MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 200,000 Max Cl/Cd: 70.26 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh70-il-200000.txt Download as CSV file: xf-mh70-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 70 11.08%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2862 0.08997 0.08688 -0.0274 1.0000 0.0469
-9.000 -0.2980 0.08486 0.08182 -0.0321 1.0000 0.0487
-8.750 -0.3107 0.07956 0.07657 -0.0372 1.0000 0.0491
-8.500 -0.3229 0.07396 0.07104 -0.0422 1.0000 0.0493
-8.250 -0.2976 0.07173 0.06884 -0.0360 1.0000 0.0510
-8.000 -0.2920 0.06874 0.06589 -0.0361 1.0000 0.0523
-7.750 -0.2945 0.06532 0.06254 -0.0370 1.0000 0.0536
-7.500 -0.4314 0.06895 0.06581 -0.0480 0.9977 0.0492
-7.250 -0.4086 0.06456 0.06161 -0.0481 0.9934 0.0505
-7.000 -0.3230 0.04119 0.03786 -0.0682 0.9638 0.0597
-6.750 -0.2938 0.03784 0.03477 -0.0681 0.9590 0.0617
-6.500 -0.3330 0.04811 0.04458 -0.0683 0.9659 0.0615
-6.250 -0.3031 0.04501 0.04141 -0.0714 0.9585 0.0651
-6.000 -0.2816 0.04067 0.03669 -0.0748 0.9467 0.0738
-5.750 -0.2670 0.02775 0.02194 -0.0739 0.9338 0.0346
-5.500 -0.2408 0.02510 0.01895 -0.0735 0.9250 0.0320
-5.250 -0.2178 0.02247 0.01586 -0.0723 0.9147 0.0300
-5.000 -0.1937 0.02045 0.01336 -0.0710 0.9050 0.0289
-4.750 -0.1686 0.01909 0.01179 -0.0699 0.8967 0.0292
-4.500 -0.1446 0.01797 0.01058 -0.0688 0.8866 0.0300
-4.250 -0.1202 0.01702 0.00953 -0.0676 0.8784 0.0317
-4.000 -0.0960 0.01614 0.00855 -0.0664 0.8690 0.0339
-3.750 -0.0721 0.01547 0.00788 -0.0655 0.8605 0.0404
-3.500 -0.0486 0.01461 0.00702 -0.0643 0.8519 0.0492
-3.250 -0.0254 0.01361 0.00617 -0.0633 0.8432 0.0823
-3.000 -0.0039 0.01238 0.00568 -0.0624 0.8353 0.2367
-2.750 0.0198 0.01190 0.00555 -0.0617 0.8263 0.3376
-2.500 0.0438 0.01152 0.00539 -0.0607 0.8187 0.4234
-2.250 0.0672 0.01115 0.00532 -0.0596 0.8095 0.5130
-2.000 0.0894 0.01072 0.00522 -0.0580 0.8022 0.6178
-1.750 0.1104 0.01037 0.00525 -0.0559 0.7927 0.7258
-1.500 0.1324 0.01014 0.00521 -0.0534 0.7857 0.8257
-1.250 0.1636 0.01007 0.00519 -0.0529 0.7760 0.9051
-1.000 0.2093 0.01003 0.00501 -0.0556 0.7686 0.9546
-0.750 0.2634 0.00999 0.00481 -0.0606 0.7586 0.9836
-0.500 0.3156 0.00990 0.00454 -0.0655 0.7493 1.0000
-0.250 0.3375 0.00990 0.00440 -0.0643 0.7397 1.0000
0.000 0.3600 0.00993 0.00433 -0.0632 0.7290 1.0000
0.250 0.3831 0.00996 0.00423 -0.0622 0.7196 1.0000
0.500 0.4066 0.01000 0.00416 -0.0612 0.7089 1.0000
0.750 0.4305 0.01005 0.00413 -0.0603 0.6978 1.0000
1.000 0.4547 0.01010 0.00406 -0.0594 0.6876 1.0000
1.250 0.4792 0.01015 0.00401 -0.0586 0.6763 1.0000
1.500 0.5037 0.01021 0.00401 -0.0578 0.6642 1.0000
1.750 0.5285 0.01028 0.00400 -0.0570 0.6522 1.0000
2.000 0.5536 0.01035 0.00399 -0.0562 0.6404 1.0000
2.250 0.5789 0.01043 0.00397 -0.0555 0.6281 1.0000
2.500 0.6041 0.01051 0.00400 -0.0549 0.6143 1.0000
2.750 0.6295 0.01061 0.00405 -0.0543 0.6002 1.0000
3.000 0.6549 0.01072 0.00410 -0.0536 0.5857 1.0000
3.250 0.6803 0.01084 0.00416 -0.0530 0.5707 1.0000
3.500 0.7057 0.01098 0.00424 -0.0524 0.5552 1.0000
