MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 112 Airfoil (mh112-il) Reynolds number: 100,000 Max Cl/Cd: 48.6 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh112-il-100000-n5.txt Download as CSV file: xf-mh112-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.1542 0.09575 0.09006 -0.1358 0.8845 0.0391
-9.250 0.1728 0.09289 0.08718 -0.1378 0.8806 0.0380
-8.750 0.1777 0.08550 0.07977 -0.1414 0.8677 0.0345
-8.500 0.1885 0.08247 0.07673 -0.1433 0.8626 0.0340
-8.250 0.2010 0.07895 0.07318 -0.1463 0.8587 0.0335
-8.000 0.1950 0.07691 0.07119 -0.1449 0.8494 0.0332
-7.500 0.1989 0.06948 0.06375 -0.1489 0.8383 0.0323
-7.250 0.1806 0.06711 0.06145 -0.1464 0.8280 0.0320
-7.000 0.1316 0.05657 0.05088 -0.1513 0.8193 0.0305
-6.750 0.1044 0.05221 0.04652 -0.1522 0.8076 0.0302
-6.500 0.0968 0.04235 0.03603 -0.1650 0.8016 0.0298
-6.250 0.0852 0.03945 0.03275 -0.1637 0.7910 0.0301
-6.000 0.1084 0.03592 0.02868 -0.1672 0.7867 0.0310
-5.750 0.1405 0.03435 0.02693 -0.1696 0.7840 0.0325
-5.500 0.1607 0.03248 0.02466 -0.1701 0.7786 0.0337
-5.250 0.1769 0.03092 0.02269 -0.1694 0.7717 0.0348
-5.000 0.2075 0.02970 0.02135 -0.1706 0.7681 0.0359
-4.750 0.2426 0.02831 0.01973 -0.1723 0.7655 0.0375
-4.500 0.2804 0.02692 0.01808 -0.1744 0.7633 0.0397
-4.250 0.2851 0.02697 0.01815 -0.1709 0.7541 0.0413
-4.000 0.3155 0.02622 0.01728 -0.1716 0.7501 0.0453
-3.750 0.3506 0.02535 0.01629 -0.1730 0.7472 0.0498
-3.500 0.3889 0.02450 0.01536 -0.1750 0.7448 0.0563
-3.250 0.3981 0.02459 0.01545 -0.1721 0.7365 0.0619
-3.000 0.4271 0.02412 0.01499 -0.1726 0.7320 0.0722
-2.750 0.4624 0.02350 0.01436 -0.1740 0.7288 0.0890
-2.500 0.5011 0.02286 0.01373 -0.1761 0.7263 0.1136
-2.250 0.5129 0.02307 0.01399 -0.1736 0.7185 0.1324
-2.000 0.5403 0.02284 0.01383 -0.1737 0.7136 0.1613
-1.750 0.5751 0.02243 0.01347 -0.1750 0.7102 0.1981
-1.500 0.6135 0.02198 0.01305 -0.1769 0.7076 0.2413
-1.250 0.6237 0.02234 0.01354 -0.1741 0.6997 0.2702
-1.000 0.6504 0.02227 0.01353 -0.1740 0.6947 0.3118
-0.750 0.6849 0.02199 0.01331 -0.1751 0.6913 0.3606
-0.500 0.7231 0.02167 0.01301 -0.1767 0.6887 0.4123
-0.250 0.7288 0.02225 0.01372 -0.1731 0.6800 0.4426
0.000 0.7566 0.02222 0.01372 -0.1729 0.6754 0.4860
0.250 0.7917 0.02200 0.01350 -0.1739 0.6721 0.5312
0.500 0.8153 0.02213 0.01365 -0.1730 0.6670 0.5689
0.750 0.8283 0.02251 0.01411 -0.1705 0.6598 0.6009
1.000 0.8583 0.02238 0.01400 -0.1705 0.6556 0.6407
1.250 0.8936 0.02209 0.01370 -0.1713 0.6525 0.6839
1.500 0.8968 0.02266 0.01439 -0.1672 0.6444 0.7179
1.750 0.9165 0.02264 0.01444 -0.1653 0.6391 0.7663
2.000 0.9426 0.02223 0.01410 -0.1641 0.6354 0.8409
2.250 0.9508 0.02247 0.01439 -0.1607 0.6283 1.0000
2.500 0.9724 0.02281 0.01462 -0.1599 0.6219 1.0000
2.750 1.0108 0.02265 0.01429 -0.1616 0.6177 1.0000
3.000 1.0286 0.02309 0.01466 -0.1602 0.6111 1.0000
3.250 1.0461 0.02353 0.01503 -0.1587 0.6040 1.0000
