MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 50,000 Max Cl/Cd: 27.4 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh70-il-50000.txt Download as CSV file: xf-mh70-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3925 0.12272 0.11603 -0.0148 1.0000 0.2016
-9.500 -0.3605 0.11589 0.10918 -0.0128 1.0000 0.2115
-9.250 -0.3823 0.11616 0.10961 -0.0161 1.0000 0.2173
-9.000 -0.3504 0.10962 0.10304 -0.0142 1.0000 0.2269
-8.750 -0.3667 0.10863 0.10221 -0.0166 1.0000 0.2339
-8.500 -0.3416 0.10355 0.09712 -0.0153 1.0000 0.2434
-8.250 -0.3465 0.10109 0.09478 -0.0164 1.0000 0.2514
-8.000 -0.3399 0.09828 0.09201 -0.0164 1.0000 0.2624
-7.750 -0.3303 0.09443 0.08825 -0.0161 1.0000 0.2708
-7.500 -0.3512 0.09375 0.08776 -0.0172 1.0000 0.2813
-7.250 -0.3290 0.08932 0.08334 -0.0159 1.0000 0.2934
-7.000 -0.3224 0.08610 0.08022 -0.0151 1.0000 0.3044
-6.750 -0.3354 0.08444 0.07875 -0.0141 1.0000 0.3152
-6.500 -0.3515 0.08357 0.07807 -0.0115 1.0000 0.3275
-6.250 -0.3456 0.08060 0.07519 -0.0088 1.0000 0.3415
-5.250 -0.4382 0.06004 0.05423 -0.0303 1.0000 0.1569
-5.000 -0.4270 0.05259 0.04615 -0.0336 1.0000 0.1239
-4.750 -0.4147 0.04728 0.04024 -0.0346 1.0000 0.1124
-4.500 -0.3992 0.04401 0.03659 -0.0343 1.0000 0.1089
-4.250 -0.3822 0.04089 0.03304 -0.0340 1.0000 0.1082
-4.000 -0.3627 0.03813 0.02978 -0.0338 1.0000 0.1084
-3.750 -0.3408 0.03560 0.02669 -0.0334 1.0000 0.1095
-3.500 -0.3179 0.03349 0.02405 -0.0328 1.0000 0.1106
-3.250 -0.2975 0.03172 0.02228 -0.0322 1.0000 0.1179
-3.000 -0.2744 0.03016 0.02031 -0.0314 1.0000 0.1269
-2.750 -0.2529 0.02886 0.01892 -0.0306 1.0000 0.1421
-2.500 -0.2313 0.02774 0.01789 -0.0298 1.0000 0.1654
-2.250 -0.2095 0.02654 0.01688 -0.0289 1.0000 0.2146
-2.000 -0.1861 0.02436 0.01604 -0.0279 1.0000 0.4144
-1.750 -0.1776 0.02297 0.01615 -0.0228 1.0000 0.6678
-1.500 -0.1183 0.02268 0.01590 -0.0281 0.9909 1.0000
-1.250 -0.0695 0.02360 0.01614 -0.0335 0.9783 1.0000
-1.000 -0.0242 0.02450 0.01652 -0.0381 0.9653 1.0000
-0.750 0.0194 0.02539 0.01699 -0.0421 0.9520 1.0000
-0.500 0.0620 0.02628 0.01753 -0.0459 0.9385 1.0000
-0.250 0.1042 0.02715 0.01810 -0.0495 0.9247 1.0000
0.000 0.1463 0.02800 0.01870 -0.0528 0.9107 1.0000
0.250 0.1863 0.02880 0.01929 -0.0557 0.8964 1.0000
0.500 0.2215 0.02955 0.01986 -0.0577 0.8815 1.0000
0.750 0.2556 0.03030 0.02046 -0.0594 0.8664 1.0000
1.000 0.2895 0.03104 0.02108 -0.0609 0.8512 1.0000
1.250 0.3229 0.03177 0.02170 -0.0622 0.8358 1.0000
1.500 0.3556 0.03247 0.02232 -0.0633 0.8203 1.0000
1.750 0.3886 0.03315 0.02292 -0.0644 0.8047 1.0000
2.000 0.4220 0.03377 0.02350 -0.0653 0.7889 1.0000
2.250 0.4550 0.03436 0.02405 -0.0660 0.7731 1.0000
2.500 0.4867 0.03490 0.02457 -0.0664 0.7572 1.0000
2.750 0.5170 0.03540 0.02507 -0.0664 0.7413 1.0000
3.000 0.5468 0.03585 0.02551 -0.0661 0.7253 1.0000
3.250 0.5763 0.03623 0.02589 -0.0657 0.7094 1.0000
3.500 0.6052 0.03656 0.02623 -0.0651 0.6935 1.0000
3.750 0.6344 0.03679 0.02650 -0.0643 0.6776 1.0000
4.000 0.6633 0.03694 0.02668 -0.0633 0.6618 1.0000
4.250 0.6919 0.03704 0.02681 -0.0622 0.6460 1.0000
4.500 0.7204 0.03705 0.02686 -0.0610 0.6302 1.0000
4.750 0.7491 0.03701 0.02689 -0.0597 0.6144 1.0000
5.000 0.7784 0.03684 0.02676 -0.0583 0.5986 1.0000
5.250 0.8079 0.03661 0.02658 -0.0569 0.5827 1.0000
5.500 0.8383 0.03627 0.02630 -0.0555 0.5668 1.0000
5.750 0.8683 0.03596 0.02603 -0.0540 0.5508 1.0000
6.000 0.8877 0.03660 0.02676 -0.0524 0.5325 1.0000
6.250 0.9100 0.03704 0.02727 -0.0509 0.5149 1.0000
6.500 0.9351 0.03725 0.02753 -0.0494 0.4976 1.0000
6.750 0.9611 0.03742 0.02775 -0.0481 0.4805 1.0000
7.000 0.9876 0.03760 0.02800 -0.0467 0.4636 1.0000
7.250 1.0137 0.03788 0.02830 -0.0454 0.4469 1.0000
7.500 1.0389 0.03833 0.02879 -0.0442 0.4304 1.0000
7.750 1.0639 0.03883 0.02934 -0.0430 0.4140 1.0000
8.000 1.0863 0.03968 0.03024 -0.0418 0.3982 1.0000
8.250 1.1077 0.04063 0.03126 -0.0405 0.3826 1.0000
8.500 1.1244 0.04207 0.03283 -0.0392 0.3680 1.0000
8.750 1.1383 0.04374 0.03465 -0.0377 0.3539 1.0000
9.000 1.1473 0.04587 0.03695 -0.0361 0.3409 1.0000
9.250 1.1575 0.04798 0.03921 -0.0347 0.3287 1.0000
9.500 1.1750 0.04947 0.04080 -0.0334 0.3162 1.0000
9.750 1.1990 0.05054 0.04191 -0.0324 0.3034 1.0000
10.000 1.1627 0.05638 0.04812 -0.0297 0.2979 1.0000
10.250 1.1159 0.06326 0.05514 -0.0277 0.2949 1.0000
10.500 1.0740 0.07076 0.06264 -0.0277 0.2916 1.0000
11.000 1.1962 0.06563 0.05778 -0.0243 0.2596 1.0000
11.250 0.7645 0.13654 0.12770 -0.0666 0.4264 1.0000
11.500 0.7601 0.13890 0.13011 -0.0669 0.4146 1.0000
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Polar data table (+)
Polar graphs
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