MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: MH 84 13.69% (mh84-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.31 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh84-il-1000000.txt Download as CSV file: xf-mh84-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 84 13.69%
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3089 0.10753 0.10523 -0.0067 0.7664 0.0152
-10.000 -0.5449 0.05534 0.05294 -0.0364 0.7929 0.0116
-9.750 -0.6205 0.03156 0.02840 -0.0646 0.7750 0.0111
-9.250 -0.5868 0.02591 0.02215 -0.0685 0.7481 0.0112
-9.000 -0.5652 0.02386 0.01983 -0.0695 0.7360 0.0113
-8.750 -0.5415 0.02227 0.01801 -0.0700 0.7235 0.0114
-8.500 -0.5164 0.02094 0.01649 -0.0704 0.7119 0.0115
-8.250 -0.4909 0.01969 0.01502 -0.0706 0.6999 0.0115
-8.000 -0.4644 0.01860 0.01377 -0.0708 0.6886 0.0116
-7.750 -0.4375 0.01764 0.01264 -0.0709 0.6772 0.0117
-7.500 -0.4101 0.01678 0.01163 -0.0709 0.6658 0.0118
-7.250 -0.3824 0.01601 0.01072 -0.0710 0.6550 0.0118
-7.000 -0.3544 0.01531 0.00989 -0.0709 0.6435 0.0119
-6.750 -0.3262 0.01468 0.00915 -0.0709 0.6331 0.0120
-6.500 -0.2978 0.01411 0.00846 -0.0709 0.6216 0.0121
-6.250 -0.2692 0.01359 0.00784 -0.0708 0.6115 0.0122
-5.750 -0.2115 0.01270 0.00677 -0.0707 0.5901 0.0123
-5.500 -0.1827 0.01215 0.00611 -0.0707 0.5795 0.0125
-5.250 -0.1538 0.01157 0.00545 -0.0707 0.5693 0.0129
-5.000 -0.1247 0.01123 0.00504 -0.0706 0.5590 0.0132
-4.750 -0.0954 0.01094 0.00469 -0.0706 0.5487 0.0136
-4.500 -0.0661 0.01068 0.00436 -0.0705 0.5386 0.0140
-4.250 -0.0366 0.01042 0.00404 -0.0704 0.5283 0.0145
-4.000 -0.0071 0.01022 0.00376 -0.0703 0.5186 0.0149
-3.750 0.0224 0.00989 0.00337 -0.0703 0.5083 0.0160
-3.500 0.0519 0.00972 0.00314 -0.0702 0.4988 0.0173
-3.250 0.0814 0.00951 0.00289 -0.0701 0.4886 0.0194
-3.000 0.1110 0.00933 0.00268 -0.0701 0.4796 0.0233
-2.750 0.1405 0.00911 0.00246 -0.0700 0.4698 0.0331
-2.500 0.1700 0.00889 0.00230 -0.0700 0.4607 0.0524
-2.250 0.1994 0.00874 0.00218 -0.0700 0.4510 0.0732
-2.000 0.2289 0.00862 0.00210 -0.0700 0.4423 0.0920
-1.750 0.2583 0.00853 0.00204 -0.0700 0.4326 0.1106
-1.500 0.2878 0.00846 0.00199 -0.0700 0.4243 0.1298
-1.250 0.3172 0.00838 0.00196 -0.0700 0.4154 0.1531
-1.000 0.3466 0.00834 0.00195 -0.0699 0.4069 0.1755
-0.750 0.3760 0.00832 0.00195 -0.0699 0.3979 0.1969
-0.500 0.4054 0.00831 0.00195 -0.0699 0.3899 0.2161
0.000 0.4641 0.00833 0.00198 -0.0698 0.3735 0.2512
0.250 0.4935 0.00832 0.00199 -0.0698 0.3656 0.2691
0.500 0.5227 0.00837 0.00202 -0.0697 0.3569 0.2884
0.750 0.5521 0.00836 0.00205 -0.0697 0.3504 0.3112
1.000 0.5812 0.00839 0.00210 -0.0697 0.3424 0.3387
1.250 0.6104 0.00838 0.00215 -0.0697 0.3354 0.3742
1.500 0.6395 0.00838 0.00222 -0.0697 0.3276 0.4170
1.750 0.6684 0.00837 0.00230 -0.0697 0.3207 0.4711
2.000 0.6974 0.00831 0.00239 -0.0697 0.3142 0.5368
2.250 0.7258 0.00830 0.00252 -0.0696 0.3064 0.6155
2.500 0.7541 0.00818 0.00263 -0.0695 0.3006 0.7070
2.750 0.7792 0.00795 0.00274 -0.0686 0.2942 0.8466
3.000 0.8082 0.00786 0.00281 -0.0684 0.2877 1.0000
3.250 0.8372 0.00799 0.00289 -0.0684 0.2819 1.0000
3.500 0.8659 0.00818 0.00300 -0.0684 0.2750 1.0000
3.750 0.8947 0.00832 0.00311 -0.0683 0.2699 1.0000
4.000 0.9235 0.00848 0.00322 -0.0683 0.2643 1.0000
4.250 0.9518 0.00870 0.00337 -0.0683 0.2576 1.0000
