MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 50,000 Max Cl/Cd: 35.61 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh70-il-50000-n5.txt Download as CSV file: xf-mh70-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3766 0.09653 0.08977 -0.0293 1.0000 0.0469
-8.750 -0.3756 0.09257 0.08589 -0.0312 1.0000 0.0464
-8.500 -0.3753 0.08858 0.08199 -0.0332 1.0000 0.0452
-8.000 -0.4024 0.07512 0.06874 -0.0449 1.0000 0.0407
-7.750 -0.4075 0.07085 0.06451 -0.0469 1.0000 0.0406
-7.500 -0.4119 0.06720 0.06088 -0.0478 1.0000 0.0403
-7.250 -0.4190 0.06375 0.05742 -0.0478 1.0000 0.0401
-7.000 -0.4278 0.06063 0.05426 -0.0469 1.0000 0.0400
-6.750 -0.4360 0.05786 0.05142 -0.0453 1.0000 0.0398
-6.500 -0.4429 0.05506 0.04847 -0.0435 1.0000 0.0396
-6.250 -0.4473 0.05195 0.04513 -0.0420 1.0000 0.0396
-6.000 -0.4366 0.04808 0.04088 -0.0429 0.9956 0.0395
-5.750 -0.4093 0.04346 0.03565 -0.0463 0.9857 0.0396
-5.500 -0.3803 0.03951 0.03101 -0.0487 0.9764 0.0401
-5.250 -0.3484 0.03631 0.02723 -0.0508 0.9683 0.0412
-5.000 -0.3163 0.03426 0.02500 -0.0527 0.9599 0.0443
-4.750 -0.2830 0.03211 0.02233 -0.0541 0.9518 0.0479
-4.500 -0.2477 0.03005 0.01998 -0.0556 0.9446 0.0511
-4.250 -0.2143 0.02862 0.01829 -0.0567 0.9365 0.0580
-4.000 -0.1784 0.02717 0.01676 -0.0582 0.9294 0.0664
-3.750 -0.1459 0.02595 0.01541 -0.0591 0.9210 0.0813
-3.500 -0.1101 0.02466 0.01415 -0.0606 0.9136 0.1100
-3.250 -0.0808 0.02333 0.01325 -0.0614 0.9044 0.1781
-3.000 -0.0487 0.02220 0.01276 -0.0626 0.8969 0.3188
-2.750 -0.0259 0.02160 0.01260 -0.0617 0.8863 0.4394
-2.500 -0.0003 0.02106 0.01246 -0.0606 0.8777 0.5551
-2.250 0.0229 0.02065 0.01241 -0.0584 0.8683 0.6665
-2.000 0.0530 0.02040 0.01235 -0.0570 0.8598 0.7896
-1.750 0.1148 0.02020 0.01198 -0.0618 0.8535 0.9149
-1.500 0.1965 0.01989 0.01121 -0.0716 0.8489 0.9949
-1.250 0.2188 0.02002 0.01107 -0.0711 0.8364 1.0000
-1.000 0.2392 0.02019 0.01099 -0.0700 0.8243 1.0000
-0.750 0.2623 0.02033 0.01089 -0.0691 0.8135 1.0000
-0.500 0.2869 0.02046 0.01080 -0.0684 0.8029 1.0000
-0.250 0.3079 0.02068 0.01084 -0.0672 0.7906 1.0000
0.000 0.3310 0.02087 0.01085 -0.0663 0.7792 1.0000
0.250 0.3579 0.02095 0.01075 -0.0657 0.7698 1.0000
0.500 0.3792 0.02120 0.01087 -0.0644 0.7570 1.0000
0.750 0.4019 0.02141 0.01096 -0.0634 0.7449 1.0000
1.000 0.4266 0.02156 0.01099 -0.0625 0.7338 1.0000
1.250 0.4521 0.02166 0.01098 -0.0616 0.7229 1.0000
1.500 0.4746 0.02190 0.01114 -0.0605 0.7099 1.0000
1.750 0.4980 0.02210 0.01127 -0.0595 0.6973 1.0000
2.000 0.5226 0.02224 0.01134 -0.0585 0.6853 1.0000
2.250 0.5488 0.02229 0.01131 -0.0576 0.6741 1.0000
