MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 102 16.99% (mh102-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.68 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh102-il-1000000.txt Download as CSV file: xf-mh102-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 102 16.99%
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8456 0.08656 0.08298 -0.0477 1.0000 0.0079
-16.500 -0.8554 0.08171 0.07807 -0.0500 1.0000 0.0079
-16.250 -0.8702 0.07622 0.07250 -0.0527 1.0000 0.0079
-16.000 -0.8860 0.07074 0.06695 -0.0555 1.0000 0.0080
-15.750 -0.8996 0.06577 0.06190 -0.0579 1.0000 0.0079
-15.500 -0.9208 0.05988 0.05591 -0.0608 1.0000 0.0080
-15.250 -0.9313 0.05541 0.05136 -0.0629 1.0000 0.0078
-15.000 -0.9629 0.04820 0.04402 -0.0666 1.0000 0.0080
-14.750 -0.9866 0.04184 0.03753 -0.0701 1.0000 0.0080
-14.500 -0.9933 0.03765 0.03324 -0.0725 1.0000 0.0080
-14.250 -1.0099 0.03225 0.02769 -0.0759 1.0000 0.0081
-14.000 -1.0179 0.02868 0.02400 -0.0775 1.0000 0.0082
-13.750 -1.0267 0.02592 0.02113 -0.0775 1.0000 0.0082
-13.500 -1.0327 0.02416 0.01930 -0.0757 1.0000 0.0083
-13.250 -1.0400 0.02296 0.01803 -0.0722 1.0000 0.0084
-13.000 -1.0498 0.02219 0.01721 -0.0671 1.0000 0.0084
-12.750 -1.0523 0.02143 0.01641 -0.0628 1.0000 0.0086
-12.500 -1.0459 0.02070 0.01563 -0.0600 0.9997 0.0087
-12.250 -1.0134 0.01976 0.01464 -0.0622 0.9970 0.0090
-12.000 -0.9800 0.01891 0.01373 -0.0643 0.9935 0.0094
-11.750 -0.9491 0.01817 0.01294 -0.0657 0.9888 0.0097
-11.500 -0.9185 0.01719 0.01190 -0.0673 0.9834 0.0103
-11.250 -0.8882 0.01644 0.01112 -0.0685 0.9761 0.0109
-11.000 -0.8543 0.01579 0.01043 -0.0702 0.9671 0.0115
-10.750 -0.8197 0.01506 0.00965 -0.0722 0.9526 0.0128
-10.500 -0.7831 0.01444 0.00896 -0.0743 0.9312 0.0142
-10.250 -0.7569 0.01391 0.00834 -0.0743 0.9025 0.0164
-10.000 -0.7355 0.01353 0.00785 -0.0732 0.8772 0.0186
-9.750 -0.7144 0.01314 0.00739 -0.0720 0.8559 0.0221
-9.500 -0.6926 0.01277 0.00696 -0.0709 0.8378 0.0265
-9.250 -0.6706 0.01237 0.00653 -0.0699 0.8217 0.0323
-9.000 -0.6480 0.01199 0.00611 -0.0690 0.8068 0.0398
-8.750 -0.6257 0.01156 0.00568 -0.0681 0.7919 0.0505
-8.500 -0.6031 0.01108 0.00525 -0.0672 0.7781 0.0648
-8.250 -0.5805 0.01060 0.00482 -0.0664 0.7653 0.0833
-8.000 -0.5572 0.01019 0.00446 -0.0657 0.7530 0.1030
-7.750 -0.5322 0.00987 0.00419 -0.0651 0.7411 0.1205
-7.500 -0.5066 0.00964 0.00397 -0.0646 0.7293 0.1343
-7.250 -0.4805 0.00947 0.00379 -0.0642 0.7171 0.1453
-7.000 -0.4539 0.00930 0.00363 -0.0639 0.7059 0.1562
-6.750 -0.4272 0.00917 0.00348 -0.0635 0.6952 0.1654
-6.500 -0.3997 0.00908 0.00336 -0.0633 0.6844 0.1734
-6.250 -0.3727 0.00896 0.00323 -0.0630 0.6741 0.1816
