MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.4 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh70-il-1000000.txt Download as CSV file: xf-mh70-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3149 0.09533 0.09387 -0.0216 1.0000 0.0096
-10.000 -0.3122 0.09142 0.08997 -0.0230 1.0000 0.0097
-9.750 -0.3107 0.08719 0.08576 -0.0246 1.0000 0.0097
-9.500 -0.3020 0.08185 0.08040 -0.0286 0.9596 0.0099
-9.250 -0.2953 0.07652 0.07499 -0.0324 0.9293 0.0101
-9.000 -0.2980 0.07196 0.07035 -0.0338 0.9025 0.0102
-8.750 -0.3028 0.06711 0.06543 -0.0354 0.8839 0.0103
-8.500 -0.3085 0.06211 0.06039 -0.0373 0.8690 0.0104
-8.250 -0.3178 0.05658 0.05482 -0.0397 0.8559 0.0104
-8.000 -0.3314 0.05065 0.04886 -0.0428 0.8434 0.0104
-7.750 -0.3720 0.04071 0.03885 -0.0516 0.8301 0.0100
-7.500 -0.3953 0.03094 0.02881 -0.0563 0.8204 0.0100
-7.250 -0.4547 0.02326 0.01946 -0.0603 0.8297 0.0066
-7.000 -0.4416 0.01929 0.01495 -0.0589 0.8204 0.0061
-6.750 -0.4221 0.01665 0.01188 -0.0578 0.8122 0.0059
-6.500 -0.3991 0.01511 0.01005 -0.0570 0.8041 0.0059
-6.250 -0.3744 0.01401 0.00875 -0.0564 0.7967 0.0060
-6.000 -0.3490 0.01321 0.00780 -0.0559 0.7891 0.0063
-5.750 -0.3226 0.01266 0.00712 -0.0555 0.7820 0.0067
-5.500 -0.2959 0.01220 0.00656 -0.0552 0.7745 0.0068
-5.250 -0.2714 0.01119 0.00542 -0.0546 0.7678 0.0073
-5.000 -0.2445 0.01078 0.00497 -0.0544 0.7606 0.0077
-4.500 -0.1902 0.01006 0.00412 -0.0539 0.7470 0.0084
-4.250 -0.1630 0.00973 0.00372 -0.0536 0.7399 0.0088
-4.000 -0.1353 0.00946 0.00339 -0.0535 0.7332 0.0091
-3.750 -0.1081 0.00904 0.00291 -0.0532 0.7261 0.0101
-3.500 -0.0803 0.00885 0.00269 -0.0531 0.7193 0.0113
-3.250 -0.0525 0.00857 0.00238 -0.0529 0.7119 0.0142
-3.000 -0.0250 0.00824 0.00207 -0.0526 0.7049 0.0268
-2.750 0.0026 0.00792 0.00186 -0.0525 0.6974 0.0538
-2.500 0.0298 0.00764 0.00169 -0.0524 0.6901 0.0961
-2.250 0.0573 0.00730 0.00156 -0.0523 0.6824 0.1554
-2.000 0.0844 0.00702 0.00145 -0.0522 0.6746 0.2185
-1.750 0.1120 0.00675 0.00138 -0.0522 0.6665 0.2799
-1.500 0.1394 0.00655 0.00131 -0.0521 0.6583 0.3391
-1.250 0.1672 0.00637 0.00126 -0.0520 0.6495 0.3910
-1.000 0.1944 0.00615 0.00122 -0.0519 0.6407 0.4626
-0.750 0.2216 0.00595 0.00119 -0.0517 0.6312 0.5324
-0.500 0.2488 0.00577 0.00118 -0.0515 0.6216 0.6005
-0.250 0.2753 0.00558 0.00117 -0.0512 0.6114 0.6769
0.000 0.3014 0.00539 0.00118 -0.0507 0.6005 0.7532
0.250 0.3268 0.00525 0.00121 -0.0499 0.5895 0.8237
0.500 0.3515 0.00517 0.00125 -0.0489 0.5782 0.8820
1.000 0.4069 0.00520 0.00130 -0.0482 0.5526 0.9596
1.250 0.4435 0.00528 0.00131 -0.0499 0.5382 0.9775
1.500 0.4819 0.00538 0.00133 -0.0521 0.5224 0.9884
1.750 0.5200 0.00549 0.00135 -0.0543 0.5063 0.9957
2.000 0.5556 0.00560 0.00139 -0.0560 0.4904 1.0000
2.250 0.5806 0.00573 0.00144 -0.0554 0.4753 1.0000
2.500 0.6058 0.00586 0.00150 -0.0548 0.4602 1.0000
2.750 0.6312 0.00601 0.00157 -0.0543 0.4449 1.0000
3.000 0.6566 0.00616 0.00165 -0.0538 0.4294 1.0000
3.250 0.6823 0.00632 0.00174 -0.0534 0.4143 1.0000
3.500 0.7081 0.00649 0.00184 -0.0529 0.3982 1.0000
3.750 0.7340 0.00667 0.00194 -0.0526 0.3821 1.0000
4.250 0.7860 0.00706 0.00219 -0.0519 0.3497 1.0000
