000 1.1000 0.08082 0.07589 -0.0447 0.0186 1.0000
11.250 1.0795 0.08689 0.08213 -0.0473 0.0187 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MA409 (smoothed) (ma409sm-il)