MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 83 13.29% (mh83-il) Reynolds number: 200,000 Max Cl/Cd: 59.1 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh83-il-200000.txt Download as CSV file: xf-mh83-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 83 13.29%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2080 0.08998 0.08638 -0.0172 0.7408 0.0512
-7.500 -0.2066 0.08694 0.08332 -0.0195 0.7279 0.0533
-7.250 -0.2321 0.08277 0.07917 -0.0294 0.7198 0.0546
-7.000 -0.2158 0.07972 0.07608 -0.0259 0.7062 0.0552
-6.750 -0.1994 0.07756 0.07386 -0.0243 0.6926 0.0563
-6.500 -0.1900 0.07516 0.07140 -0.0249 0.6812 0.0579
-6.250 -0.1823 0.07203 0.06824 -0.0280 0.6704 0.0601
-6.000 -0.1789 0.06378 0.05989 -0.0439 0.6642 0.0636
-5.750 -0.1634 0.06305 0.05915 -0.0396 0.6516 0.0648
-5.500 -0.1467 0.06083 0.05688 -0.0404 0.6401 0.0675
-5.250 -0.1283 0.05272 0.04846 -0.0532 0.6335 0.0737
-5.000 -0.1095 0.05101 0.04675 -0.0524 0.6220 0.0752
-4.750 -0.0885 0.04843 0.04403 -0.0539 0.6125 0.0783
-4.500 -0.0556 0.03007 0.02367 -0.0667 0.6107 0.0475
-4.250 -0.0274 0.02539 0.01827 -0.0673 0.6009 0.0411
-4.000 0.0000 0.02316 0.01577 -0.0675 0.5909 0.0405
-3.750 0.0284 0.02143 0.01366 -0.0674 0.5809 0.0402
-3.500 0.0574 0.02010 0.01200 -0.0673 0.5704 0.0405
-3.250 0.0854 0.01903 0.01068 -0.0671 0.5612 0.0422
-3.000 0.1140 0.01827 0.00988 -0.0670 0.5501 0.0441
-2.750 0.1426 0.01749 0.00891 -0.0666 0.5409 0.0455
-2.500 0.1715 0.01682 0.00810 -0.0663 0.5309 0.0472
-2.250 0.1997 0.01611 0.00740 -0.0662 0.5221 0.0501
-2.000 0.2284 0.01564 0.00686 -0.0660 0.5127 0.0550
-1.750 0.2571 0.01519 0.00642 -0.0659 0.5038 0.0648
-1.500 0.2861 0.01449 0.00588 -0.0659 0.4950 0.1044
-1.250 0.3146 0.01403 0.00570 -0.0660 0.4864 0.1893
-1.000 0.3429 0.01380 0.00563 -0.0661 0.4781 0.2576
-0.750 0.3709 0.01360 0.00567 -0.0661 0.4705 0.3439
-0.500 0.3985 0.01333 0.00569 -0.0659 0.4625 0.4426
-0.250 0.4248 0.01308 0.00573 -0.0654 0.4557 0.5571
0.000 0.4481 0.01265 0.00580 -0.0640 0.4480 0.7125
0.250 0.4783 0.01220 0.00563 -0.0633 0.4413 1.0000
0.500 0.5075 0.01238 0.00567 -0.0634 0.4340 1.0000
0.750 0.5364 0.01257 0.00567 -0.0634 0.4277 1.0000
1.000 0.5651 0.01285 0.00574 -0.0634 0.4221 1.0000
1.250 0.5939 0.01304 0.00584 -0.0634 0.4154 1.0000
1.500 0.6225 0.01325 0.00589 -0.0634 0.4098 1.0000
1.750 0.6509 0.01354 0.00604 -0.0634 0.4043 1.0000
2.000 0.6794 0.01375 0.00619 -0.0634 0.3985 1.0000
2.250 0.7078 0.01400 0.00631 -0.0633 0.3937 1.0000
2.500 0.7360 0.01436 0.00651 -0.0633 0.3894 1.0000
2.750 0.7642 0.01460 0.00675 -0.0633 0.3842 1.0000
3.000 0.7924 0.01484 0.00692 -0.0633 0.3793 1.0000
3.250 0.8204 0.01514 0.00709 -0.0632 0.3752 1.0000
3.500 0.8483 0.01550 0.00741 -0.0632 0.3710 1.0000
3.750 0.8761 0.01580 0.00771 -0.0632 0.3666 1.0000