3.500 1.0828 0.02338 0.01475 -0.1600 0.5995 1.0000
3.750 1.0971 0.02394 0.01527 -0.1581 0.5926 1.0000
4.000 1.1154 0.02437 0.01565 -0.1567 0.5857 1.0000
4.250 1.1514 0.02422 0.01538 -0.1579 0.5811 1.0000
4.500 1.1606 0.02498 0.01614 -0.1553 0.5736 1.0000
4.750 1.1808 0.02536 0.01648 -0.1542 0.5670 1.0000
5.000 1.2173 0.02518 0.01620 -0.1554 0.5625 1.0000
5.250 1.2198 0.02621 0.01728 -0.1520 0.5542 1.0000
5.500 1.2433 0.02647 0.01749 -0.1514 0.5479 1.0000
5.750 1.2786 0.02631 0.01722 -0.1524 0.5431 1.0000
6.000 1.2756 0.02763 0.01862 -0.1484 0.5340 1.0000
6.250 1.3039 0.02768 0.01862 -0.1484 0.5282 1.0000
6.500 1.3168 0.02843 0.01937 -0.1466 0.5210 1.0000
6.750 1.3300 0.02915 0.02010 -0.1448 0.5133 1.0000
7.000 1.3653 0.02889 0.01974 -0.1457 0.5081 1.0000
7.250 1.3599 0.03052 0.02149 -0.1418 0.4987 1.0000
7.500 1.3856 0.03065 0.02157 -0.1415 0.4923 1.0000
7.750 1.3924 0.03179 0.02275 -0.1392 0.4840 1.0000
8.000 1.4079 0.03247 0.02342 -0.1379 0.4764 1.0000
8.250 1.4261 0.03303 0.02398 -0.1368 0.4693 1.0000
8.500 1.4313 0.03432 0.02533 -0.1346 0.4604 1.0000
8.750 1.4578 0.03439 0.02533 -0.1343 0.4539 1.0000
9.000 1.4544 0.03631 0.02735 -0.1314 0.4443 1.0000
9.250 1.4812 0.03631 0.02729 -0.1312 0.4377 1.0000
9.500 1.4761 0.03846 0.02956 -0.1284 0.4279 1.0000
9.750 1.4985 0.03874 0.02979 -0.1278 0.4210 1.0000
10.000 1.4967 0.04080 0.03195 -0.1254 0.4116 1.0000
10.250 1.5150 0.04137 0.03250 -0.1246 0.4043 1.0000
10.500 1.5160 0.04335 0.03455 -0.1226 0.3954 1.0000
10.750 1.5304 0.04423 0.03542 -0.1215 0.3877 1.0000
11.000 1.5343 0.04608 0.03734 -0.1199 0.3794 1.0000
11.250 1.5448 0.04735 0.03863 -0.1188 0.3716 1.0000
11.500 1.5518 0.04899 0.04031 -0.1175 0.3638 1.0000
11.750 1.5581 0.05072 0.04208 -0.1162 0.3558 1.0000
12.000 1.5699 0.05197 0.04333 -0.1152 0.3487 1.0000
12.250 1.5708 0.05431 0.04578 -0.1139 0.3406 1.0000
12.500 1.5891 0.05493 0.04633 -0.1132 0.3343 1.0000
12.750 1.5837 0.05804 0.04960 -0.1118 0.3261 1.0000
13.000 1.5988 0.05898 0.05050 -0.1111 0.3196 1.0000
13.250 1.5977 0.06178 0.05342 -0.1101 0.3123 1.0000
13.500 1.6041 0.06371 0.05539 -0.1093 0.3053 1.0000
13.750 1.6132 0.06541 0.05711 -0.1085 0.2990 1.0000
14.000 1.6103 0.06855 0.06037 -0.1077 0.2917 1.0000
14.250 1.6270 0.06931 0.06109 -0.1072 0.2859 1.0000
14.500 1.6187 0.07325 0.06521 -0.1065 0.2788 1.0000
14.750 1.6238 0.07549 0.06750 -0.1060 0.2724 1.0000
15.000 1.6303 0.07759 0.06964 -0.1056 0.2665 1.0000
15.250 1.6236 0.08151 0.07370 -0.1053 0.2596 1.0000
15.500 1.6371 0.08266 0.07483 -0.1049 0.2541 1.0000
15.750 1.6273 0.08711 0.07946 -0.1048 0.2476 1.0000
16.000 1.6275 0.09018 0.08262 -0.1048 0.2414 1.0000
16.250 1.6367 0.09196 0.08440 -0.1046 0.2361 1.0000
16.500 1.6229 0.09718 0.08982 -0.1051 0.2295 1.0000
16.750 1.6309 0.09913 0.09179 -0.1050 0.2241 1.0000
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