4.500 0.9805 0.00883 0.00348 -0.0682 0.2533 1.0000
4.750 1.0090 0.00901 0.00361 -0.0682 0.2482 1.0000
5.000 1.0371 0.00924 0.00379 -0.0681 0.2424 1.0000
5.250 1.0655 0.00939 0.00393 -0.0681 0.2386 1.0000
5.500 1.0937 0.00957 0.00407 -0.0680 0.2340 1.0000
5.750 1.1215 0.00981 0.00426 -0.0679 0.2287 1.0000
6.000 1.1494 0.01001 0.00444 -0.0679 0.2248 1.0000
6.250 1.1775 0.01019 0.00461 -0.0678 0.2213 1.0000
6.500 1.2051 0.01041 0.00479 -0.0677 0.2172 1.0000
6.750 1.2322 0.01070 0.00504 -0.0676 0.2123 1.0000
7.000 1.2600 0.01087 0.00522 -0.0675 0.2095 1.0000
7.250 1.2875 0.01107 0.00541 -0.0674 0.2061 1.0000
7.500 1.3145 0.01133 0.00564 -0.0673 0.2024 1.0000
7.750 1.3409 0.01165 0.00593 -0.0672 0.1981 1.0000
8.000 1.3681 0.01185 0.00614 -0.0670 0.1958 1.0000
8.250 1.3951 0.01206 0.00637 -0.0669 0.1930 1.0000
8.500 1.4216 0.01233 0.00662 -0.0667 0.1897 1.0000
8.750 1.4473 0.01266 0.00693 -0.0665 0.1859 1.0000
9.000 1.4731 0.01297 0.00724 -0.0663 0.1830 1.0000
9.250 1.4995 0.01319 0.00748 -0.0661 0.1810 1.0000
9.500 1.5253 0.01346 0.00776 -0.0659 0.1783 1.0000
9.750 1.5504 0.01379 0.00808 -0.0656 0.1754 1.0000
10.000 1.5744 0.01421 0.00848 -0.0653 0.1719 1.0000
10.250 1.5992 0.01452 0.00881 -0.0649 0.1696 1.0000
10.500 1.6243 0.01478 0.00911 -0.0647 0.1675 1.0000
10.750 1.6485 0.01511 0.00945 -0.0643 0.1651 1.0000
11.000 1.6717 0.01550 0.00985 -0.0638 0.1626 1.0000
11.250 1.6933 0.01600 0.01033 -0.0632 0.1596 1.0000
11.500 1.7152 0.01643 0.01079 -0.0626 0.1574 1.0000
11.750 1.7382 0.01675 0.01116 -0.0621 0.1558 1.0000
12.000 1.7598 0.01714 0.01158 -0.0615 0.1537 1.0000
12.250 1.7798 0.01760 0.01206 -0.0607 0.1514 1.0000
12.500 1.7974 0.01817 0.01264 -0.0596 0.1491 1.0000
12.750 1.8095 0.01892 0.01340 -0.0579 0.1465 1.0000
13.000 1.8222 0.01944 0.01398 -0.0561 0.1454 1.0000
13.250 1.8343 0.02004 0.01465 -0.0544 0.1441 1.0000
13.500 1.8453 0.02079 0.01545 -0.0529 0.1426 1.0000
13.750 1.8553 0.02170 0.01640 -0.0515 0.1409 1.0000
14.000 1.8637 0.02281 0.01755 -0.0503 0.1392 1.0000
14.250 1.8697 0.02419 0.01897 -0.0491 0.1374 1.0000
14.500 1.8714 0.02602 0.02083 -0.0480 0.1353 1.0000
14.750 1.8804 0.02740 0.02228 -0.0474 0.1342 1.0000
15.000 1.8907 0.02873 0.02369 -0.0469 0.1331 1.0000
15.250 1.8992 0.03025 0.02527 -0.0465 0.1318 1.0000
15.500 1.9055 0.03203 0.02712 -0.0461 0.1304 1.0000
15.750 1.9095 0.03408 0.02923 -0.0459 0.1289 1.0000
16.000 1.9102 0.03653 0.03173 -0.0457 0.1274 1.0000
16.250 1.9061 0.03953 0.03478 -0.0457 0.1257 1.0000
16.500 1.8999 0.04285 0.03816 -0.0459 0.1240 1.0000
16.750 1.9041 0.04510 0.04051 -0.0461 0.1232 1.0000
17.000 1.9066 0.04758 0.04308 -0.0463 0.1221 1.0000
17.250 1.9071 0.05034 0.04591 -0.0467 0.1209 1.0000
17.500 1.9054 0.05345 0.04911 -0.0472 0.1197 1.0000
17.750 1.9013 0.05697 0.05270 -0.0480 0.1183 1.0000
18.000 1.8936 0.06100 0.05679 -0.0491 0.1169 1.0000
18.250 1.8817 0.06568 0.06152 -0.0504 0.1152 1.0000
18.500 1.8730 0.07004 0.06595 -0.0517 0.1137 1.0000
18.750 1.8712 0.07357 0.06959 -0.0529 0.1129 1.0000
19.000 1.8693 0.07716 0.07327 -0.0541 0.1118 1.0000
19.250 1.8642 0.08127 0.07747 -0.0556 0.1105 1.0000
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Polar data table (+)
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