MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 100,000 Max Cl/Cd: 44.81 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh64-il-100000.txt Download as CSV file: xf-mh64-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 64 8.59%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4681 0.11689 0.11261 0.0140 1.0000 0.0864
-9.750 -0.4746 0.11318 0.10893 0.0110 1.0000 0.0900
-9.500 -0.4949 0.10971 0.10554 0.0053 1.0000 0.0915
-9.250 -0.4743 0.10410 0.09993 0.0076 1.0000 0.0939
-9.000 -0.4637 0.10021 0.09604 0.0078 1.0000 0.0972
-8.750 -0.4646 0.09608 0.09195 0.0059 1.0000 0.1014
-8.500 -0.4931 0.09206 0.08803 -0.0014 1.0000 0.1047
-8.250 -0.4755 0.08669 0.08267 0.0006 1.0000 0.1070
-8.000 -0.4647 0.08284 0.07884 0.0011 1.0000 0.1107
-7.750 -0.5642 0.08545 0.08128 -0.0038 1.0000 0.1067
-7.500 -0.5495 0.08225 0.07809 -0.0020 1.0000 0.1103
-7.250 -0.4776 0.06932 0.06550 -0.0056 1.0000 0.1226
-7.000 -0.5508 0.07245 0.06833 -0.0123 1.0000 0.1211
-6.750 -0.5398 0.06876 0.06464 -0.0132 1.0000 0.1257
-6.500 -0.5361 0.06366 0.05946 -0.0179 1.0000 0.1348
-6.250 -0.5288 0.05925 0.05490 -0.0215 1.0000 0.1468
-6.000 -0.5139 0.04010 0.03426 -0.0283 1.0000 0.0473
-5.750 -0.4925 0.03554 0.02873 -0.0275 1.0000 0.0394
-5.500 -0.4728 0.03149 0.02433 -0.0271 1.0000 0.0378
-5.250 -0.4505 0.02840 0.02079 -0.0264 1.0000 0.0371
-5.000 -0.4265 0.02637 0.01828 -0.0255 1.0000 0.0391
-4.750 -0.4037 0.02386 0.01542 -0.0246 1.0000 0.0413
-4.500 -0.3819 0.02168 0.01317 -0.0236 1.0000 0.0436
-4.250 -0.3617 0.02002 0.01144 -0.0219 1.0000 0.0470
-4.000 -0.3438 0.01873 0.00999 -0.0198 1.0000 0.0516
-3.750 -0.3287 0.01740 0.00872 -0.0177 1.0000 0.0663
-3.500 -0.3166 0.01497 0.00708 -0.0152 1.0000 0.1617
-3.250 -0.3041 0.01373 0.00680 -0.0131 1.0000 0.3649
-3.000 -0.2888 0.01335 0.00670 -0.0111 1.0000 0.4534
-2.750 -0.2730 0.01298 0.00663 -0.0091 1.0000 0.5368
-2.500 -0.2565 0.01261 0.00656 -0.0069 1.0000 0.6233
-2.250 -0.2402 0.01224 0.00655 -0.0042 1.0000 0.7278
-2.000 -0.1713 0.01188 0.00645 -0.0102 1.0000 0.9476
-1.750 -0.1143 0.01197 0.00614 -0.0171 0.9972 1.0000
-1.500 -0.0608 0.01215 0.00601 -0.0231 0.9857 1.0000
-1.250 -0.0073 0.01231 0.00590 -0.0288 0.9746 1.0000
-1.000 0.0487 0.01242 0.00581 -0.0348 0.9642 1.0000
-0.750 0.1050 0.01246 0.00570 -0.0406 0.9538 1.0000
-0.500 0.1534 0.01249 0.00559 -0.0447 0.9410 1.0000
-0.250 0.1916 0.01257 0.00559 -0.0466 0.9254 1.0000
0.000 0.2223 0.01270 0.00565 -0.0469 0.9086 1.0000
0.250 0.2480 0.01286 0.00574 -0.0461 0.8916 1.0000
0.500 0.2701 0.01303 0.00583 -0.0443 0.8751 1.0000
