MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 100,000 Max Cl/Cd: 44.99 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh60-il-100000.txt Download as CSV file: xf-mh60-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 60 10.08%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5204 0.09090 0.08676 0.0018 1.0000 0.1147
-8.000 -0.5254 0.08698 0.08291 -0.0022 1.0000 0.1203
-7.750 -0.5543 0.08078 0.07681 -0.0138 1.0000 0.1238
-7.500 -0.5275 0.07823 0.07431 -0.0082 1.0000 0.1274
-6.500 -0.5320 0.04138 0.03583 -0.0304 1.0000 0.0494
-6.250 -0.5176 0.03707 0.03053 -0.0292 1.0000 0.0435
-6.000 -0.5056 0.03408 0.02716 -0.0277 1.0000 0.0433
-5.750 -0.4995 0.03246 0.02512 -0.0247 1.0000 0.0442
-5.500 -0.4925 0.03009 0.02245 -0.0219 1.0000 0.0445
-5.250 -0.4826 0.02757 0.01969 -0.0196 1.0000 0.0455
-5.000 -0.4693 0.02561 0.01755 -0.0175 1.0000 0.0469
-4.750 -0.4534 0.02399 0.01575 -0.0156 1.0000 0.0478
-4.500 -0.4297 0.02235 0.01394 -0.0149 0.9980 0.0510
-4.250 -0.3899 0.02049 0.01202 -0.0173 0.9905 0.0613
-4.000 -0.3500 0.01867 0.01026 -0.0196 0.9832 0.0856
-3.750 -0.3188 0.01628 0.00890 -0.0208 0.9744 0.2357
-3.500 -0.2820 0.01561 0.00872 -0.0231 0.9655 0.3730
-3.250 -0.2414 0.01522 0.00864 -0.0256 0.9575 0.4730
-3.000 -0.2081 0.01486 0.00854 -0.0265 0.9477 0.5574
-2.750 -0.1728 0.01450 0.00847 -0.0273 0.9390 0.6474
-2.500 -0.1349 0.01418 0.00843 -0.0280 0.9306 0.7467
-2.250 -0.0877 0.01405 0.00846 -0.0299 0.9230 0.8488
-2.000 -0.0135 0.01412 0.00833 -0.0370 0.9181 0.9234
-1.750 0.0637 0.01415 0.00808 -0.0455 0.9119 0.9646
-1.500 0.1405 0.01388 0.00755 -0.0548 0.9038 0.9990
-1.250 0.1565 0.01393 0.00744 -0.0532 0.8883 1.0000
-1.000 0.1709 0.01404 0.00742 -0.0509 0.8735 1.0000
-0.750 0.1863 0.01419 0.00743 -0.0487 0.8593 1.0000
-0.500 0.2029 0.01436 0.00746 -0.0465 0.8455 1.0000
-0.250 0.2206 0.01452 0.00751 -0.0444 0.8318 1.0000
0.000 0.2390 0.01467 0.00756 -0.0424 0.8182 1.0000
0.250 0.2581 0.01482 0.00761 -0.0405 0.8048 1.0000
0.500 0.2778 0.01496 0.00766 -0.0386 0.7914 1.0000
0.750 0.2980 0.01508 0.00770 -0.0368 0.7779 1.0000
1.000 0.3187 0.01519 0.00774 -0.0350 0.7644 1.0000
1.250 0.3397 0.01528 0.00777 -0.0332 0.7509 1.0000
1.500 0.3612 0.01536 0.00778 -0.0315 0.7372 1.0000
1.750 0.3831 0.01542 0.00778 -0.0299 0.7234 1.0000
2.000 0.4053 0.01546 0.00777 -0.0282 0.7092 1.0000
2.250 0.4279 0.01550 0.00777 -0.0267 0.6948 1.0000
2.500 0.4508 0.01552 0.00774 -0.0252 0.6800 1.0000
