MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 115 11.06% (mh115-il) Reynolds number: 200,000 Max Cl/Cd: 91.54 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh115-il-200000.txt Download as CSV file: xf-mh115-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 115 11.06%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2204 0.10544 0.10220 -0.0518 0.9847 0.0368
-8.250 -0.2136 0.10156 0.09835 -0.0608 0.9769 0.0378
-8.000 -0.1985 0.09703 0.09382 -0.0697 0.9723 0.0380
-7.750 -0.1780 0.09277 0.08956 -0.0666 0.9700 0.0391
-7.500 -0.1607 0.08964 0.08643 -0.0686 0.9644 0.0402
-7.250 -0.1402 0.08588 0.08266 -0.0733 0.9607 0.0418
-7.000 -0.1301 0.08262 0.07941 -0.0766 0.9522 0.0432
-6.750 -0.1194 0.07721 0.07403 -0.0901 0.9395 0.0460
-6.500 -0.0979 0.07056 0.06737 -0.0997 0.9341 0.0468
-6.250 -0.0749 0.06811 0.06491 -0.0984 0.9326 0.0483
-6.000 -0.0613 0.06528 0.06208 -0.1004 0.9236 0.0498
-5.750 -0.0277 0.05965 0.05639 -0.1113 0.9195 0.0534
-5.250 0.0452 0.03376 0.02928 -0.1437 0.9053 0.0321
-5.000 0.0927 0.02551 0.01977 -0.1509 0.9035 0.0249
-4.750 0.1250 0.02278 0.01646 -0.1525 0.8979 0.0251
-4.500 0.1585 0.02092 0.01441 -0.1542 0.8929 0.0274
-4.250 0.1983 0.01939 0.01255 -0.1565 0.8901 0.0320
-4.000 0.2389 0.01795 0.01096 -0.1588 0.8878 0.0368
-3.750 0.2648 0.01720 0.01015 -0.1584 0.8798 0.0455
-3.500 0.3008 0.01603 0.00899 -0.1600 0.8756 0.0604
-3.250 0.3395 0.01529 0.00817 -0.1619 0.8724 0.0801
-3.000 0.3652 0.01468 0.00766 -0.1616 0.8640 0.1003
-2.750 0.4004 0.01400 0.00702 -0.1630 0.8592 0.1392
-2.500 0.4316 0.01347 0.00668 -0.1637 0.8530 0.1933
-2.250 0.4615 0.01307 0.00646 -0.1642 0.8459 0.2598
-2.000 0.4968 0.01261 0.00618 -0.1656 0.8414 0.3418
-1.750 0.5213 0.01243 0.00620 -0.1650 0.8323 0.4162
-1.500 0.5539 0.01208 0.00603 -0.1657 0.8269 0.5030
-1.250 0.5783 0.01195 0.00609 -0.1649 0.8182 0.5798
-1.000 0.6076 0.01170 0.00598 -0.1647 0.8121 0.6608
-0.750 0.6292 0.01160 0.00604 -0.1630 0.8035 0.7342
-0.500 0.6522 0.01137 0.00592 -0.1612 0.7969 0.8123
-0.250 0.6661 0.01118 0.00585 -0.1575 0.7882 0.9102
0.000 0.7020 0.01105 0.00558 -0.1589 0.7815 1.0000
0.250 0.7295 0.01118 0.00559 -0.1589 0.7727 1.0000
0.500 0.7615 0.01121 0.00546 -0.1595 0.7658 1.0000
0.750 0.7878 0.01134 0.00551 -0.1593 0.7566 1.0000
1.000 0.8195 0.01139 0.00541 -0.1599 0.7497 1.0000
1.250 0.8449 0.01153 0.00551 -0.1594 0.7400 1.0000
1.500 0.8746 0.01162 0.00548 -0.1596 0.7324 1.0000
1.750 0.9012 0.01174 0.00555 -0.1593 0.7229 1.0000
2.000 0.9288 0.01186 0.00560 -0.1592 0.7142 1.0000
2.250 0.9570 0.01196 0.00562 -0.1591 0.7054 1.0000
2.500 0.9829 0.01210 0.00574 -0.1587 0.6955 1.0000
2.750 1.0116 0.01221 0.00577 -0.1587 0.6870 1.0000
3.000 1.0369 0.01235 0.00589 -0.1582 0.6764 1.0000
3.250 1.0631 0.01250 0.00600 -0.1578 0.6664 1.0000
