MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 100,000 Max Cl/Cd: 39.74 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh80-il-100000-n5.txt Download as CSV file: xf-mh80-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 80 12.72%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4957 0.10351 0.09917 0.0159 1.0000 0.0237
-9.500 -0.4919 0.09957 0.09528 0.0141 1.0000 0.0234
-9.250 -0.4901 0.09519 0.09097 0.0118 1.0000 0.0230
-9.000 -0.4911 0.09019 0.08603 0.0088 1.0000 0.0227
-8.750 -0.4940 0.08475 0.08066 0.0051 1.0000 0.0222
-8.250 -0.5439 0.06351 0.05929 -0.0112 1.0000 0.0199
-8.000 -0.5498 0.05884 0.05450 -0.0128 1.0000 0.0197
-7.750 -0.5522 0.05420 0.04968 -0.0139 1.0000 0.0196
-7.500 -0.5477 0.04936 0.04449 -0.0152 0.9082 0.0194
-7.250 -0.5442 0.04542 0.04006 -0.0143 0.8572 0.0193
-7.000 -0.5395 0.04174 0.03585 -0.0124 0.8247 0.0193
-6.750 -0.5306 0.03844 0.03197 -0.0105 0.7990 0.0194
-6.500 -0.5182 0.03521 0.02803 -0.0086 0.7765 0.0201
-6.250 -0.4998 0.03358 0.02616 -0.0074 0.7546 0.0206
-6.000 -0.4800 0.03216 0.02447 -0.0063 0.7345 0.0216
-5.750 -0.4592 0.03028 0.02214 -0.0050 0.7164 0.0225
-5.500 -0.4366 0.02839 0.01979 -0.0038 0.6992 0.0232
-5.250 -0.4125 0.02666 0.01763 -0.0026 0.6827 0.0238
-5.000 -0.3881 0.02527 0.01605 -0.0018 0.6665 0.0244
-4.750 -0.3634 0.02414 0.01477 -0.0010 0.6507 0.0253
-4.500 -0.3385 0.02308 0.01354 -0.0001 0.6356 0.0265
-4.250 -0.3133 0.02213 0.01236 0.0008 0.6212 0.0284
-4.000 -0.2890 0.02136 0.01155 0.0016 0.6074 0.0312
-3.750 -0.2645 0.02059 0.01064 0.0025 0.5943 0.0349
-3.500 -0.2395 0.01987 0.00978 0.0033 0.5809 0.0391
-3.250 -0.2145 0.01917 0.00904 0.0040 0.5682 0.0472
-3.000 -0.1897 0.01843 0.00829 0.0048 0.5563 0.0635
-2.750 -0.1658 0.01753 0.00771 0.0056 0.5449 0.1182
-2.500 -0.1416 0.01677 0.00735 0.0062 0.5329 0.2119
-2.250 -0.1182 0.01605 0.00705 0.0070 0.5222 0.3210
-2.000 -0.0977 0.01508 0.00683 0.0084 0.5118 0.4999
-1.750 -0.0721 0.01430 0.00700 0.0106 0.5009 0.7366
-1.500 -0.0305 0.01449 0.00716 0.0099 0.4893 0.8518
-1.250 0.0039 0.01470 0.00715 0.0096 0.4784 0.8962
-1.000 0.0390 0.01489 0.00712 0.0090 0.4675 0.9262
-0.750 0.0842 0.01507 0.00701 0.0062 0.4570 0.9468
-0.500 0.1340 0.01519 0.00687 0.0024 0.4454 0.9652
-0.250 0.1881 0.01527 0.00671 -0.0025 0.4341 0.9843
0.000 0.2440 0.01523 0.00640 -0.0081 0.4240 1.0000
0.250 0.2680 0.01530 0.00634 -0.0075 0.4156 1.0000
0.500 0.2917 0.01539 0.00624 -0.0068 0.4090 1.0000
0.750 0.3159 0.01550 0.00627 -0.0063 0.4010 1.0000
1.000 0.3397 0.01562 0.00625 -0.0056 0.3946 1.0000
1.250 0.3639 0.01578 0.00631 -0.0050 0.3879 1.0000