2.750 0.4741 0.01552 0.00770 -0.0237 0.6648 1.0000
3.000 0.4977 0.01553 0.00765 -0.0223 0.6493 1.0000
3.250 0.5215 0.01552 0.00762 -0.0209 0.6335 1.0000
3.500 0.5456 0.01552 0.00755 -0.0196 0.6175 1.0000
3.750 0.5702 0.01562 0.00766 -0.0187 0.5982 1.0000
4.000 0.5948 0.01568 0.00768 -0.0176 0.5797 1.0000
4.250 0.6194 0.01574 0.00769 -0.0164 0.5616 1.0000
4.500 0.6443 0.01590 0.00786 -0.0156 0.5407 1.0000
4.750 0.6691 0.01606 0.00795 -0.0146 0.5206 1.0000
5.000 0.6939 0.01629 0.00816 -0.0138 0.4992 1.0000
5.250 0.7186 0.01655 0.00839 -0.0130 0.4779 1.0000
5.500 0.7433 0.01689 0.00872 -0.0123 0.4554 1.0000
5.750 0.7678 0.01725 0.00898 -0.0115 0.4339 1.0000
6.000 0.7920 0.01768 0.00944 -0.0108 0.4102 1.0000
6.250 0.8161 0.01816 0.00989 -0.0101 0.3880 1.0000
6.500 0.8399 0.01867 0.01038 -0.0095 0.3648 1.0000
6.750 0.8634 0.01925 0.01097 -0.0088 0.3416 1.0000
7.000 0.8867 0.01986 0.01148 -0.0081 0.3201 1.0000
7.250 0.9093 0.02054 0.01223 -0.0074 0.2969 1.0000
7.500 0.9318 0.02127 0.01293 -0.0067 0.2762 1.0000
7.750 0.9536 0.02204 0.01377 -0.0060 0.2549 1.0000
8.000 0.9754 0.02288 0.01450 -0.0053 0.2358 1.0000
8.250 0.9959 0.02378 0.01553 -0.0045 0.2161 1.0000
8.500 1.0162 0.02471 0.01647 -0.0036 0.1977 1.0000
8.750 1.0361 0.02576 0.01743 -0.0028 0.1805 1.0000
9.000 1.0537 0.02686 0.01872 -0.0018 0.1627 1.0000
9.250 1.0706 0.02801 0.01995 -0.0008 0.1455 1.0000
9.500 1.0864 0.02928 0.02122 0.0003 0.1293 1.0000
9.750 1.1007 0.03068 0.02258 0.0015 0.1141 1.0000
10.000 1.1143 0.03242 0.02427 0.0027 0.0998 1.0000
10.250 1.1249 0.03402 0.02599 0.0041 0.0877 1.0000
10.500 1.1350 0.03605 0.02828 0.0058 0.0780 1.0000
10.750 1.1437 0.03832 0.03070 0.0072 0.0697 1.0000
11.000 1.1576 0.04100 0.03323 0.0081 0.0623 1.0000
11.250 1.1580 0.04339 0.03615 0.0103 0.0582 1.0000
11.500 1.1584 0.04511 0.03796 0.0121 0.0534 1.0000
11.750 1.1611 0.04867 0.04162 0.0134 0.0500 1.0000
12.000 1.1502 0.05167 0.04499 0.0151 0.0485 1.0000
12.250 1.1384 0.05502 0.04865 0.0160 0.0467 1.0000
12.500 1.1284 0.05840 0.05225 0.0162 0.0448 1.0000
12.750 1.1180 0.06200 0.05603 0.0159 0.0435 1.0000
13.000 1.1181 0.06538 0.05933 0.0157 0.0406 1.0000
13.250 1.1006 0.07084 0.06500 0.0143 0.0402 1.0000
13.500 1.0817 0.07628 0.07067 0.0121 0.0401 1.0000
13.750 1.0619 0.08197 0.07660 0.0090 0.0404 1.0000
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Polar data table (+)
Polar graphs
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