3.500 1.0912 0.01262 0.00604 -0.1577 0.6570 1.0000
3.750 1.1154 0.01277 0.00623 -0.1570 0.6455 1.0000
4.000 1.1407 0.01294 0.00637 -0.1564 0.6344 1.0000
4.250 1.1667 0.01309 0.00649 -0.1560 0.6235 1.0000
4.500 1.1923 0.01326 0.00663 -0.1555 0.6120 1.0000
4.750 1.2159 0.01344 0.00683 -0.1546 0.5992 1.0000
5.000 1.2398 0.01364 0.00702 -0.1538 0.5862 1.0000
5.250 1.2636 0.01385 0.00723 -0.1530 0.5730 1.0000
5.500 1.2870 0.01407 0.00744 -0.1521 0.5592 1.0000
5.750 1.3099 0.01431 0.00767 -0.1512 0.5449 1.0000
6.000 1.3321 0.01458 0.00793 -0.1501 0.5297 1.0000
6.250 1.3536 0.01487 0.00822 -0.1489 0.5139 1.0000
6.500 1.3743 0.01518 0.00852 -0.1476 0.4973 1.0000
6.750 1.3944 0.01553 0.00885 -0.1462 0.4802 1.0000
7.000 1.4136 0.01592 0.00922 -0.1446 0.4628 1.0000
7.250 1.4321 0.01635 0.00961 -0.1430 0.4453 1.0000
7.500 1.4495 0.01683 0.01004 -0.1412 0.4277 1.0000
7.750 1.4663 0.01731 0.01053 -0.1393 0.4101 1.0000
8.000 1.4820 0.01784 0.01106 -0.1373 0.3926 1.0000
8.250 1.4964 0.01841 0.01162 -0.1350 0.3755 1.0000
8.500 1.5086 0.01900 0.01220 -0.1324 0.3589 1.0000
8.750 1.5200 0.01965 0.01283 -0.1297 0.3426 1.0000
9.000 1.5307 0.02035 0.01354 -0.1270 0.3266 1.0000
9.250 1.5407 0.02111 0.01429 -0.1243 0.3109 1.0000
9.500 1.5501 0.02194 0.01511 -0.1215 0.2955 1.0000
9.750 1.5585 0.02284 0.01602 -0.1188 0.2802 1.0000
10.000 1.5663 0.02382 0.01700 -0.1161 0.2652 1.0000
10.250 1.5733 0.02489 0.01809 -0.1134 0.2504 1.0000
10.500 1.5796 0.02606 0.01928 -0.1108 0.2358 1.0000
10.750 1.5850 0.02734 0.02057 -0.1082 0.2214 1.0000
11.000 1.5898 0.02874 0.02198 -0.1057 0.2074 1.0000
11.250 1.5938 0.03026 0.02351 -0.1033 0.1936 1.0000
11.500 1.5972 0.03189 0.02516 -0.1011 0.1802 1.0000
11.750 1.6002 0.03365 0.02694 -0.0990 0.1676 1.0000
12.000 1.6025 0.03554 0.02887 -0.0970 0.1558 1.0000
12.250 1.6035 0.03763 0.03095 -0.0951 0.1452 1.0000
12.500 1.6046 0.03979 0.03314 -0.0934 0.1350 1.0000
12.750 1.6077 0.04189 0.03532 -0.0920 0.1252 1.0000
13.000 1.6083 0.04429 0.03777 -0.0906 0.1169 1.0000
13.250 1.6075 0.04691 0.04042 -0.0893 0.1090 1.0000
13.500 1.6096 0.04936 0.04300 -0.0883 0.1010 1.0000
13.750 1.6061 0.05248 0.04611 -0.0874 0.0943 1.0000
14.000 1.6069 0.05526 0.04905 -0.0867 0.0865 1.0000
14.250 1.6041 0.05856 0.05243 -0.0862 0.0796 1.0000
14.500 1.5988 0.06228 0.05618 -0.0859 0.0728 1.0000
14.750 1.5959 0.06587 0.05991 -0.0858 0.0650 1.0000
15.000 1.5879 0.07025 0.06433 -0.0860 0.0585 1.0000
15.250 1.5792 0.07490 0.06903 -0.0864 0.0522 1.0000
15.500 1.5719 0.07953 0.07378 -0.0870 0.0458 1.0000
15.750 1.5593 0.08504 0.07931 -0.0880 0.0416 1.0000
16.000 1.5523 0.08995 0.08436 -0.0892 0.0369 1.0000
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Polar data table (+)
Polar graphs
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