-6.000 -0.3451 0.00892 0.00314 -0.0628 0.6630 0.1884
-5.750 -0.3177 0.00881 0.00301 -0.0625 0.6526 0.1948
-5.250 -0.2621 0.00871 0.00283 -0.0622 0.6325 0.2075
-5.000 -0.2350 0.00863 0.00273 -0.0619 0.6225 0.2139
-4.750 -0.2068 0.00857 0.00264 -0.0618 0.6132 0.2187
-4.500 -0.1789 0.00857 0.00256 -0.0616 0.6031 0.2222
-4.250 -0.1514 0.00846 0.00245 -0.0614 0.5935 0.2285
-4.000 -0.1237 0.00842 0.00238 -0.0612 0.5842 0.2336
-3.750 -0.0954 0.00840 0.00231 -0.0611 0.5753 0.2377
-3.500 -0.0679 0.00834 0.00223 -0.0608 0.5664 0.2438
-3.250 -0.0398 0.00828 0.00217 -0.0607 0.5578 0.2496
-3.000 -0.0120 0.00829 0.00212 -0.0605 0.5486 0.2546
-2.750 0.0160 0.00823 0.00206 -0.0604 0.5403 0.2617
-2.500 0.0436 0.00822 0.00202 -0.0602 0.5317 0.2684
-2.250 0.0721 0.00820 0.00198 -0.0601 0.5244 0.2740
-2.000 0.0996 0.00817 0.00194 -0.0599 0.5160 0.2829
-1.750 0.1278 0.00816 0.00192 -0.0598 0.5086 0.2903
-1.500 0.1556 0.00812 0.00189 -0.0597 0.5010 0.2997
-1.250 0.1834 0.00814 0.00188 -0.0595 0.4936 0.3081
-1.000 0.2114 0.00810 0.00187 -0.0594 0.4867 0.3185
-0.750 0.2391 0.00812 0.00187 -0.0593 0.4793 0.3286
-0.500 0.2671 0.00809 0.00187 -0.0592 0.4732 0.3408
-0.250 0.2950 0.00808 0.00187 -0.0590 0.4667 0.3522
0.000 0.3224 0.00812 0.00189 -0.0588 0.4599 0.3642
0.250 0.3505 0.00808 0.00190 -0.0588 0.4548 0.3785
0.500 0.3782 0.00807 0.00192 -0.0586 0.4490 0.3939
0.750 0.4054 0.00811 0.00196 -0.0584 0.4427 0.4095
1.000 0.4335 0.00809 0.00199 -0.0583 0.4382 0.4260
1.250 0.4612 0.00808 0.00202 -0.0582 0.4330 0.4440
1.500 0.4883 0.00809 0.00207 -0.0580 0.4276 0.4650
1.750 0.5155 0.00809 0.00213 -0.0577 0.4228 0.4897
2.000 0.5432 0.00805 0.00217 -0.0576 0.4183 0.5164
2.250 0.5702 0.00804 0.00223 -0.0574 0.4134 0.5455
2.500 0.5965 0.00806 0.00232 -0.0570 0.4081 0.5790
2.750 0.6235 0.00801 0.00239 -0.0567 0.4042 0.6170
3.000 0.6501 0.00796 0.00246 -0.0564 0.3998 0.6571
3.250 0.6761 0.00795 0.00255 -0.0560 0.3949 0.6968
3.500 0.7011 0.00798 0.00267 -0.0553 0.3895 0.7384
3.750 0.7271 0.00791 0.00276 -0.0548 0.3860 0.7841
4.000 0.7520 0.00787 0.00286 -0.0540 0.3814 0.8292
4.250 0.7759 0.00788 0.00298 -0.0530 0.3765 0.8738
4.500 0.8004 0.00792 0.00311 -0.0521 0.3715 0.9195
4.750 0.8364 0.00797 0.00323 -0.0536 0.3668 0.9557
5.000 0.8794 0.00812 0.00336 -0.0568 0.3607 0.9761
5.250 0.9209 0.00829 0.00350 -0.0598 0.3543 0.9866
5.500 0.9589 0.00841 0.00361 -0.0619 0.3487 0.9962
5.750 0.9923 0.00858 0.00374 -0.0632 0.3418 1.0000
6.000 1.0147 0.00871 0.00385 -0.0621 0.3366 1.0000
6.250 1.0379 0.00883 0.00397 -0.0612 0.3307 1.0000
6.500 1.0597 0.00901 0.00411 -0.0600 0.3237 1.0000
6.750 1.0831 0.00915 0.00424 -0.0591 0.3178 1.0000
