MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.94 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh117-il-1000000-n5.txt Download as CSV file: xf-mh117-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 117 9.8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7009 0.07721 0.07516 -0.0362 1.0000 0.0017
-12.250 -0.7448 0.06580 0.06371 -0.0432 1.0000 0.0017
-12.000 -0.8044 0.05146 0.04930 -0.0526 1.0000 0.0016
-11.750 -0.8551 0.03567 0.03320 -0.0674 1.0000 0.0016
-11.500 -0.8643 0.03182 0.02912 -0.0678 1.0000 0.0016
-11.250 -0.8644 0.02897 0.02605 -0.0671 1.0000 0.0016
-11.000 -0.8582 0.02678 0.02366 -0.0660 1.0000 0.0016
-10.750 -0.8496 0.02481 0.02149 -0.0647 1.0000 0.0016
-10.500 -0.8298 0.02300 0.01946 -0.0652 0.9987 0.0017
-10.250 -0.8029 0.02130 0.01755 -0.0668 0.9957 0.0017
-10.000 -0.7757 0.01986 0.01593 -0.0681 0.9925 0.0017
-9.750 -0.7484 0.01876 0.01468 -0.0689 0.9884 0.0018
-9.500 -0.7190 0.01775 0.01354 -0.0701 0.9847 0.0018
-9.250 -0.6886 0.01687 0.01254 -0.0714 0.9810 0.0019
-9.000 -0.6611 0.01587 0.01140 -0.0720 0.9741 0.0019
-8.750 -0.6322 0.01445 0.00976 -0.0732 0.9671 0.0022
-8.500 -0.6018 0.01372 0.00893 -0.0741 0.9576 0.0023
-8.250 -0.5714 0.01314 0.00826 -0.0750 0.9461 0.0024
-8.000 -0.5425 0.01265 0.00767 -0.0754 0.9314 0.0026
-7.750 -0.5161 0.01217 0.00706 -0.0752 0.9151 0.0027
-7.500 -0.4905 0.01177 0.00655 -0.0748 0.8991 0.0028
-7.250 -0.4650 0.01139 0.00605 -0.0744 0.8842 0.0030
-7.000 -0.4392 0.01104 0.00557 -0.0740 0.8698 0.0031
-6.500 -0.3870 0.01041 0.00473 -0.0733 0.8436 0.0034
-6.250 -0.3605 0.01012 0.00436 -0.0730 0.8315 0.0035
-6.000 -0.3340 0.00978 0.00392 -0.0728 0.8201 0.0041
-5.750 -0.3073 0.00952 0.00360 -0.0725 0.8093 0.0048
-5.500 -0.2804 0.00929 0.00328 -0.0723 0.7987 0.0063
-5.250 -0.2534 0.00901 0.00297 -0.0721 0.7884 0.0094
-5.000 -0.2265 0.00873 0.00268 -0.0719 0.7786 0.0158
-4.750 -0.1995 0.00848 0.00243 -0.0718 0.7691 0.0264
-4.500 -0.1723 0.00824 0.00222 -0.0717 0.7594 0.0384
-4.250 -0.1450 0.00804 0.00203 -0.0716 0.7503 0.0514
-4.000 -0.1177 0.00786 0.00187 -0.0714 0.7415 0.0662
-3.750 -0.0901 0.00770 0.00173 -0.0714 0.7323 0.0803
-3.500 -0.0624 0.00757 0.00161 -0.0713 0.7241 0.0924
-3.250 -0.0347 0.00748 0.00148 -0.0712 0.7152 0.1018
-3.000 -0.0068 0.00736 0.00138 -0.0712 0.7068 0.1153
-2.750 0.0209 0.00727 0.00129 -0.0711 0.6984 0.1288
-2.500 0.0488 0.00717 0.00120 -0.0711 0.6895 0.1451
-2.250 0.0766 0.00708 0.00112 -0.0710 0.6808 0.1626
-2.000 0.1043 0.00702 0.00106 -0.0709 0.6714 0.1785
-1.750 0.1322 0.00693 0.00100 -0.0709 0.6615 0.1975
-1.500 0.1599 0.00685 0.00095 -0.0709 0.6517 0.2215
-1.250 0.1877 0.00680 0.00091 -0.0708 0.6417 0.2415
-1.000 0.2155 0.00672 0.00088 -0.0708 0.6316 0.2685
-0.750 0.2433 0.00666 0.00086 -0.0707 0.6217 0.2934
-0.500 0.2710 0.00660 0.00085 -0.0707 0.6117 0.3227
0.000 0.3263 0.00647 0.00085 -0.0706 0.5903 0.3907
0.250 0.3539 0.00641 0.00086 -0.0705 0.5792 0.4282
0.500 0.3814 0.00636 0.00088 -0.0705 0.5674 0.4695
0.750 0.4088 0.00631 0.00091 -0.0704 0.5550 0.5122
1.000 0.4361 0.00626 0.00095 -0.0703 0.5420 0.5585
1.250 0.4632 0.00622 0.00100 -0.0701 0.5276 0.6080
1.500 0.4902 0.00618 0.00106 -0.0699 0.5125 0.6589
1.750 0.5168 0.00615 0.00113 -0.0697 0.4961 0.7123
2.000 0.5428 0.00614 0.00122 -0.0692 0.4770 0.7681
2.250 0.5680 0.00614 0.00132 -0.0686 0.4570 0.8230
2.500 0.5918 0.00617 0.00142 -0.0676 0.4341 0.8788
2.750 0.6145 0.00624 0.00153 -0.0663 0.4079 0.9367
