MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 84 13.69% (mh84-il) Reynolds number: 100,000 Max Cl/Cd: 48.18 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh84-il-100000-n5.txt Download as CSV file: xf-mh84-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2857 0.12640 0.12178 -0.0031 1.0000 0.0577
-10.250 -0.2808 0.12310 0.11854 -0.0054 1.0000 0.0580
-9.750 -0.2771 0.11115 0.10661 -0.0113 1.0000 0.0363
-9.500 -0.2632 0.10860 0.10412 -0.0117 1.0000 0.0356
-9.000 -0.2580 0.09908 0.09471 -0.0178 0.9584 0.0319
-8.750 -0.2410 0.09515 0.09072 -0.0218 0.9076 0.0314
-8.500 -0.2331 0.09153 0.08703 -0.0239 0.8756 0.0310
-8.250 -0.2292 0.08803 0.08348 -0.0254 0.8506 0.0305
-8.000 -0.2284 0.08408 0.07949 -0.0271 0.8303 0.0302
-7.750 -0.2290 0.07989 0.07527 -0.0291 0.8130 0.0298
-7.500 -0.2332 0.07503 0.07039 -0.0317 0.7977 0.0293
-7.250 -0.2677 0.06219 0.05753 -0.0423 0.7870 0.0279
-7.000 -0.2842 0.04610 0.04100 -0.0619 0.7770 0.0271
-6.750 -0.2773 0.03806 0.03219 -0.0700 0.7650 0.0271
-6.500 -0.2590 0.03365 0.02708 -0.0728 0.7527 0.0275
-6.250 -0.2371 0.03102 0.02396 -0.0737 0.7414 0.0284
-6.000 -0.2123 0.02973 0.02252 -0.0740 0.7280 0.0295
-5.750 -0.1875 0.02800 0.02040 -0.0743 0.7165 0.0311
-5.500 -0.1616 0.02635 0.01838 -0.0744 0.7045 0.0324
-5.250 -0.1354 0.02524 0.01714 -0.0743 0.6927 0.0335
-5.000 -0.1090 0.02408 0.01573 -0.0739 0.6816 0.0349
-4.750 -0.0816 0.02298 0.01441 -0.0738 0.6695 0.0366
-4.500 -0.0550 0.02223 0.01354 -0.0735 0.6591 0.0390
-4.250 -0.0273 0.02148 0.01269 -0.0734 0.6468 0.0427
-4.000 0.0003 0.02077 0.01183 -0.0731 0.6363 0.0471
-3.750 0.0283 0.02010 0.01107 -0.0730 0.6246 0.0528
-3.500 0.0563 0.01952 0.01044 -0.0728 0.6139 0.0617
-3.250 0.0844 0.01895 0.00982 -0.0727 0.6031 0.0757
-3.000 0.1128 0.01847 0.00937 -0.0726 0.5919 0.0967
-2.750 0.1409 0.01814 0.00902 -0.0724 0.5819 0.1225
-2.500 0.1694 0.01792 0.00881 -0.0723 0.5704 0.1488
-2.250 0.1975 0.01780 0.00858 -0.0720 0.5609 0.1748
-2.000 0.2261 0.01767 0.00847 -0.0719 0.5494 0.1986
-1.750 0.2541 0.01756 0.00829 -0.0715 0.5397 0.2205
-1.500 0.2825 0.01745 0.00815 -0.0713 0.5288 0.2417
-1.250 0.3106 0.01736 0.00798 -0.0710 0.5193 0.2627
-1.000 0.3388 0.01727 0.00787 -0.0708 0.5086 0.2842
-0.750 0.3668 0.01720 0.00775 -0.0705 0.4992 0.3071
-0.500 0.3949 0.01714 0.00767 -0.0702 0.4891 0.3320
-0.250 0.4227 0.01708 0.00761 -0.0699 0.4797 0.3595
0.000 0.4503 0.01702 0.00758 -0.0695 0.4700 0.3925
0.250 0.4782 0.01697 0.00758 -0.0692 0.4610 0.4329
0.500 0.5058 0.01690 0.00760 -0.0689 0.4515 0.4846
0.750 0.5327 0.01682 0.00766 -0.0684 0.4428 0.5524
1.000 0.5581 0.01668 0.00774 -0.0674 0.4338 0.6416
1.250 0.5803 0.01643 0.00774 -0.0656 0.4261 0.7642
1.500 0.6115 0.01625 0.00769 -0.0655 0.4165 1.0000
