MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 83 13.29% (mh83-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.83 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh83-il-1000000.txt Download as CSV file: xf-mh83-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2621 0.09790 0.09512 -0.0083 0.6214 0.0142
-8.750 -0.2554 0.09487 0.09206 -0.0098 0.6116 0.0146
-8.500 -0.2503 0.09144 0.08862 -0.0116 0.6032 0.0149
-8.250 -0.2585 0.08458 0.08176 -0.0159 0.5984 0.0159
-8.000 -0.2593 0.07981 0.07699 -0.0186 0.5916 0.0160
-7.750 -0.2595 0.07564 0.07282 -0.0208 0.5841 0.0160
-7.500 -0.2679 0.07119 0.06839 -0.0226 0.5775 0.0162
-7.250 -0.2658 0.06876 0.06596 -0.0238 0.5694 0.0163
-7.000 -0.3376 0.02286 0.01841 -0.0642 0.5867 0.0135
-6.750 -0.3128 0.02071 0.01592 -0.0648 0.5764 0.0135
-6.500 -0.2867 0.01905 0.01399 -0.0651 0.5660 0.0135
-6.250 -0.2598 0.01770 0.01241 -0.0652 0.5565 0.0136
-6.000 -0.2324 0.01657 0.01108 -0.0653 0.5465 0.0136
-5.750 -0.2046 0.01561 0.00995 -0.0653 0.5369 0.0137
-5.250 -0.1482 0.01412 0.00818 -0.0653 0.5169 0.0140
-5.000 -0.1197 0.01350 0.00743 -0.0653 0.5076 0.0141
-4.750 -0.0910 0.01302 0.00686 -0.0652 0.4986 0.0144
-4.500 -0.0623 0.01261 0.00635 -0.0652 0.4897 0.0148
-4.250 -0.0334 0.01216 0.00581 -0.0651 0.4806 0.0151
-4.000 -0.0045 0.01173 0.00528 -0.0650 0.4716 0.0154
-3.750 0.0246 0.01137 0.00484 -0.0650 0.4624 0.0157
-3.500 0.0538 0.01113 0.00452 -0.0649 0.4543 0.0160
-3.250 0.0827 0.01054 0.00386 -0.0650 0.4461 0.0166
-3.000 0.1119 0.01028 0.00355 -0.0650 0.4382 0.0171
-2.750 0.1412 0.01008 0.00330 -0.0649 0.4305 0.0177
-2.500 0.1705 0.00992 0.00307 -0.0649 0.4225 0.0184
-2.250 0.1999 0.00977 0.00287 -0.0649 0.4149 0.0190
-2.000 0.2292 0.00957 0.00260 -0.0649 0.4066 0.0201
-1.750 0.2586 0.00943 0.00244 -0.0649 0.4001 0.0217
-1.500 0.2879 0.00932 0.00229 -0.0649 0.3928 0.0241
-1.250 0.3174 0.00920 0.00215 -0.0649 0.3866 0.0290
-1.000 0.3466 0.00890 0.00202 -0.0650 0.3801 0.0746
-0.750 0.3758 0.00880 0.00198 -0.0651 0.3731 0.1093
-0.500 0.4050 0.00868 0.00195 -0.0652 0.3674 0.1421
-0.250 0.4341 0.00858 0.00194 -0.0653 0.3609 0.1893
0.000 0.4633 0.00849 0.00196 -0.0654 0.3552 0.2386
0.250 0.4924 0.00839 0.00198 -0.0655 0.3501 0.2907
0.500 0.5214 0.00830 0.00202 -0.0656 0.3445 0.3545
0.750 0.5502 0.00817 0.00209 -0.0657 0.3395 0.4351
1.250 0.6077 0.00791 0.00222 -0.0658 0.3301 0.6096
1.500 0.6355 0.00780 0.00233 -0.0657 0.3246 0.7133
1.750 0.6580 0.00736 0.00240 -0.0641 0.3217 0.8919
2.000 0.6907 0.00733 0.00242 -0.0648 0.3176 1.0000
2.250 0.7197 0.00746 0.00248 -0.0648 0.3135 1.0000
2.500 0.7484 0.00763 0.00258 -0.0649 0.3088 1.0000
2.750 0.7776 0.00771 0.00264 -0.0649 0.3063 1.0000
3.000 0.8065 0.00782 0.00271 -0.0650 0.3029 1.0000
3.250 0.8353 0.00796 0.00279 -0.0650 0.2993 1.0000
3.500 0.8639 0.00813 0.00291 -0.0650 0.2955 1.0000
3.750 0.8925 0.00828 0.00303 -0.0651 0.2924 1.0000
4.000 0.9214 0.00838 0.00312 -0.0651 0.2902 1.0000
4.250 0.9500 0.00850 0.00322 -0.0652 0.2874 1.0000
4.500 0.9785 0.00865 0.00334 -0.0652 0.2843 1.0000
4.750 1.0068 0.00883 0.00348 -0.0653 0.2810 1.0000