0.750 0.2898 0.01321 0.00596 -0.0422 0.8576 1.0000
1.000 0.3094 0.01338 0.00607 -0.0400 0.8399 1.0000
1.250 0.3291 0.01351 0.00615 -0.0377 0.8230 1.0000
1.500 0.3489 0.01362 0.00622 -0.0353 0.8067 1.0000
1.750 0.3698 0.01374 0.00631 -0.0334 0.7884 1.0000
2.000 0.3910 0.01382 0.00635 -0.0314 0.7702 1.0000
2.250 0.4124 0.01386 0.00634 -0.0293 0.7528 1.0000
2.500 0.4348 0.01393 0.00639 -0.0276 0.7329 1.0000
2.750 0.4575 0.01395 0.00643 -0.0258 0.7132 1.0000
3.000 0.4807 0.01400 0.00646 -0.0243 0.6921 1.0000
3.250 0.5041 0.01401 0.00643 -0.0226 0.6708 1.0000
3.500 0.5280 0.01407 0.00648 -0.0213 0.6464 1.0000
3.750 0.5522 0.01414 0.00656 -0.0200 0.6212 1.0000
4.000 0.5765 0.01424 0.00662 -0.0187 0.5945 1.0000
4.250 0.6009 0.01438 0.00673 -0.0175 0.5661 1.0000
4.500 0.6254 0.01458 0.00687 -0.0164 0.5365 1.0000
4.750 0.6498 0.01486 0.00706 -0.0154 0.5062 1.0000
5.000 0.6742 0.01521 0.00744 -0.0145 0.4725 1.0000
5.250 0.6983 0.01563 0.00777 -0.0136 0.4393 1.0000
5.500 0.7224 0.01612 0.00822 -0.0128 0.4041 1.0000
5.750 0.7460 0.01669 0.00867 -0.0120 0.3698 1.0000
6.000 0.7694 0.01732 0.00927 -0.0113 0.3331 1.0000
6.250 0.7924 0.01804 0.00991 -0.0106 0.2979 1.0000
6.500 0.8149 0.01883 0.01061 -0.0098 0.2634 1.0000
6.750 0.8370 0.01971 0.01153 -0.0091 0.2298 1.0000
7.000 0.8585 0.02069 0.01244 -0.0084 0.1973 1.0000
7.250 0.8788 0.02182 0.01345 -0.0076 0.1658 1.0000
7.500 0.8985 0.02312 0.01477 -0.0067 0.1341 1.0000
7.750 0.9168 0.02472 0.01629 -0.0057 0.1054 1.0000
8.000 0.9343 0.02647 0.01803 -0.0046 0.0818 1.0000
8.250 0.9531 0.02877 0.02036 -0.0033 0.0670 1.0000
8.500 0.9706 0.03089 0.02258 -0.0022 0.0549 1.0000
8.750 0.9886 0.03420 0.02608 -0.0010 0.0480 1.0000
9.000 1.0038 0.03636 0.02835 0.0000 0.0406 1.0000
9.250 1.0153 0.04032 0.03278 0.0014 0.0374 1.0000
9.500 1.0234 0.04418 0.03718 0.0030 0.0361 1.0000
9.750 1.0251 0.04833 0.04184 0.0046 0.0355 1.0000
10.000 1.0208 0.05256 0.04651 0.0060 0.0353 1.0000
10.250 1.0100 0.05665 0.05096 0.0072 0.0348 1.0000
10.500 0.9934 0.06052 0.05508 0.0085 0.0353 1.0000
10.750 0.9749 0.06472 0.05949 0.0082 0.0357 1.0000
11.000 0.9542 0.06968 0.06464 0.0063 0.0360 1.0000
11.250 0.9348 0.07537 0.07046 0.0031 0.0367 1.0000
11.500 0.9128 0.08222 0.07744 -0.0017 0.0370 1.0000
11.750 0.8945 0.08959 0.08489 -0.0067 0.0378 1.0000
12.000 0.8759 0.09788 0.09322 -0.0122 0.0384 1.0000
12.250 0.8632 0.10563 0.10096 -0.0162 0.0391 1.0000
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Polar data table (+)
Polar graphs
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