MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.13 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh117-il-1000000.txt Download as CSV file: xf-mh117-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6277 0.06356 0.06177 -0.0423 1.0000 0.0037
-10.500 -0.6394 0.05719 0.05537 -0.0462 1.0000 0.0037
-10.250 -0.6575 0.04851 0.04662 -0.0526 1.0000 0.0036
-10.000 -0.6788 0.03932 0.03724 -0.0627 1.0000 0.0036
-9.750 -0.6878 0.03551 0.03323 -0.0633 1.0000 0.0036
-9.500 -0.6885 0.03284 0.03036 -0.0624 1.0000 0.0036
-9.250 -0.6862 0.03056 0.02790 -0.0608 1.0000 0.0036
-9.000 -0.6754 0.02850 0.02565 -0.0602 0.9995 0.0035
-8.750 -0.6489 0.02484 0.02159 -0.0636 0.9964 0.0035
-8.500 -0.6227 0.02091 0.01721 -0.0665 0.9933 0.0035
-8.250 -0.5940 0.01909 0.01513 -0.0679 0.9895 0.0035
-8.000 -0.5674 0.01540 0.01096 -0.0697 0.9853 0.0037
-7.750 -0.5343 0.01402 0.00941 -0.0715 0.9830 0.0040
-7.500 -0.5034 0.01331 0.00863 -0.0725 0.9785 0.0043
-7.250 -0.4721 0.01267 0.00791 -0.0735 0.9729 0.0047
-7.000 -0.4395 0.01202 0.00716 -0.0747 0.9675 0.0051
-6.750 -0.4096 0.01144 0.00649 -0.0752 0.9583 0.0054
-6.500 -0.3795 0.01097 0.00594 -0.0757 0.9481 0.0056
-6.250 -0.3515 0.01029 0.00513 -0.0758 0.9354 0.0059
-6.000 -0.3250 0.00969 0.00440 -0.0755 0.9212 0.0065
-5.750 -0.2985 0.00934 0.00393 -0.0751 0.9068 0.0073
-5.500 -0.2720 0.00908 0.00359 -0.0747 0.8930 0.0085
-5.250 -0.2466 0.00844 0.00294 -0.0742 0.8795 0.0216
-5.000 -0.2206 0.00807 0.00265 -0.0738 0.8666 0.0433
-4.750 -0.1938 0.00789 0.00245 -0.0736 0.8545 0.0557
-4.500 -0.1668 0.00772 0.00227 -0.0733 0.8426 0.0670
-4.250 -0.1397 0.00756 0.00210 -0.0732 0.8311 0.0797
-4.000 -0.1124 0.00741 0.00196 -0.0730 0.8203 0.0948
-3.750 -0.0851 0.00727 0.00182 -0.0728 0.8098 0.1109
-3.250 -0.0303 0.00698 0.00156 -0.0725 0.7892 0.1470
-3.000 -0.0028 0.00686 0.00146 -0.0724 0.7794 0.1683
-2.750 0.0246 0.00674 0.00136 -0.0723 0.7698 0.1914
-2.500 0.0522 0.00661 0.00128 -0.0722 0.7599 0.2173
-2.250 0.0799 0.00650 0.00120 -0.0721 0.7503 0.2450
-2.000 0.1074 0.00640 0.00114 -0.0720 0.7406 0.2723
-1.750 0.1350 0.00629 0.00109 -0.0719 0.7305 0.3041
-1.500 0.1627 0.00618 0.00104 -0.0719 0.7206 0.3407
-1.250 0.1902 0.00608 0.00101 -0.0718 0.7111 0.3769
-1.000 0.2177 0.00597 0.00098 -0.0717 0.7013 0.4221
-0.750 0.2453 0.00585 0.00097 -0.0716 0.6917 0.4673
-0.500 0.2726 0.00573 0.00096 -0.0715 0.6823 0.5198
-0.250 0.2998 0.00561 0.00097 -0.0714 0.6726 0.5775
0.000 0.3271 0.00547 0.00099 -0.0712 0.6629 0.6372
0.250 0.3539 0.00535 0.00101 -0.0709 0.6534 0.6985
0.500 0.3801 0.00524 0.00105 -0.0704 0.6433 0.7612
0.750 0.4059 0.00513 0.00110 -0.0698 0.6332 0.8220
1.000 0.4303 0.00503 0.00115 -0.0688 0.6233 0.8809
1.250 0.4539 0.00499 0.00119 -0.0675 0.6129 0.9374
1.500 0.4899 0.00501 0.00120 -0.0691 0.6012 0.9792
1.750 0.5291 0.00507 0.00121 -0.0716 0.5886 1.0000
2.000 0.5556 0.00515 0.00125 -0.0713 0.5761 1.0000
2.250 0.5822 0.00525 0.00130 -0.0710 0.5631 1.0000
2.500 0.6089 0.00535 0.00135 -0.0707 0.5490 1.0000
2.750 0.6355 0.00547 0.00141 -0.0704 0.5333 1.0000
3.000 0.6621 0.00561 0.00149 -0.0701 0.5165 1.0000