7.000 1.1057 0.00932 0.00439 -0.0581 0.3102 1.0000
7.250 1.1283 0.00951 0.00456 -0.0572 0.3033 1.0000
7.500 1.1512 0.00970 0.00472 -0.0562 0.2956 1.0000
7.750 1.1733 0.00993 0.00492 -0.0552 0.2877 1.0000
8.000 1.1959 0.01014 0.00511 -0.0543 0.2800 1.0000
8.250 1.2173 0.01040 0.00534 -0.0532 0.2721 1.0000
8.500 1.2392 0.01064 0.00556 -0.0522 0.2640 1.0000
8.750 1.2598 0.01093 0.00582 -0.0510 0.2562 1.0000
9.000 1.2810 0.01118 0.00606 -0.0499 0.2490 1.0000
9.250 1.3001 0.01151 0.00635 -0.0484 0.2412 1.0000
9.500 1.3203 0.01177 0.00661 -0.0472 0.2343 1.0000
9.750 1.3362 0.01213 0.00694 -0.0452 0.2269 1.0000
10.000 1.3539 0.01238 0.00720 -0.0434 0.2213 1.0000
10.250 1.3678 0.01276 0.00755 -0.0411 0.2144 1.0000
10.500 1.3837 0.01309 0.00789 -0.0392 0.2084 1.0000
10.750 1.3985 0.01348 0.00827 -0.0372 0.2020 1.0000
11.000 1.4121 0.01394 0.00871 -0.0351 0.1957 1.0000
11.250 1.4275 0.01433 0.00912 -0.0333 0.1900 1.0000
11.500 1.4389 0.01491 0.00967 -0.0311 0.1836 1.0000
11.750 1.4539 0.01537 0.01015 -0.0294 0.1787 1.0000
12.000 1.4660 0.01597 0.01075 -0.0275 0.1730 1.0000
12.250 1.4765 0.01668 0.01146 -0.0255 0.1673 1.0000
12.500 1.4894 0.01731 0.01211 -0.0239 0.1624 1.0000
12.750 1.4984 0.01819 0.01299 -0.0220 0.1570 1.0000
13.000 1.5091 0.01904 0.01386 -0.0205 0.1521 1.0000
13.250 1.5194 0.01997 0.01480 -0.0190 0.1474 1.0000
13.500 1.5249 0.02124 0.01607 -0.0174 0.1417 1.0000
13.750 1.5361 0.02224 0.01711 -0.0163 0.1380 1.0000
14.000 1.5431 0.02357 0.01845 -0.0151 0.1331 1.0000
14.250 1.5475 0.02516 0.02005 -0.0139 0.1282 1.0000
14.500 1.5560 0.02652 0.02145 -0.0131 0.1241 1.0000
14.750 1.5590 0.02836 0.02331 -0.0121 0.1195 1.0000
15.000 1.5628 0.03021 0.02519 -0.0114 0.1153 1.0000
15.250 1.5677 0.03204 0.02706 -0.0108 0.1117 1.0000
15.500 1.5682 0.03430 0.02934 -0.0103 0.1080 1.0000
15.750 1.5688 0.03661 0.03169 -0.0098 0.1042 1.0000
16.000 1.5707 0.03886 0.03400 -0.0095 0.1008 1.0000
16.250 1.5679 0.04165 0.03681 -0.0093 0.0974 1.0000
16.500 1.5653 0.04446 0.03967 -0.0091 0.0943 1.0000
16.750 1.5654 0.04708 0.04234 -0.0091 0.0915 1.0000
17.000 1.5611 0.05019 0.04550 -0.0092 0.0884 1.0000
17.250 1.5538 0.05368 0.04903 -0.0094 0.0856 1.0000
17.500 1.5517 0.05668 0.05209 -0.0097 0.0832 1.0000
17.750 1.5465 0.06007 0.05553 -0.0100 0.0802 1.0000
18.000 1.5370 0.06398 0.05948 -0.0105 0.0774 1.0000
18.250 1.5314 0.06750 0.06306 -0.0111 0.0749 1.0000
18.500 1.5274 0.07088 0.06650 -0.0116 0.0727 1.0000
18.750 1.5184 0.07492 0.07059 -0.0124 0.0702 1.0000
19.000 1.5077 0.07926 0.07497 -0.0134 0.0681 1.0000
19.250 1.5034 0.08284 0.07862 -0.0142 0.0660 1.0000
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