MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 95 15.86% (mh95-il) Reynolds number: 100,000 Max Cl/Cd: 44.54 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh95-il-100000.txt Download as CSV file: xf-mh95-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 95 15.86%
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5467 0.08741 0.08222 -0.0558 1.0000 0.1004
-10.750 -0.6403 0.07349 0.06805 -0.0599 1.0000 0.0815
-10.500 -0.6969 0.06907 0.06347 -0.0562 1.0000 0.0793
-10.250 -0.7660 0.06686 0.06104 -0.0475 1.0000 0.0777
-10.000 -0.7846 0.06390 0.05792 -0.0428 1.0000 0.0739
-9.750 -0.8025 0.06081 0.05469 -0.0383 1.0000 0.0721
-9.500 -0.8715 0.05720 0.05011 -0.0269 1.0000 0.0667
-9.250 -0.8612 0.05377 0.04670 -0.0253 1.0000 0.0658
-9.000 -0.8612 0.05092 0.04366 -0.0221 1.0000 0.0649
-8.750 -0.8621 0.04820 0.04069 -0.0186 1.0000 0.0640
-8.500 -0.8605 0.04572 0.03793 -0.0153 1.0000 0.0635
-8.250 -0.8564 0.04344 0.03534 -0.0121 1.0000 0.0634
-8.000 -0.8495 0.04145 0.03306 -0.0092 1.0000 0.0638
-7.750 -0.8399 0.03955 0.03086 -0.0066 1.0000 0.0643
-7.500 -0.8276 0.03775 0.02877 -0.0042 1.0000 0.0647
-7.250 -0.8125 0.03604 0.02680 -0.0022 1.0000 0.0650
-7.000 -0.7957 0.03449 0.02503 -0.0003 1.0000 0.0654
-6.750 -0.7779 0.03312 0.02345 0.0014 1.0000 0.0661
-6.500 -0.7590 0.03185 0.02202 0.0030 1.0000 0.0671
-6.250 -0.7387 0.03041 0.02069 0.0041 1.0000 0.0688
-6.000 -0.7210 0.02946 0.01978 0.0057 1.0000 0.0714
-5.750 -0.7040 0.02867 0.01892 0.0074 1.0000 0.0749
-5.500 -0.6878 0.02764 0.01800 0.0091 1.0000 0.0785
-5.250 -0.6728 0.02681 0.01725 0.0110 1.0000 0.0831
-5.000 -0.6592 0.02593 0.01641 0.0131 1.0000 0.0882
-4.750 -0.6464 0.02514 0.01569 0.0153 1.0000 0.0961
-4.500 -0.6349 0.02415 0.01486 0.0175 1.0000 0.1123
-4.250 -0.6280 0.02228 0.01378 0.0203 1.0000 0.1875
-4.000 -0.6226 0.02013 0.01333 0.0230 0.9982 0.4404
-3.750 -0.5925 0.02033 0.01445 0.0233 0.9899 0.6031
-3.500 -0.5573 0.02156 0.01586 0.0232 0.9813 0.6875
-3.250 -0.5268 0.02279 0.01708 0.0241 0.9713 0.7367
-3.000 -0.4991 0.02412 0.01838 0.0260 0.9611 0.7714
-2.750 -0.4645 0.02584 0.02005 0.0275 0.9525 0.7975
-2.500 -0.4316 0.02698 0.02109 0.0284 0.9429 0.8190
-2.250 -0.3953 0.02782 0.02180 0.0280 0.9336 0.8347
-2.000 -0.3487 0.02857 0.02240 0.0254 0.9258 0.8489
-1.750 -0.3152 0.02894 0.02266 0.0249 0.9155 0.8635
-1.500 -0.2449 0.02982 0.02338 0.0180 0.9099 0.8727
-1.250 -0.1942 0.03019 0.02364 0.0141 0.9011 0.8837
-1.000 -0.1225 0.03055 0.02387 0.0064 0.8947 0.8927
-0.750 -0.0378 0.03066 0.02386 -0.0038 0.8911 0.8994
-0.500 0.0150 0.03055 0.02368 -0.0085 0.8797 0.9077
-0.250 0.0861 0.03013 0.02318 -0.0163 0.8749 0.9150
0.000 0.1416 0.02972 0.02274 -0.0214 0.8632 0.9223
0.250 0.2101 0.02892 0.02189 -0.0285 0.8583 0.9296
0.500 0.2687 0.02819 0.02116 -0.0342 0.8469 0.9356
0.750 0.3407 0.02701 0.01996 -0.0418 0.8422 0.9414
1.000 0.3984 0.02603 0.01899 -0.0471 0.8307 0.9469
1.250 0.4752 0.02460 0.01757 -0.0557 0.8242 0.9514