3.250 0.6887 0.00576 0.00158 -0.0698 0.4963 1.0000
3.500 0.7148 0.00595 0.00167 -0.0695 0.4725 1.0000
3.750 0.7407 0.00617 0.00180 -0.0691 0.4450 1.0000
4.000 0.7662 0.00645 0.00194 -0.0687 0.4105 1.0000
4.250 0.7911 0.00678 0.00212 -0.0682 0.3738 1.0000
4.500 0.8164 0.00709 0.00230 -0.0678 0.3428 1.0000
4.750 0.8415 0.00742 0.00251 -0.0674 0.3124 1.0000
5.000 0.8662 0.00778 0.00273 -0.0669 0.2796 1.0000
5.250 0.8911 0.00813 0.00296 -0.0665 0.2515 1.0000
5.500 0.9160 0.00847 0.00320 -0.0660 0.2262 1.0000
5.750 0.9405 0.00885 0.00347 -0.0655 0.1995 1.0000
6.000 0.9650 0.00923 0.00374 -0.0650 0.1761 1.0000
6.250 0.9894 0.00961 0.00402 -0.0645 0.1543 1.0000
6.500 1.0136 0.01000 0.00433 -0.0640 0.1335 1.0000
6.750 1.0374 0.01042 0.00465 -0.0634 0.1146 1.0000
7.000 1.0612 0.01084 0.00500 -0.0628 0.0974 1.0000
7.250 1.0850 0.01124 0.00535 -0.0623 0.0840 1.0000
7.500 1.1086 0.01166 0.00572 -0.0616 0.0722 1.0000
7.750 1.1317 0.01210 0.00611 -0.0610 0.0616 1.0000
8.000 1.1551 0.01251 0.00649 -0.0603 0.0530 1.0000
8.250 1.1782 0.01292 0.00687 -0.0597 0.0452 1.0000
8.500 1.2005 0.01340 0.00732 -0.0589 0.0373 1.0000
8.750 1.2232 0.01383 0.00773 -0.0582 0.0321 1.0000
9.000 1.2453 0.01429 0.00818 -0.0574 0.0271 1.0000
9.250 1.2671 0.01476 0.00864 -0.0566 0.0231 1.0000
9.500 1.2883 0.01526 0.00914 -0.0557 0.0194 1.0000
9.750 1.3089 0.01578 0.00966 -0.0547 0.0160 1.0000
10.000 1.3287 0.01635 0.01024 -0.0536 0.0125 1.0000
10.250 1.3467 0.01704 0.01091 -0.0523 0.0088 1.0000
10.500 1.3628 0.01784 0.01174 -0.0506 0.0056 1.0000
10.750 1.3767 0.01877 0.01270 -0.0487 0.0037 1.0000
11.000 1.3919 0.01952 0.01353 -0.0469 0.0032 1.0000
11.250 1.4035 0.02029 0.01436 -0.0445 0.0027 1.0000
11.500 1.4103 0.02131 0.01548 -0.0415 0.0024 1.0000
11.750 1.4174 0.02234 0.01661 -0.0387 0.0022 1.0000
12.000 1.4277 0.02317 0.01752 -0.0365 0.0021 1.0000
12.250 1.4355 0.02421 0.01865 -0.0342 0.0020 1.0000
12.500 1.4442 0.02522 0.01973 -0.0322 0.0017 1.0000
12.750 1.4511 0.02641 0.02100 -0.0303 0.0017 1.0000
13.000 1.4565 0.02778 0.02249 -0.0284 0.0016 1.0000
13.250 1.4577 0.02958 0.02440 -0.0264 0.0014 1.0000
13.500 1.4577 0.03158 0.02652 -0.0247 0.0014 1.0000
13.750 1.4599 0.03352 0.02856 -0.0234 0.0014 1.0000
14.000 1.4310 0.03866 0.03398 -0.0216 0.0012 1.0000
14.250 1.4339 0.04088 0.03629 -0.0211 0.0012 1.0000
14.500 1.4204 0.04509 0.04068 -0.0210 0.0012 1.0000
14.750 1.4140 0.04872 0.04444 -0.0213 0.0012 1.0000
15.000 1.4099 0.05227 0.04811 -0.0219 0.0012 1.0000
15.250 1.4011 0.05665 0.05263 -0.0229 0.0011 1.0000
15.500 1.3903 0.06156 0.05768 -0.0245 0.0011 1.0000
15.750 1.3779 0.06707 0.06333 -0.0266 0.0011 1.0000
16.000 1.3673 0.07261 0.06900 -0.0290 0.0011 1.0000
16.250 1.3509 0.07951 0.07606 -0.0323 0.0011 1.0000
16.500 1.3324 0.08716 0.08387 -0.0362 0.0011 1.0000
16.750 1.3146 0.09512 0.09197 -0.0404 0.0011 1.0000
17.000 1.2937 0.10401 0.10102 -0.0453 0.0011 1.0000
17.250 1.2746 0.11282 0.10997 -0.0502 0.0011 1.0000
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Polar data table (+)
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