MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 200,000 Max Cl/Cd: 76.96 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh117-il-200000.txt Download as CSV file: xf-mh117-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 117 9.8%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4085 0.09543 0.09193 -0.0300 1.0000 0.0510
-9.000 -0.4077 0.09188 0.08843 -0.0314 1.0000 0.0523
-8.750 -0.4099 0.08790 0.08449 -0.0332 1.0000 0.0537
-8.500 -0.3773 0.06255 0.05945 -0.0431 1.0000 0.0340
-8.250 -0.3865 0.05822 0.05518 -0.0434 1.0000 0.0326
-8.000 -0.4050 0.05294 0.04999 -0.0449 1.0000 0.0316
-7.750 -0.5242 0.04703 0.04332 -0.0570 1.0000 0.0259
-7.500 -0.5260 0.04398 0.04003 -0.0557 1.0000 0.0257
-7.250 -0.5279 0.04026 0.03616 -0.0538 1.0000 0.0249
-7.000 -0.5319 0.03606 0.03167 -0.0520 1.0000 0.0243
-6.750 -0.5303 0.03217 0.02737 -0.0502 1.0000 0.0236
-6.500 -0.5231 0.02853 0.02324 -0.0486 1.0000 0.0230
-6.250 -0.4891 0.02455 0.01858 -0.0512 0.9959 0.0228
-6.000 -0.4527 0.02177 0.01531 -0.0534 0.9916 0.0234
-5.750 -0.4155 0.01983 0.01302 -0.0554 0.9866 0.0248
-5.500 -0.3781 0.01765 0.01069 -0.0577 0.9828 0.0289
-5.250 -0.3425 0.01655 0.00951 -0.0595 0.9762 0.0386
-5.000 -0.3031 0.01546 0.00844 -0.0620 0.9712 0.0658
-4.750 -0.2651 0.01503 0.00799 -0.0643 0.9652 0.0936
-4.500 -0.2269 0.01457 0.00750 -0.0666 0.9592 0.1153
-4.250 -0.1843 0.01410 0.00698 -0.0697 0.9556 0.1372
-4.000 -0.1501 0.01355 0.00650 -0.0712 0.9479 0.1580
-3.750 -0.1097 0.01300 0.00601 -0.0737 0.9434 0.1855
-3.500 -0.0746 0.01253 0.00564 -0.0753 0.9364 0.2185
-3.250 -0.0386 0.01205 0.00527 -0.0769 0.9300 0.2583
-3.000 -0.0056 0.01164 0.00500 -0.0780 0.9222 0.3047
-2.750 0.0275 0.01122 0.00475 -0.0789 0.9148 0.3577
-2.500 0.0561 0.01089 0.00459 -0.0790 0.9052 0.4147
-2.250 0.0862 0.01052 0.00442 -0.0792 0.8974 0.4824
-2.000 0.1121 0.01021 0.00434 -0.0785 0.8871 0.5542
-1.750 0.1366 0.00992 0.00431 -0.0775 0.8770 0.6323
-1.250 0.1830 0.00945 0.00428 -0.0740 0.8582 0.7957
-1.000 0.2061 0.00933 0.00428 -0.0720 0.8482 0.8725
-0.750 0.2453 0.00923 0.00416 -0.0734 0.8405 0.9408
-0.500 0.2986 0.00913 0.00397 -0.0783 0.8314 0.9853
-0.250 0.3362 0.00913 0.00384 -0.0804 0.8212 1.0000
0.000 0.3593 0.00919 0.00378 -0.0794 0.8107 1.0000
0.250 0.3831 0.00926 0.00374 -0.0784 0.8001 1.0000
0.500 0.4068 0.00935 0.00375 -0.0775 0.7887 1.0000
0.750 0.4314 0.00945 0.00376 -0.0767 0.7779 1.0000
1.000 0.4566 0.00953 0.00377 -0.0760 0.7676 1.0000
1.250 0.4822 0.00962 0.00377 -0.0754 0.7573 1.0000
1.500 0.5074 0.00972 0.00382 -0.0747 0.7457 1.0000
1.750 0.5329 0.00981 0.00387 -0.0741 0.7343 1.0000
2.000 0.5587 0.00991 0.00393 -0.0735 0.7230 1.0000
2.250 0.5848 0.01000 0.00397 -0.0729 0.7117 1.0000
2.500 0.6109 0.01010 0.00401 -0.0723 0.7000 1.0000
2.750 0.6365 0.01019 0.00408 -0.0717 0.6871 1.0000