1.750 0.6398 0.01650 0.00772 -0.0654 0.4088 1.0000
2.000 0.6681 0.01677 0.00786 -0.0654 0.3997 1.0000
2.250 0.6959 0.01704 0.00791 -0.0652 0.3926 1.0000
2.500 0.7239 0.01733 0.00814 -0.0652 0.3837 1.0000
2.750 0.7515 0.01762 0.00826 -0.0650 0.3765 1.0000
3.000 0.7791 0.01794 0.00849 -0.0648 0.3686 1.0000
3.250 0.8064 0.01826 0.00870 -0.0647 0.3611 1.0000
3.500 0.8336 0.01860 0.00891 -0.0645 0.3545 1.0000
3.750 0.8606 0.01895 0.00922 -0.0643 0.3469 1.0000
4.000 0.8874 0.01930 0.00942 -0.0640 0.3407 1.0000
4.250 0.9141 0.01970 0.00980 -0.0639 0.3336 1.0000
4.500 0.9406 0.02008 0.01011 -0.0636 0.3271 1.0000
4.750 0.9668 0.02048 0.01039 -0.0633 0.3215 1.0000
5.000 0.9929 0.02092 0.01085 -0.0631 0.3147 1.0000
5.250 1.0187 0.02133 0.01119 -0.0628 0.3089 1.0000
5.500 1.0443 0.02179 0.01159 -0.0625 0.3036 1.0000
5.750 1.0696 0.02228 0.01210 -0.0623 0.2974 1.0000
6.000 1.0948 0.02273 0.01250 -0.0619 0.2922 1.0000
6.250 1.1197 0.02324 0.01294 -0.0616 0.2873 1.0000
6.500 1.1441 0.02379 0.01356 -0.0613 0.2817 1.0000
6.750 1.1685 0.02430 0.01404 -0.0609 0.2768 1.0000
7.000 1.1928 0.02483 0.01445 -0.0605 0.2727 1.0000
7.250 1.2158 0.02547 0.01522 -0.0601 0.2674 1.0000
7.500 1.2390 0.02607 0.01584 -0.0596 0.2627 1.0000
7.750 1.2622 0.02663 0.01635 -0.0592 0.2588 1.0000
8.000 1.2847 0.02731 0.01705 -0.0587 0.2548 1.0000
8.250 1.3058 0.02804 0.01788 -0.0582 0.2501 1.0000
8.500 1.3273 0.02871 0.01857 -0.0576 0.2461 1.0000
8.750 1.3492 0.02935 0.01917 -0.0571 0.2428 1.0000
9.000 1.3693 0.03017 0.02005 -0.0564 0.2392 1.0000
9.250 1.3873 0.03107 0.02107 -0.0557 0.2352 1.0000
9.500 1.4058 0.03187 0.02193 -0.0549 0.2315 1.0000
9.750 1.4250 0.03261 0.02266 -0.0542 0.2284 1.0000
10.000 1.4438 0.03345 0.02348 -0.0535 0.2255 1.0000
10.250 1.4562 0.03464 0.02487 -0.0524 0.2221 1.0000
10.500 1.4691 0.03575 0.02610 -0.0514 0.2189 1.0000
10.750 1.4821 0.03675 0.02715 -0.0502 0.2159 1.0000
11.000 1.4960 0.03765 0.02804 -0.0491 0.2134 1.0000
11.250 1.5089 0.03872 0.02913 -0.0481 0.2109 1.0000
11.500 1.5075 0.04061 0.03124 -0.0465 0.2081 1.0000
11.750 1.5089 0.04251 0.03329 -0.0455 0.2054 1.0000
12.000 1.5133 0.04430 0.03518 -0.0447 0.2029 1.0000
12.250 1.5210 0.04587 0.03681 -0.0441 0.2006 1.0000
12.500 1.5345 0.04706 0.03799 -0.0435 0.1985 1.0000
12.750 1.5354 0.04936 0.04041 -0.0431 0.1963 1.0000
13.000 1.5165 0.05365 0.04498 -0.0434 0.1937 1.0000
13.250 1.4996 0.05816 0.04971 -0.0443 0.1911 1.0000
13.500 1.4889 0.06223 0.05393 -0.0451 0.1887 1.0000
13.750 1.4891 0.06514 0.05691 -0.0456 0.1866 1.0000
14.000 1.5033 0.06638 0.05815 -0.0453 0.1849 1.0000
14.250 1.4820 0.07224 0.06419 -0.0472 0.1827 1.0000
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Polar data table (+)
Polar graphs
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