1.500 0.3879 0.01593 0.00636 -0.0044 0.3812 1.0000
1.750 0.4117 0.01611 0.00639 -0.0037 0.3757 1.0000
2.000 0.4360 0.01630 0.00655 -0.0031 0.3688 1.0000
2.250 0.4599 0.01650 0.00665 -0.0024 0.3633 1.0000
2.500 0.4838 0.01672 0.00678 -0.0017 0.3584 1.0000
2.750 0.5078 0.01697 0.00702 -0.0011 0.3522 1.0000
3.000 0.5316 0.01720 0.00716 -0.0004 0.3471 1.0000
3.250 0.5554 0.01746 0.00734 0.0003 0.3424 1.0000
3.500 0.5793 0.01775 0.00766 0.0008 0.3370 1.0000
3.750 0.6031 0.01803 0.00790 0.0015 0.3323 1.0000
4.000 0.6267 0.01832 0.00807 0.0023 0.3283 1.0000
4.250 0.6504 0.01867 0.00847 0.0028 0.3232 1.0000
4.500 0.6740 0.01899 0.00881 0.0035 0.3183 1.0000
4.750 0.6976 0.01931 0.00907 0.0042 0.3144 1.0000
5.000 0.7211 0.01968 0.00940 0.0048 0.3107 1.0000
5.250 0.7445 0.02010 0.00990 0.0054 0.3059 1.0000
5.500 0.7678 0.02047 0.01030 0.0060 0.3016 1.0000
5.750 0.7914 0.02082 0.01059 0.0067 0.2981 1.0000
6.000 0.8146 0.02127 0.01106 0.0073 0.2945 1.0000
6.250 0.8374 0.02177 0.01169 0.0079 0.2901 1.0000
6.500 0.8606 0.02221 0.01216 0.0085 0.2861 1.0000
6.750 0.8841 0.02259 0.01251 0.0091 0.2827 1.0000
7.000 0.9073 0.02309 0.01304 0.0096 0.2793 1.0000
7.250 0.9294 0.02372 0.01383 0.0101 0.2751 1.0000
7.500 0.9520 0.02425 0.01444 0.0106 0.2714 1.0000
7.750 0.9754 0.02469 0.01489 0.0111 0.2681 1.0000
8.000 0.9991 0.02514 0.01531 0.0116 0.2651 1.0000
8.250 1.0193 0.02597 0.01637 0.0121 0.2609 1.0000
8.500 1.0406 0.02666 0.01720 0.0126 0.2572 1.0000
8.750 1.0630 0.02719 0.01778 0.0131 0.2539 1.0000
9.000 1.0867 0.02763 0.01819 0.0135 0.2510 1.0000
9.250 1.1053 0.02856 0.01935 0.0140 0.2472 1.0000
9.500 1.1235 0.02950 0.02047 0.0146 0.2434 1.0000
9.750 1.1437 0.03020 0.02128 0.0151 0.2400 1.0000
10.000 1.1661 0.03069 0.02179 0.0156 0.2371 1.0000
10.250 1.1851 0.03151 0.02271 0.0161 0.2340 1.0000
10.500 1.1965 0.03290 0.02437 0.0169 0.2299 1.0000
10.750 1.2114 0.03392 0.02555 0.0176 0.2265 1.0000
11.000 1.2308 0.03453 0.02622 0.0181 0.2234 1.0000
11.250 1.2547 0.03487 0.02651 0.0186 0.2208 1.0000
11.500 1.2508 0.03712 0.02914 0.0198 0.2169 1.0000
11.750 1.2509 0.03893 0.03115 0.0209 0.2134 1.0000
12.000 1.2568 0.04013 0.03244 0.0220 0.2104 1.0000
12.250 1.2779 0.04042 0.03274 0.0227 0.2076 1.0000
12.500 1.2633 0.04333 0.03583 0.0233 0.2048 1.0000
12.750 1.0638 0.07024 0.06312 0.0094 0.1957 1.0000
13.000 1.1042 0.06729 0.06024 0.0119 0.1948 1.0000
13.250 1.1661 0.06157 0.05454 0.0160 0.1940 1.0000
15.250 0.9115 0.13463 0.12797 -0.0205 0.1419 1.0000
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Polar data table (+)
Polar graphs
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