2.500 0.5723 0.02248 0.01145 -0.0566 0.6607 1.0000
2.750 0.5957 0.02268 0.01162 -0.0555 0.6469 1.0000
3.000 0.6195 0.02286 0.01178 -0.0545 0.6331 1.0000
3.250 0.6436 0.02302 0.01193 -0.0535 0.6192 1.0000
3.500 0.6678 0.02318 0.01206 -0.0525 0.6052 1.0000
3.750 0.6921 0.02333 0.01219 -0.0515 0.5909 1.0000
4.000 0.7163 0.02349 0.01233 -0.0505 0.5762 1.0000
4.250 0.7405 0.02367 0.01253 -0.0495 0.5612 1.0000
4.500 0.7643 0.02387 0.01272 -0.0485 0.5456 1.0000
4.750 0.7880 0.02410 0.01295 -0.0475 0.5298 1.0000
5.000 0.8115 0.02436 0.01323 -0.0465 0.5136 1.0000
5.250 0.8348 0.02465 0.01352 -0.0455 0.4971 1.0000
5.500 0.8578 0.02497 0.01384 -0.0444 0.4804 1.0000
5.750 0.8806 0.02533 0.01420 -0.0434 0.4637 1.0000
6.000 0.9031 0.02573 0.01463 -0.0424 0.4469 1.0000
6.250 0.9253 0.02617 0.01507 -0.0414 0.4303 1.0000
6.500 0.9471 0.02666 0.01556 -0.0403 0.4138 1.0000
6.750 0.9686 0.02720 0.01612 -0.0393 0.3976 1.0000
7.000 0.9895 0.02779 0.01672 -0.0383 0.3816 1.0000
7.250 1.0100 0.02844 0.01739 -0.0372 0.3660 1.0000
7.500 1.0299 0.02913 0.01813 -0.0361 0.3506 1.0000
7.750 1.0492 0.02990 0.01895 -0.0351 0.3358 1.0000
8.000 1.0678 0.03072 0.01982 -0.0339 0.3213 1.0000
8.250 1.0857 0.03159 0.02078 -0.0328 0.3074 1.0000
8.500 1.1032 0.03254 0.02183 -0.0316 0.2941 1.0000
8.750 1.1200 0.03351 0.02289 -0.0305 0.2814 1.0000
9.000 1.1370 0.03452 0.02396 -0.0293 0.2696 1.0000
9.250 1.1544 0.03549 0.02497 -0.0282 0.2584 1.0000
9.500 1.1687 0.03662 0.02623 -0.0269 0.2470 1.0000
9.750 1.1816 0.03792 0.02769 -0.0255 0.2365 1.0000
10.000 1.1956 0.03911 0.02895 -0.0242 0.2265 1.0000
10.250 1.2087 0.04031 0.03024 -0.0229 0.2170 1.0000
10.500 1.2164 0.04191 0.03206 -0.0212 0.2080 1.0000
10.750 1.2284 0.04311 0.03327 -0.0198 0.1996 1.0000
11.000 1.2309 0.04493 0.03533 -0.0179 0.1916 1.0000
11.250 1.2398 0.04645 0.03691 -0.0165 0.1841 1.0000
11.500 1.2402 0.04851 0.03919 -0.0150 0.1769 1.0000
11.750 1.2469 0.05026 0.04101 -0.0138 0.1701 1.0000
12.000 1.2431 0.05291 0.04393 -0.0127 0.1639 1.0000
12.250 1.2520 0.05451 0.04553 -0.0118 0.1574 1.0000
12.500 1.2392 0.05823 0.04957 -0.0112 0.1524 1.0000
12.750 1.2417 0.06055 0.05198 -0.0107 0.1467 1.0000
13.000 1.2356 0.06398 0.05558 -0.0106 0.1421 1.0000
13.250 1.2157 0.06923 0.06111 -0.0116 0.1385 1.0000
13.500 1.2121 0.07255 0.06454 -0.0119 0.1337 1.0000
13.750 1.2064 0.07641 0.06849 -0.0127 0.1297 1.0000
14.000 1.1657 0.08585 0.07821 -0.0168 0.1283 1.0000
14.250 1.0960 0.10219 0.09473 -0.0257 0.1282 1.0000
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Polar data table (+)
Polar graphs
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