5.000 1.0348 0.00905 0.00366 -0.0653 0.2776 1.0000
5.250 1.0633 0.00916 0.00377 -0.0653 0.2760 1.0000
5.500 1.0917 0.00928 0.00390 -0.0654 0.2739 1.0000
5.750 1.1200 0.00942 0.00403 -0.0654 0.2713 1.0000
6.000 1.1480 0.00960 0.00418 -0.0654 0.2687 1.0000
6.250 1.1757 0.00980 0.00437 -0.0655 0.2659 1.0000
6.500 1.2029 0.01008 0.00461 -0.0654 0.2625 1.0000
6.750 1.2310 0.01020 0.00475 -0.0655 0.2612 1.0000
7.000 1.2590 0.01033 0.00491 -0.0655 0.2592 1.0000
7.250 1.2868 0.01049 0.00507 -0.0655 0.2570 1.0000
7.500 1.3142 0.01067 0.00526 -0.0655 0.2548 1.0000
7.750 1.3413 0.01089 0.00547 -0.0655 0.2524 1.0000
8.000 1.3678 0.01117 0.00574 -0.0655 0.2493 1.0000
8.250 1.3947 0.01140 0.00598 -0.0654 0.2470 1.0000
8.500 1.4221 0.01155 0.00617 -0.0655 0.2454 1.0000
8.750 1.4492 0.01173 0.00637 -0.0654 0.2436 1.0000
9.000 1.4760 0.01192 0.00659 -0.0654 0.2413 1.0000
9.250 1.5024 0.01215 0.00683 -0.0654 0.2388 1.0000
9.500 1.5281 0.01245 0.00711 -0.0653 0.2361 1.0000
9.750 1.5530 0.01281 0.00748 -0.0651 0.2330 1.0000
10.000 1.5797 0.01297 0.00769 -0.0650 0.2315 1.0000
10.250 1.6059 0.01316 0.00793 -0.0650 0.2295 1.0000
10.500 1.6316 0.01339 0.00819 -0.0649 0.2271 1.0000
10.750 1.6567 0.01366 0.00848 -0.0647 0.2244 1.0000
11.000 1.6806 0.01402 0.00884 -0.0644 0.2214 1.0000
11.250 1.7042 0.01439 0.00923 -0.0641 0.2185 1.0000
11.500 1.7295 0.01459 0.00949 -0.0640 0.2165 1.0000
11.750 1.7540 0.01484 0.00980 -0.0637 0.2140 1.0000
12.000 1.7773 0.01517 0.01014 -0.0634 0.2111 1.0000
12.250 1.7991 0.01559 0.01057 -0.0629 0.2078 1.0000
12.500 1.8204 0.01601 0.01102 -0.0624 0.2043 1.0000
12.750 1.8436 0.01627 0.01135 -0.0621 0.2013 1.0000
13.000 1.8643 0.01667 0.01177 -0.0615 0.1972 1.0000
13.250 1.8813 0.01726 0.01236 -0.0605 0.1930 1.0000
13.500 1.9002 0.01769 0.01285 -0.0596 0.1901 1.0000
13.750 1.9166 0.01815 0.01336 -0.0585 0.1864 1.0000
14.000 1.9245 0.01884 0.01408 -0.0563 0.1827 1.0000
14.250 1.9290 0.01983 0.01509 -0.0541 0.1781 1.0000
14.500 1.9391 0.02068 0.01599 -0.0528 0.1734 1.0000
14.750 1.9434 0.02203 0.01736 -0.0514 0.1686 1.0000
15.000 1.9484 0.02347 0.01884 -0.0503 0.1645 1.0000
15.250 1.9542 0.02498 0.02040 -0.0495 0.1596 1.0000
15.500 1.9539 0.02710 0.02255 -0.0487 0.1552 1.0000
15.750 1.9556 0.02917 0.02467 -0.0482 0.1505 1.0000
16.000 1.9545 0.03160 0.02716 -0.0478 0.1460 1.0000
16.250 1.9457 0.03490 0.03048 -0.0476 0.1408 1.0000
16.500 1.9423 0.03782 0.03348 -0.0476 0.1363 1.0000
16.750 1.9298 0.04176 0.03747 -0.0479 0.1318 1.0000
17.000 1.9175 0.04585 0.04163 -0.0484 0.1278 1.0000
17.250 1.9051 0.05006 0.04591 -0.0490 0.1238 1.0000
17.500 1.8841 0.05555 0.05146 -0.0503 0.1196 1.0000
17.750 1.8672 0.06077 0.05677 -0.0516 0.1161 1.0000
18.000 1.8489 0.06633 0.06242 -0.0532 0.1123 1.0000
18.250 1.8238 0.07303 0.06918 -0.0554 0.1085 1.0000
18.500 1.8039 0.07921 0.07546 -0.0576 0.1056 1.0000
18.750 1.7841 0.08557 0.08190 -0.0599 0.1020 1.0000
19.000 1.7595 0.09276 0.08917 -0.0627 0.0987 1.0000
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Polar data table (+)
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