MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 112 Airfoil (mh112-il) Reynolds number: 500,000 Max Cl/Cd: 119.97 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh112-il-500000.txt Download as CSV file: xf-mh112-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 112 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.2405 0.09474 0.09170 -0.1599 0.8974 0.0252
-10.750 0.2293 0.08904 0.08596 -0.1641 0.8862 0.0269
-10.500 0.2431 0.08659 0.08344 -0.1656 0.8783 0.0270
-10.250 0.2593 0.08549 0.08232 -0.1650 0.8706 0.0274
-10.000 0.2700 0.08344 0.08023 -0.1657 0.8628 0.0277
-9.750 0.2800 0.08140 0.07814 -0.1665 0.8557 0.0282
-9.500 0.2587 0.07518 0.07192 -0.1702 0.8461 0.0306
-9.250 0.2708 0.07324 0.06992 -0.1704 0.8399 0.0308
-9.000 0.2829 0.07215 0.06884 -0.1696 0.8337 0.0311
-8.750 0.2915 0.07037 0.06705 -0.1697 0.8272 0.0314
-8.500 0.3017 0.06860 0.06522 -0.1701 0.8211 0.0320
-8.250 0.3062 0.06646 0.06310 -0.1703 0.8148 0.0328
-8.000 0.1452 0.03745 0.03381 -0.1899 0.7997 0.0268
-7.750 0.1476 0.03491 0.03127 -0.1909 0.7937 0.0273
-7.500 0.1588 0.03328 0.02958 -0.1918 0.7881 0.0275
-7.250 0.1778 0.03246 0.02871 -0.1923 0.7833 0.0280
-7.000 0.2958 0.05158 0.04820 -0.1736 0.7835 0.0364
-6.750 0.1770 0.01841 0.01259 -0.1972 0.7718 0.0199
-6.500 0.2026 0.01740 0.01139 -0.1973 0.7675 0.0200
-6.250 0.2299 0.01642 0.01023 -0.1977 0.7632 0.0201
-6.000 0.2543 0.01550 0.00925 -0.1975 0.7588 0.0203
-5.750 0.2802 0.01477 0.00850 -0.1974 0.7541 0.0206
-5.500 0.3073 0.01423 0.00790 -0.1975 0.7498 0.0209
-5.250 0.3360 0.01379 0.00737 -0.1978 0.7455 0.0215
-5.000 0.3631 0.01337 0.00690 -0.1978 0.7411 0.0222
-4.750 0.3903 0.01298 0.00647 -0.1977 0.7363 0.0231
-4.500 0.4181 0.01249 0.00595 -0.1979 0.7319 0.0243
-4.250 0.4473 0.01220 0.00559 -0.1982 0.7276 0.0259
-4.000 0.4758 0.01187 0.00524 -0.1984 0.7231 0.0281
-3.750 0.5033 0.01158 0.00494 -0.1984 0.7182 0.0315
-3.500 0.5317 0.01130 0.00466 -0.1985 0.7135 0.0379
-3.250 0.5611 0.01104 0.00440 -0.1989 0.7092 0.0511
-3.000 0.5897 0.01084 0.00425 -0.1991 0.7046 0.0701
-2.750 0.6171 0.01065 0.00414 -0.1991 0.6995 0.0897
-2.500 0.6452 0.01049 0.00404 -0.1992 0.6946 0.1122
-2.250 0.6744 0.01038 0.00395 -0.1995 0.6900 0.1390
-2.000 0.7023 0.01026 0.00391 -0.1996 0.6852 0.1695
-1.750 0.7296 0.01013 0.00388 -0.1995 0.6798 0.2041
-1.250 0.7871 0.01000 0.00383 -0.2000 0.6699 0.2788
-1.000 0.8135 0.00991 0.00386 -0.1997 0.6647 0.3146
-0.750 0.8407 0.00986 0.00387 -0.1996 0.6592 0.3508
-0.500 0.8688 0.00984 0.00388 -0.1996 0.6540 0.3891
-0.250 0.8961 0.00983 0.00394 -0.1995 0.6487 0.4270
0.000 0.9222 0.00982 0.00399 -0.1992 0.6426 0.4621
0.250 0.9491 0.00984 0.00403 -0.1989 0.6365 0.4961
0.500 0.9755 0.00989 0.00410 -0.1986 0.6304 0.5266
0.750 1.0009 0.00990 0.00417 -0.1981 0.6239 0.5553
1.000 1.0271 0.00997 0.00423 -0.1977 0.6178 0.5825
1.250 1.0529 0.01003 0.00432 -0.1973 0.6120 0.6096
1.500 1.0779 0.01006 0.00442 -0.1967 0.6058 0.6359
1.750 1.1033 0.01015 0.00450 -0.1962 0.5998 0.6638
2.000 1.1281 0.01022 0.00462 -0.1956 0.5941 0.6933
2.250 1.1520 0.01026 0.00474 -0.1948 0.5879 0.7265
2.500 1.1755 0.01033 0.00486 -0.1939 0.5819 0.7661
2.750 1.1969 0.01035 0.00500 -0.1925 0.5761 0.8174
3.000 1.2094 0.01017 0.00505 -0.1891 0.5701 0.9603
3.250 1.2344 0.01034 0.00514 -0.1886 0.5640 1.0000
3.500 1.2582 0.01052 0.00527 -0.1879 0.5581 1.0000