1.500 0.5167 0.02378 0.01675 -0.0580 0.8091 0.9579
1.750 0.5758 0.02262 0.01560 -0.0635 0.7927 0.9626
2.000 0.6234 0.02174 0.01469 -0.0668 0.7734 0.9681
2.250 0.6692 0.02094 0.01384 -0.0699 0.7498 0.9730
2.500 0.7085 0.02036 0.01319 -0.0719 0.7216 0.9783
2.750 0.7434 0.01995 0.01266 -0.0731 0.6913 0.9836
3.000 0.7789 0.01956 0.01212 -0.0744 0.6574 0.9885
3.250 0.8088 0.01938 0.01177 -0.0748 0.6225 0.9935
3.500 0.8398 0.01921 0.01141 -0.0756 0.5861 0.9984
3.750 0.8590 0.01932 0.01132 -0.0742 0.5543 1.0000
4.000 0.8707 0.01955 0.01144 -0.0713 0.5248 1.0000
4.250 0.8830 0.01983 0.01155 -0.0687 0.4978 1.0000
4.500 0.8939 0.02014 0.01173 -0.0658 0.4716 1.0000
4.750 0.9058 0.02048 0.01189 -0.0631 0.4484 1.0000
5.000 0.9160 0.02084 0.01216 -0.0602 0.4255 1.0000
5.250 0.9260 0.02121 0.01244 -0.0572 0.4045 1.0000
5.500 0.9355 0.02160 0.01273 -0.0542 0.3846 1.0000
5.750 0.9447 0.02201 0.01305 -0.0511 0.3661 1.0000
6.000 0.9533 0.02244 0.01340 -0.0480 0.3485 1.0000
6.250 0.9611 0.02288 0.01376 -0.0447 0.3318 1.0000
6.500 0.9684 0.02334 0.01414 -0.0414 0.3161 1.0000
6.750 0.9755 0.02383 0.01454 -0.0380 0.3014 1.0000
7.000 0.9833 0.02435 0.01493 -0.0348 0.2877 1.0000
7.250 0.9870 0.02479 0.01537 -0.0309 0.2745 1.0000
7.500 0.9911 0.02530 0.01587 -0.0270 0.2622 1.0000
7.750 0.9981 0.02587 0.01634 -0.0237 0.2516 1.0000
8.000 1.0018 0.02634 0.01680 -0.0198 0.2418 1.0000
8.250 1.0074 0.02693 0.01738 -0.0162 0.2331 1.0000
8.500 1.0114 0.02741 0.01783 -0.0124 0.2251 1.0000
8.750 1.0190 0.02807 0.01846 -0.0092 0.2179 1.0000
9.000 1.0217 0.02856 0.01901 -0.0051 0.2112 1.0000
9.250 1.0431 0.02950 0.01978 -0.0045 0.2043 1.0000
9.500 1.0469 0.03018 0.02065 -0.0007 0.1989 1.0000
9.750 1.0642 0.03101 0.02145 0.0006 0.1930 1.0000
10.000 1.0884 0.03221 0.02259 0.0006 0.1874 1.0000
10.250 1.0975 0.03317 0.02376 0.0032 0.1827 1.0000
10.500 1.1159 0.03419 0.02482 0.0042 0.1781 1.0000
10.750 1.1506 0.03580 0.02626 0.0023 0.1735 1.0000
11.000 1.1542 0.03698 0.02777 0.0055 0.1706 1.0000
11.250 1.1626 0.03828 0.02927 0.0079 0.1672 1.0000
11.500 1.1746 0.03949 0.03060 0.0096 0.1638 1.0000
11.750 1.1984 0.04087 0.03195 0.0095 0.1605 1.0000
12.000 1.2163 0.04300 0.03418 0.0099 0.1580 1.0000
12.250 1.2077 0.04464 0.03614 0.0144 0.1564 1.0000
12.500 1.1987 0.04654 0.03832 0.0185 0.1546 1.0000
12.750 1.1906 0.04860 0.04062 0.0220 0.1529 1.0000
13.000 1.1842 0.05072 0.04294 0.0250 0.1510 1.0000
13.250 1.1838 0.05278 0.04513 0.0270 0.1491 1.0000
13.500 1.1854 0.05491 0.04738 0.0287 0.1474 1.0000
13.750 1.1979 0.05707 0.04958 0.0291 0.1455 1.0000
14.000 1.1923 0.06047 0.05310 0.0306 0.1442 1.0000
14.250 1.1544 0.06461 0.05753 0.0338 0.1439 1.0000
14.500 1.1119 0.06995 0.06313 0.0355 0.1439 1.0000
14.750 1.0563 0.07756 0.07099 0.0352 0.1442 1.0000
15.000 0.5245 0.15645 0.15093 -0.0037 0.2051 1.0000
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Polar data table (+)
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