4.500 0.8121 0.00726 0.00233 -0.0516 0.3347 1.0000
4.750 0.8382 0.00747 0.00248 -0.0513 0.3191 1.0000
5.000 0.8642 0.00769 0.00263 -0.0510 0.3036 1.0000
5.250 0.8902 0.00792 0.00280 -0.0508 0.2892 1.0000
5.500 0.9161 0.00816 0.00298 -0.0505 0.2741 1.0000
6.000 0.9679 0.00864 0.00336 -0.0499 0.2476 1.0000
6.250 0.9936 0.00889 0.00356 -0.0497 0.2346 1.0000
6.500 1.0193 0.00914 0.00377 -0.0494 0.2230 1.0000
6.750 1.0447 0.00942 0.00400 -0.0491 0.2109 1.0000
7.000 1.0699 0.00971 0.00425 -0.0487 0.1997 1.0000
7.250 1.0950 0.01000 0.00450 -0.0484 0.1887 1.0000
7.500 1.1203 0.01026 0.00474 -0.0481 0.1794 1.0000
7.750 1.1450 0.01057 0.00502 -0.0477 0.1696 1.0000
8.000 1.1693 0.01091 0.00532 -0.0473 0.1594 1.0000
8.250 1.1941 0.01120 0.00559 -0.0469 0.1511 1.0000
8.500 1.2181 0.01154 0.00592 -0.0465 0.1426 1.0000
8.750 1.2418 0.01189 0.00624 -0.0460 0.1341 1.0000
9.000 1.2657 0.01222 0.00657 -0.0455 0.1267 1.0000
9.250 1.2882 0.01264 0.00695 -0.0449 0.1179 1.0000
9.500 1.3116 0.01298 0.00729 -0.0443 0.1113 1.0000
9.750 1.3337 0.01340 0.00770 -0.0436 0.1038 1.0000
10.000 1.3557 0.01381 0.00810 -0.0429 0.0972 1.0000
10.250 1.3771 0.01424 0.00853 -0.0422 0.0910 1.0000
10.500 1.3974 0.01472 0.00899 -0.0412 0.0842 1.0000
10.750 1.4177 0.01518 0.00946 -0.0403 0.0782 1.0000
11.000 1.4356 0.01577 0.01001 -0.0391 0.0709 1.0000
11.250 1.4546 0.01624 0.01050 -0.0380 0.0661 1.0000
11.500 1.4703 0.01688 0.01113 -0.0365 0.0601 1.0000
11.750 1.4853 0.01739 0.01167 -0.0347 0.0561 1.0000
12.000 1.4947 0.01811 0.01237 -0.0322 0.0511 1.0000
12.250 1.5066 0.01871 0.01301 -0.0302 0.0476 1.0000
12.500 1.5146 0.01958 0.01387 -0.0279 0.0434 1.0000
12.750 1.5251 0.02037 0.01470 -0.0260 0.0399 1.0000
13.250 1.5419 0.02238 0.01676 -0.0225 0.0337 1.0000
13.500 1.5486 0.02360 0.01800 -0.0209 0.0309 1.0000
13.750 1.5556 0.02487 0.01930 -0.0194 0.0278 1.0000
14.000 1.5625 0.02622 0.02070 -0.0182 0.0262 1.0000
14.250 1.5666 0.02785 0.02236 -0.0169 0.0238 1.0000
14.500 1.5730 0.02936 0.02393 -0.0159 0.0219 1.0000
14.750 1.5756 0.03128 0.02588 -0.0150 0.0201 1.0000
15.000 1.5799 0.03311 0.02778 -0.0142 0.0186 1.0000
15.250 1.5829 0.03515 0.02988 -0.0136 0.0174 1.0000
15.500 1.5835 0.03749 0.03229 -0.0132 0.0164 1.0000
15.750 1.5839 0.03993 0.03481 -0.0129 0.0154 1.0000
16.000 1.5849 0.04242 0.03738 -0.0128 0.0146 1.0000
16.250 1.5831 0.04529 0.04033 -0.0128 0.0138 1.0000
16.500 1.5790 0.04855 0.04366 -0.0131 0.0130 1.0000
16.750 1.5748 0.05200 0.04720 -0.0137 0.0124 1.0000
17.000 1.5720 0.05540 0.05070 -0.0144 0.0119 1.0000
17.250 1.5668 0.05925 0.05467 -0.0154 0.0114 1.0000
17.500 1.5587 0.06366 0.05916 -0.0168 0.0106 1.0000
17.750 1.5501 0.06830 0.06391 -0.0184 0.0104 1.0000
18.000 1.5376 0.07368 0.06940 -0.0205 0.0099 1.0000
18.250 1.5276 0.07885 0.07469 -0.0226 0.0097 1.0000
18.500 1.5167 0.08429 0.08024 -0.0249 0.0094 1.0000
18.750 1.5033 0.09029 0.08636 -0.0276 0.0091 1.0000
19.000 1.4887 0.09665 0.09285 -0.0306 0.0088 1.0000
19.250 1.4728 0.10338 0.09970 -0.0339 0.0087 1.0000
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Polar data table (+)
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