3.750 1.2801 0.01067 0.00540 -0.1869 0.5516 1.0000
4.000 1.3019 0.01088 0.00553 -0.1858 0.5454 1.0000
4.250 1.3230 0.01107 0.00570 -0.1846 0.5393 1.0000
4.500 1.3435 0.01126 0.00587 -0.1832 0.5327 1.0000
4.750 1.3640 0.01153 0.00606 -0.1820 0.5265 1.0000
5.000 1.3842 0.01172 0.00627 -0.1807 0.5202 1.0000
5.250 1.4035 0.01197 0.00649 -0.1792 0.5133 1.0000
5.500 1.4227 0.01227 0.00673 -0.1777 0.5068 1.0000
5.750 1.4417 0.01251 0.00699 -0.1763 0.4999 1.0000
6.000 1.4595 0.01283 0.00726 -0.1746 0.4930 1.0000
6.250 1.4778 0.01315 0.00757 -0.1731 0.4862 1.0000
6.500 1.4951 0.01348 0.00789 -0.1714 0.4787 1.0000
6.750 1.5110 0.01390 0.00826 -0.1695 0.4715 1.0000
7.000 1.5284 0.01424 0.00863 -0.1679 0.4641 1.0000
7.250 1.5427 0.01474 0.00907 -0.1659 0.4562 1.0000
7.500 1.5591 0.01515 0.00952 -0.1642 0.4485 1.0000
7.750 1.5730 0.01569 0.01002 -0.1622 0.4403 1.0000
8.000 1.5875 0.01623 0.01056 -0.1604 0.4322 1.0000
8.250 1.6005 0.01685 0.01116 -0.1584 0.4235 1.0000
8.500 1.6138 0.01749 0.01179 -0.1565 0.4150 1.0000
8.750 1.6254 0.01822 0.01250 -0.1544 0.4059 1.0000
9.000 1.6378 0.01895 0.01324 -0.1525 0.3969 1.0000
9.250 1.6474 0.01985 0.01410 -0.1502 0.3874 1.0000
9.500 1.6596 0.02066 0.01492 -0.1485 0.3782 1.0000
9.750 1.6670 0.02176 0.01596 -0.1461 0.3689 1.0000
10.000 1.6793 0.02263 0.01686 -0.1445 0.3597 1.0000
10.250 1.6860 0.02385 0.01804 -0.1422 0.3509 1.0000
10.500 1.6973 0.02485 0.01905 -0.1406 0.3420 1.0000
10.750 1.7039 0.02617 0.02034 -0.1385 0.3338 1.0000
11.000 1.7146 0.02728 0.02147 -0.1370 0.3255 1.0000
11.250 1.7201 0.02876 0.02291 -0.1350 0.3177 1.0000
11.500 1.7314 0.02989 0.02408 -0.1336 0.3103 1.0000
11.750 1.7364 0.03150 0.02566 -0.1318 0.3029 1.0000
12.000 1.7472 0.03273 0.02694 -0.1305 0.2961 1.0000
12.250 1.7539 0.03431 0.02851 -0.1289 0.2892 1.0000
12.500 1.7614 0.03585 0.03007 -0.1275 0.2827 1.0000
12.750 1.7698 0.03737 0.03162 -0.1263 0.2760 1.0000
13.000 1.7736 0.03930 0.03352 -0.1247 0.2695 1.0000
13.250 1.7838 0.04075 0.03504 -0.1237 0.2636 1.0000
13.500 1.7895 0.04261 0.03690 -0.1225 0.2570 1.0000
13.750 1.7947 0.04454 0.03885 -0.1213 0.2512 1.0000
14.000 1.8030 0.04624 0.04061 -0.1204 0.2450 1.0000
14.250 1.8048 0.04860 0.04295 -0.1191 0.2387 1.0000
14.500 1.8131 0.05036 0.04478 -0.1183 0.2332 1.0000
14.750 1.8170 0.05262 0.04706 -0.1174 0.2269 1.0000
15.000 1.8195 0.05502 0.04947 -0.1165 0.2211 1.0000
15.250 1.8257 0.05712 0.05164 -0.1158 0.2153 1.0000
15.500 1.8264 0.05982 0.05433 -0.1150 0.2093 1.0000
15.750 1.8310 0.06216 0.05673 -0.1144 0.2038 1.0000
16.000 1.8332 0.06479 0.05940 -0.1139 0.1977 1.0000
16.250 1.8329 0.06776 0.06238 -0.1133 0.1922 1.0000
16.500 1.8371 0.07024 0.06493 -0.1129 0.1867 1.0000
16.750 1.8357 0.07343 0.06813 -0.1125 0.1812 1.0000
17.000 1.8377 0.07626 0.07102 -0.1123 0.1763 1.0000
17.250 1.8388 0.07922 0.07403 -0.1121 0.1709 1.0000
17.500 1.8343 0.08293 0.07774 -0.1120 0.1657 1.0000
17.750 1.8386 0.08554 0.08045 -0.1120 0.1610 1.0000
18.000 1.8357 0.08914 0.08407 -0.1120 0.1561 1.0000
18.250 1.8342 0.09256 0.08753 -0.1122 0.1515 1.0000
18.500 1.8347 0.09577 0.09082 -0.1124 0.1469 1.0000
18.750 1.8303 0.09966 0.09472 -0.1128 0.1423 1.0000
19.000 1.8300 0.10299 0.09812 -0.1132 0.1382 1.0000
19.250 1.8288 0.10645 0.10165 -0.1137 0.1339 1.0000
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