MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 200,000 Max Cl/Cd: 56.28 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh108-il-200000.txt Download as CSV file: xf-mh108-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 108 11.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7425 0.09011 0.08662 0.0004 1.0000 0.0224
-12.000 -0.7748 0.07842 0.07486 -0.0079 1.0000 0.0214
-11.750 -0.8075 0.06793 0.06419 -0.0165 1.0000 0.0209
-11.500 -0.8936 0.05312 0.04858 -0.0260 1.0000 0.0180
-11.250 -0.9071 0.04974 0.04505 -0.0256 1.0000 0.0183
-11.000 -0.9152 0.04727 0.04247 -0.0241 1.0000 0.0186
-10.750 -0.9346 0.04378 0.03858 -0.0206 1.0000 0.0182
-10.500 -0.9313 0.04209 0.03684 -0.0188 1.0000 0.0189
-10.250 -0.9282 0.03991 0.03447 -0.0169 1.0000 0.0193
-10.000 -0.9189 0.03840 0.03285 -0.0153 1.0000 0.0204
-9.750 -0.9132 0.03579 0.02992 -0.0132 1.0000 0.0207
-9.500 -0.9035 0.03343 0.02724 -0.0112 1.0000 0.0214
-9.250 -0.8909 0.03105 0.02453 -0.0094 1.0000 0.0218
-9.000 -0.8753 0.02901 0.02221 -0.0078 1.0000 0.0224
-8.750 -0.8572 0.02735 0.02030 -0.0063 1.0000 0.0231
-8.500 -0.8420 0.02467 0.01752 -0.0048 1.0000 0.0244
-8.250 -0.8235 0.02333 0.01616 -0.0034 1.0000 0.0263
-8.000 -0.8035 0.02221 0.01493 -0.0021 1.0000 0.0293
-7.750 -0.7859 0.02080 0.01351 -0.0006 1.0000 0.0338
-7.500 -0.7660 0.01970 0.01232 0.0008 1.0000 0.0401
-7.250 -0.7470 0.01855 0.01117 0.0023 1.0000 0.0508
-7.000 -0.7274 0.01755 0.01025 0.0036 1.0000 0.0654
-6.750 -0.7058 0.01685 0.00959 0.0046 1.0000 0.0808
-6.500 -0.6833 0.01628 0.00903 0.0056 1.0000 0.0967
-6.250 -0.6605 0.01578 0.00851 0.0065 1.0000 0.1132
-6.000 -0.6386 0.01518 0.00797 0.0075 1.0000 0.1299
-5.750 -0.6167 0.01463 0.00751 0.0086 1.0000 0.1473
-5.500 -0.5945 0.01414 0.00707 0.0096 1.0000 0.1661
-5.250 -0.5726 0.01367 0.00666 0.0107 1.0000 0.1866
-5.000 -0.5515 0.01321 0.00632 0.0119 1.0000 0.2085
-4.750 -0.5310 0.01279 0.00599 0.0132 1.0000 0.2322
-4.500 -0.5114 0.01242 0.00573 0.0147 1.0000 0.2575
-4.250 -0.4775 0.01198 0.00546 0.0130 0.9879 0.2911
-4.000 -0.4318 0.01152 0.00517 0.0092 0.9587 0.3350
-3.750 -0.3881 0.01110 0.00488 0.0061 0.9224 0.3813
-3.500 -0.3545 0.01080 0.00465 0.0053 0.8810 0.4252
-3.250 -0.3306 0.01061 0.00447 0.0067 0.8414 0.4663
-3.000 -0.3090 0.01043 0.00432 0.0084 0.8076 0.5086
-2.750 -0.2874 0.01026 0.00418 0.0102 0.7775 0.5523
-2.500 -0.2654 0.01009 0.00407 0.0118 0.7498 0.5994
-2.250 -0.2430 0.00992 0.00399 0.0135 0.7243 0.6489
-2.000 -0.2201 0.00980 0.00392 0.0151 0.7013 0.6995
-1.750 -0.1959 0.00971 0.00390 0.0165 0.6783 0.7494
-1.500 -0.1698 0.00970 0.00391 0.0176 0.6573 0.7961
-1.250 -0.1406 0.00976 0.00396 0.0181 0.6357 0.8380
-1.000 -0.1067 0.00993 0.00405 0.0177 0.6157 0.8714
-0.750 -0.0702 0.01016 0.00416 0.0167 0.5954 0.8981
-0.500 -0.0298 0.01043 0.00429 0.0148 0.5749 0.9173
-0.250 0.0117 0.01073 0.00442 0.0126 0.5563 0.9325
0.000 0.0559 0.01104 0.00454 0.0098 0.5385 0.9446
0.250 0.0993 0.01128 0.00465 0.0070 0.5205 0.9565
0.500 0.1433 0.01151 0.00474 0.0039 0.5037 0.9677
0.750 0.1917 0.01168 0.00477 -0.0002 0.4881 0.9764
1.000 0.2377 0.01180 0.00476 -0.0039 0.4736 0.9857