4.000 0.9039 0.01609 0.00796 -0.0632 0.3627 1.0000
4.250 0.9318 0.01643 0.00818 -0.0631 0.3592 1.0000
4.500 0.9592 0.01686 0.00856 -0.0631 0.3555 1.0000
4.750 0.9864 0.01717 0.00895 -0.0630 0.3513 1.0000
5.000 1.0138 0.01750 0.00926 -0.0630 0.3476 1.0000
5.250 1.0413 0.01785 0.00954 -0.0629 0.3444 1.0000
5.500 1.0688 0.01834 0.00992 -0.0629 0.3415 1.0000
5.750 1.0952 0.01876 0.01044 -0.0628 0.3380 1.0000
6.000 1.1216 0.01914 0.01088 -0.0628 0.3342 1.0000
6.250 1.1484 0.01950 0.01125 -0.0627 0.3308 1.0000
6.500 1.1754 0.01989 0.01160 -0.0626 0.3280 1.0000
6.750 1.2026 0.02044 0.01205 -0.0626 0.3254 1.0000
7.000 1.2278 0.02096 0.01270 -0.0625 0.3222 1.0000
7.250 1.2530 0.02142 0.01328 -0.0623 0.3186 1.0000
7.500 1.2788 0.02184 0.01374 -0.0622 0.3154 1.0000
7.750 1.3052 0.02226 0.01414 -0.0621 0.3127 1.0000
8.000 1.3320 0.02277 0.01459 -0.0620 0.3102 1.0000
8.250 1.3567 0.02347 0.01536 -0.0619 0.3074 1.0000
8.500 1.3796 0.02405 0.01612 -0.0616 0.3041 1.0000
8.750 1.4035 0.02457 0.01674 -0.0613 0.3008 1.0000
9.000 1.4286 0.02506 0.01726 -0.0612 0.2981 1.0000
9.250 1.4548 0.02553 0.01770 -0.0611 0.2957 1.0000
9.500 1.4810 0.02629 0.01841 -0.0611 0.2930 1.0000
9.750 1.5004 0.02701 0.01937 -0.0605 0.2899 1.0000
10.000 1.5210 0.02773 0.02026 -0.0600 0.2867 1.0000
10.250 1.5434 0.02834 0.02096 -0.0597 0.2838 1.0000
10.500 1.5681 0.02878 0.02140 -0.0595 0.2812 1.0000
10.750 1.5952 0.02929 0.02184 -0.0595 0.2787 1.0000
11.000 1.6131 0.03030 0.02303 -0.0589 0.2758 1.0000
11.250 1.6282 0.03128 0.02424 -0.0580 0.2726 1.0000
11.500 1.6460 0.03202 0.02513 -0.0573 0.2694 1.0000
11.750 1.6683 0.03248 0.02561 -0.0569 0.2666 1.0000
12.000 1.6954 0.03284 0.02593 -0.0569 0.2641 1.0000
12.250 1.7131 0.03390 0.02709 -0.0563 0.2613 1.0000
12.500 1.7179 0.03521 0.02869 -0.0546 0.2580 1.0000
12.750 1.7277 0.03623 0.02986 -0.0533 0.2548 1.0000
13.000 1.7452 0.03678 0.03046 -0.0525 0.2520 1.0000
13.250 1.7749 0.03685 0.03047 -0.0527 0.2493 1.0000
13.500 1.7864 0.03804 0.03178 -0.0516 0.2464 1.0000
13.750 1.7679 0.04006 0.03407 -0.0480 0.2437 1.0000
14.000 1.7535 0.04216 0.03635 -0.0455 0.2409 1.0000
14.250 1.7561 0.04351 0.03779 -0.0444 0.2381 1.0000
14.500 1.7895 0.04302 0.03724 -0.0444 0.2352 1.0000
14.750 1.8047 0.04402 0.03828 -0.0438 0.2323 1.0000
15.000 1.7542 0.04950 0.04409 -0.0424 0.2297 1.0000
15.250 1.7010 0.05683 0.05169 -0.0434 0.2265 1.0000
15.500 1.6924 0.06017 0.05513 -0.0439 0.2234 1.0000
15.750 1.7643 0.05493 0.04974 -0.0420 0.2206 1.0000
16.000 1.7478 0.05917 0.05412 -0.0426 0.2177 1.0000
16.750 1.6188 0.08405 0.07951 -0.0517 0.2062 1.0000
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Polar data table (+)
Polar graphs
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