3.000 0.6623 0.01029 0.00418 -0.0711 0.6739 1.0000
3.250 0.6880 0.01039 0.00427 -0.0704 0.6602 1.0000
3.500 0.7137 0.01050 0.00435 -0.0698 0.6459 1.0000
3.750 0.7393 0.01060 0.00446 -0.0692 0.6307 1.0000
4.000 0.7648 0.01072 0.00455 -0.0685 0.6147 1.0000
4.250 0.7898 0.01084 0.00469 -0.0678 0.5959 1.0000
4.500 0.8147 0.01097 0.00480 -0.0670 0.5760 1.0000
4.750 0.8393 0.01112 0.00496 -0.0662 0.5535 1.0000
5.000 0.8634 0.01131 0.00510 -0.0653 0.5284 1.0000
5.250 0.8869 0.01153 0.00528 -0.0643 0.4990 1.0000
5.500 0.9097 0.01182 0.00550 -0.0633 0.4649 1.0000
5.750 0.9315 0.01221 0.00577 -0.0621 0.4263 1.0000
6.000 0.9524 0.01271 0.00613 -0.0609 0.3848 1.0000
6.250 0.9726 0.01330 0.00656 -0.0596 0.3442 1.0000
6.500 0.9921 0.01398 0.00706 -0.0584 0.3042 1.0000
6.750 1.0115 0.01469 0.00762 -0.0571 0.2654 1.0000
7.000 1.0305 0.01544 0.00823 -0.0559 0.2308 1.0000
7.250 1.0491 0.01624 0.00892 -0.0546 0.1983 1.0000
7.500 1.0670 0.01710 0.00965 -0.0532 0.1692 1.0000
7.750 1.0845 0.01801 0.01046 -0.0518 0.1449 1.0000
8.000 1.1007 0.01901 0.01134 -0.0502 0.1256 1.0000
8.250 1.1171 0.01999 0.01228 -0.0486 0.1098 1.0000
8.500 1.1327 0.02104 0.01328 -0.0470 0.0975 1.0000
8.750 1.1491 0.02198 0.01425 -0.0454 0.0871 1.0000
9.000 1.1653 0.02294 0.01533 -0.0438 0.0782 1.0000
9.250 1.1782 0.02428 0.01664 -0.0419 0.0712 1.0000
9.500 1.1934 0.02516 0.01763 -0.0402 0.0643 1.0000
9.750 1.2044 0.02653 0.01904 -0.0381 0.0582 1.0000
10.000 1.2161 0.02743 0.02003 -0.0360 0.0524 1.0000
10.250 1.2249 0.02899 0.02163 -0.0338 0.0470 1.0000
10.500 1.2345 0.02990 0.02268 -0.0317 0.0418 1.0000
10.750 1.2402 0.03191 0.02469 -0.0296 0.0371 1.0000
11.000 1.2474 0.03288 0.02587 -0.0276 0.0323 1.0000
11.250 1.2485 0.03549 0.02843 -0.0255 0.0281 1.0000
11.500 1.2545 0.03690 0.03014 -0.0238 0.0252 1.0000
11.750 1.2575 0.03845 0.03177 -0.0225 0.0221 1.0000
12.000 1.2551 0.04159 0.03499 -0.0209 0.0198 1.0000
12.250 1.2574 0.04386 0.03750 -0.0197 0.0180 1.0000
12.500 1.2584 0.04657 0.04040 -0.0187 0.0170 1.0000
12.750 1.2581 0.04941 0.04341 -0.0180 0.0162 1.0000
13.000 1.2563 0.05240 0.04653 -0.0176 0.0155 1.0000
13.250 1.2513 0.05602 0.05027 -0.0175 0.0147 1.0000
13.500 1.2427 0.06048 0.05493 -0.0175 0.0143 1.0000
13.750 1.2307 0.06555 0.06026 -0.0181 0.0141 1.0000
14.000 1.2145 0.07138 0.06635 -0.0195 0.0140 1.0000
14.500 1.1824 0.08345 0.07887 -0.0241 0.0139 1.0000
14.750 1.1654 0.09015 0.08579 -0.0275 0.0139 1.0000
15.000 1.1529 0.09643 0.09227 -0.0310 0.0140 1.0000
15.250 1.1329 0.10471 0.10076 -0.0359 0.0140 1.0000
15.500 1.1190 0.11222 0.10844 -0.0407 0.0141 1.0000
15.750 1.1046 0.12038 0.11677 -0.0461 0.0142 1.0000
16.000 1.0871 0.13006 0.12665 -0.0527 0.0145 1.0000
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Polar data table (+)
Polar graphs
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