1.250 0.2846 0.01186 0.00471 -0.0079 0.4600 0.9945
1.500 0.3249 0.01186 0.00459 -0.0107 0.4488 1.0000
1.750 0.3467 0.01189 0.00458 -0.0098 0.4391 1.0000
2.000 0.3689 0.01197 0.00461 -0.0089 0.4305 1.0000
2.250 0.3914 0.01206 0.00462 -0.0081 0.4224 1.0000
2.500 0.4143 0.01216 0.00471 -0.0073 0.4141 1.0000
2.750 0.4372 0.01230 0.00476 -0.0065 0.4069 1.0000
3.000 0.4605 0.01241 0.00490 -0.0057 0.3990 1.0000
3.250 0.4837 0.01259 0.00499 -0.0049 0.3922 1.0000
3.500 0.5071 0.01273 0.00519 -0.0041 0.3847 1.0000
3.750 0.5305 0.01292 0.00531 -0.0033 0.3781 1.0000
4.000 0.5540 0.01310 0.00553 -0.0025 0.3709 1.0000
4.250 0.5776 0.01329 0.00568 -0.0017 0.3643 1.0000
4.500 0.6012 0.01351 0.00595 -0.0009 0.3575 1.0000
4.750 0.6249 0.01370 0.00614 -0.0001 0.3506 1.0000
5.000 0.6485 0.01395 0.00639 0.0007 0.3441 1.0000
5.250 0.6721 0.01415 0.00664 0.0015 0.3369 1.0000
5.500 0.6958 0.01442 0.00690 0.0022 0.3305 1.0000
5.750 0.7194 0.01462 0.00716 0.0031 0.3229 1.0000
6.000 0.7430 0.01490 0.00743 0.0038 0.3163 1.0000
6.250 0.7665 0.01510 0.00773 0.0047 0.3084 1.0000
6.500 0.7899 0.01538 0.00801 0.0055 0.3011 1.0000
6.750 0.8132 0.01558 0.00828 0.0063 0.2928 1.0000
7.000 0.8363 0.01585 0.00861 0.0072 0.2848 1.0000
7.250 0.8595 0.01606 0.00883 0.0080 0.2763 1.0000
7.500 0.8822 0.01632 0.00922 0.0089 0.2671 1.0000
7.750 0.9049 0.01659 0.00948 0.0098 0.2582 1.0000
8.000 0.9273 0.01679 0.00977 0.0108 0.2480 1.0000
8.250 0.9493 0.01706 0.01014 0.0117 0.2372 1.0000
8.500 0.9711 0.01734 0.01047 0.0127 0.2262 1.0000
8.750 0.9924 0.01765 0.01083 0.0137 0.2150 1.0000
9.000 1.0131 0.01800 0.01119 0.0148 0.2031 1.0000
9.250 1.0333 0.01839 0.01165 0.0159 0.1904 1.0000
9.500 1.0528 0.01887 0.01218 0.0170 0.1774 1.0000
9.750 1.0714 0.01944 0.01280 0.0182 0.1646 1.0000
10.000 1.0891 0.02009 0.01350 0.0195 0.1523 1.0000
10.250 1.1058 0.02083 0.01431 0.0208 0.1406 1.0000
10.500 1.1211 0.02166 0.01517 0.0222 0.1294 1.0000
10.750 1.1346 0.02257 0.01610 0.0238 0.1184 1.0000
11.000 1.1458 0.02360 0.01711 0.0255 0.1077 1.0000
11.250 1.1569 0.02457 0.01817 0.0271 0.0970 1.0000
11.500 1.1653 0.02568 0.01937 0.0290 0.0870 1.0000
11.750 1.1676 0.02701 0.02074 0.0314 0.0784 1.0000
12.000 1.1633 0.02856 0.02230 0.0341 0.0720 1.0000
12.250 1.1608 0.03040 0.02425 0.0357 0.0654 1.0000
12.500 1.1533 0.03306 0.02694 0.0362 0.0602 1.0000
12.750 1.1490 0.03591 0.02992 0.0359 0.0551 1.0000
13.000 1.1424 0.03931 0.03338 0.0349 0.0508 1.0000
13.250 1.1303 0.04342 0.03749 0.0337 0.0475 1.0000
13.500 1.1256 0.04702 0.04126 0.0323 0.0440 1.0000
13.750 1.1168 0.05114 0.04546 0.0306 0.0411 1.0000
14.000 1.1035 0.05568 0.04998 0.0290 0.0387 1.0000
14.250 1.0950 0.05994 0.05436 0.0274 0.0361 1.0000
14.500 1.0869 0.06416 0.05870 0.0257 0.0341 1.0000
14.750 1.0782 0.06853 0.06313 0.0239 0.0324 1.0000
15.000 1.0681 0.07301 0.06762 0.0221 0.0306 1.0000
15.250 1.0608 0.07720 0.07185 0.0208 0.0288 1.0000
15.500 1.0528 0.08204 0.07684 0.0185 0.0273 1.0000
15.750 1.0469 0.08652 0.08143 0.0166 0.0261 1.0000
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Polar data table (+)
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