3.000 0.6499 0.00645 0.00164 -0.0680 0.3763 0.9871
3.250 0.6783 0.00672 0.00178 -0.0683 0.3462 1.0000
3.500 0.7039 0.00700 0.00193 -0.0679 0.3165 1.0000
3.750 0.7294 0.00729 0.00210 -0.0675 0.2892 1.0000
4.000 0.7548 0.00759 0.00227 -0.0671 0.2605 1.0000
4.250 0.7801 0.00791 0.00246 -0.0667 0.2328 1.0000
4.500 0.8058 0.00818 0.00265 -0.0664 0.2119 1.0000
4.750 0.8315 0.00846 0.00285 -0.0661 0.1935 1.0000
5.000 0.8568 0.00876 0.00306 -0.0657 0.1726 1.0000
5.250 0.8821 0.00907 0.00329 -0.0653 0.1539 1.0000
5.500 0.9074 0.00936 0.00351 -0.0649 0.1391 1.0000
5.750 0.9325 0.00968 0.00376 -0.0645 0.1228 1.0000
6.000 0.9575 0.01000 0.00403 -0.0641 0.1079 1.0000
6.250 0.9824 0.01032 0.00430 -0.0637 0.0953 1.0000
6.500 1.0069 0.01068 0.00459 -0.0632 0.0820 1.0000
6.750 1.0314 0.01103 0.00490 -0.0627 0.0712 1.0000
7.000 1.0555 0.01140 0.00522 -0.0622 0.0611 1.0000
7.250 1.0803 0.01170 0.00553 -0.0617 0.0553 1.0000
7.500 1.1043 0.01207 0.00588 -0.0612 0.0486 1.0000
7.750 1.1285 0.01240 0.00621 -0.0606 0.0437 1.0000
8.000 1.1517 0.01283 0.00660 -0.0600 0.0364 1.0000
8.250 1.1740 0.01331 0.00703 -0.0592 0.0282 1.0000
8.500 1.1963 0.01379 0.00746 -0.0585 0.0220 1.0000
8.750 1.2183 0.01427 0.00794 -0.0577 0.0170 1.0000
9.000 1.2397 0.01478 0.00843 -0.0568 0.0129 1.0000
9.250 1.2609 0.01530 0.00895 -0.0559 0.0101 1.0000
9.500 1.2820 0.01580 0.00946 -0.0549 0.0079 1.0000
9.750 1.3019 0.01638 0.01005 -0.0539 0.0057 1.0000
10.000 1.3210 0.01699 0.01068 -0.0527 0.0039 1.0000
10.250 1.3403 0.01756 0.01128 -0.0515 0.0031 1.0000
10.500 1.3584 0.01818 0.01196 -0.0502 0.0025 1.0000
10.750 1.3761 0.01878 0.01261 -0.0488 0.0020 1.0000
11.000 1.3926 0.01942 0.01331 -0.0472 0.0017 1.0000
11.250 1.4059 0.02008 0.01403 -0.0451 0.0015 1.0000
11.500 1.4175 0.02079 0.01480 -0.0428 0.0013 1.0000
11.750 1.4281 0.02157 0.01564 -0.0404 0.0012 1.0000
12.000 1.4393 0.02232 0.01646 -0.0383 0.0011 1.0000
12.250 1.4491 0.02319 0.01742 -0.0361 0.0010 1.0000
12.500 1.4590 0.02408 0.01838 -0.0341 0.0009 1.0000
12.750 1.4679 0.02508 0.01947 -0.0322 0.0009 1.0000
13.000 1.4757 0.02621 0.02068 -0.0304 0.0009 1.0000
13.250 1.4820 0.02752 0.02208 -0.0285 0.0008 1.0000
13.500 1.4883 0.02889 0.02354 -0.0269 0.0008 1.0000
13.750 1.4937 0.03040 0.02514 -0.0255 0.0007 1.0000
14.000 1.4970 0.03218 0.02701 -0.0241 0.0006 1.0000
14.250 1.5012 0.03397 0.02889 -0.0230 0.0007 1.0000
14.500 1.5021 0.03617 0.03120 -0.0221 0.0006 1.0000
14.750 1.5021 0.03857 0.03371 -0.0213 0.0006 1.0000
15.000 1.5033 0.04095 0.03620 -0.0209 0.0006 1.0000
15.250 1.4955 0.04449 0.03989 -0.0206 0.0005 1.0000
15.500 1.4945 0.04739 0.04290 -0.0207 0.0005 1.0000
15.750 1.4883 0.05109 0.04672 -0.0212 0.0005 1.0000
16.000 1.4755 0.05583 0.05163 -0.0222 0.0004 1.0000
16.250 1.4670 0.06031 0.05624 -0.0235 0.0004 1.0000
16.500 1.4566 0.06532 0.06139 -0.0253 0.0004 1.0000
16.750 1.4458 0.07067 0.06688 -0.0274 0.0004 1.0000
17.000 1.4315 0.07692 0.07328 -0.0303 0.0004 1.0000
17.250 1.4181 0.08330 0.07979 -0.0334 0.0004 1.0000
17.500 1.3979 0.09131 0.08797 -0.0376 0.0004 1.0000
17.750 1.3764 0.10000 0.09682 -0.0423 0.0004 1.0000
18.000 1.3514 0.10973 0.10671 -0.0477 0.0004 1.0000
18.250 1.3225 0.12070 0.11784 -0.0540 0.0004 1.0000
18.500 1.3040 0.12953 0.12680 -0.0591 0.0005 1.0000
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Polar data table (+)
Polar graphs
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