3.750 0.7311 0.01114 0.00433 -0.0519 0.5392 1.0000
4.000 0.7563 0.01132 0.00445 -0.0513 0.5227 1.0000
4.250 0.7814 0.01152 0.00458 -0.0507 0.5059 1.0000
4.500 0.8063 0.01176 0.00473 -0.0501 0.4888 1.0000
4.750 0.8312 0.01200 0.00494 -0.0495 0.4706 1.0000
5.000 0.8558 0.01226 0.00516 -0.0489 0.4522 1.0000
5.250 0.8802 0.01255 0.00539 -0.0483 0.4339 1.0000
5.500 0.9043 0.01287 0.00566 -0.0477 0.4156 1.0000
5.750 0.9282 0.01322 0.00593 -0.0471 0.3977 1.0000
6.000 0.9519 0.01359 0.00624 -0.0464 0.3796 1.0000
6.250 0.9754 0.01396 0.00660 -0.0458 0.3616 1.0000
6.500 0.9987 0.01437 0.00697 -0.0451 0.3442 1.0000
6.750 1.0215 0.01480 0.00736 -0.0444 0.3274 1.0000
7.000 1.0441 0.01526 0.00778 -0.0437 0.3112 1.0000
7.250 1.0664 0.01574 0.00824 -0.0430 0.2959 1.0000
7.500 1.0884 0.01624 0.00872 -0.0422 0.2812 1.0000
7.750 1.1101 0.01677 0.00922 -0.0414 0.2673 1.0000
8.000 1.1313 0.01732 0.00977 -0.0406 0.2541 1.0000
8.250 1.1520 0.01791 0.01033 -0.0397 0.2416 1.0000
8.500 1.1721 0.01855 0.01091 -0.0387 0.2299 1.0000
8.750 1.1924 0.01909 0.01152 -0.0378 0.2181 1.0000
9.000 1.2120 0.01970 0.01218 -0.0368 0.2072 1.0000
9.250 1.2306 0.02039 0.01286 -0.0357 0.1971 1.0000
9.500 1.2483 0.02111 0.01355 -0.0345 0.1874 1.0000
9.750 1.2660 0.02173 0.01429 -0.0332 0.1776 1.0000
10.000 1.2821 0.02253 0.01509 -0.0319 0.1690 1.0000
10.250 1.2969 0.02326 0.01585 -0.0304 0.1604 1.0000
10.500 1.3106 0.02404 0.01672 -0.0287 0.1523 1.0000
10.750 1.3212 0.02497 0.01759 -0.0267 0.1451 1.0000
11.000 1.3318 0.02575 0.01854 -0.0247 0.1377 1.0000
11.250 1.3408 0.02688 0.01959 -0.0228 0.1310 1.0000
11.500 1.3497 0.02780 0.02070 -0.0210 0.1242 1.0000
11.750 1.3572 0.02912 0.02194 -0.0194 0.1180 1.0000
12.000 1.3648 0.03024 0.02328 -0.0178 0.1118 1.0000
12.250 1.3705 0.03171 0.02471 -0.0164 0.1061 1.0000
12.500 1.3770 0.03317 0.02635 -0.0151 0.1006 1.0000
12.750 1.3815 0.03478 0.02800 -0.0140 0.0954 1.0000
13.000 1.3861 0.03662 0.02992 -0.0129 0.0905 1.0000
13.250 1.3898 0.03845 0.03187 -0.0120 0.0857 1.0000
13.500 1.3926 0.04058 0.03394 -0.0112 0.0812 1.0000
13.750 1.3941 0.04277 0.03636 -0.0106 0.0772 1.0000
14.000 1.3953 0.04507 0.03874 -0.0103 0.0734 1.0000
14.250 1.3963 0.04759 0.04126 -0.0098 0.0698 1.0000
14.500 1.3953 0.05033 0.04422 -0.0098 0.0665 1.0000
14.750 1.3939 0.05314 0.04712 -0.0100 0.0634 1.0000
15.000 1.3940 0.05594 0.04987 -0.0098 0.0601 1.0000
15.250 1.3898 0.05938 0.05356 -0.0104 0.0579 1.0000
15.500 1.3862 0.06283 0.05715 -0.0111 0.0553 1.0000
15.750 1.3836 0.06624 0.06061 -0.0120 0.0530 1.0000
16.000 1.3823 0.06958 0.06396 -0.0124 0.0506 1.0000
16.250 1.3746 0.07405 0.06867 -0.0139 0.0489 1.0000
16.500 1.3682 0.07845 0.07324 -0.0156 0.0470 1.0000
16.750 1.3642 0.08254 0.07741 -0.0172 0.0453 1.0000
17.000 1.3659 0.08553 0.08032 -0.0175 0.0429 1.0000
17.250 1.3541 0.09122 0.08627 -0.0202 0.0420 1.0000
17.500 1.3418 0.09719 0.09248 -0.0232 0.0408 1.0000
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Polar data table (+)
Polar graphs
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