MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 50,000 Max Cl/Cd: 36.13 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh117-il-50000.txt Download as CSV file: xf-mh117-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4047 0.09994 0.09337 -0.0201 1.0000 0.2516
-8.000 -0.3995 0.09653 0.09003 -0.0192 1.0000 0.2656
-7.750 -0.3980 0.09352 0.08710 -0.0183 1.0000 0.2799
-7.500 -0.3864 0.08951 0.08312 -0.0171 1.0000 0.2924
-7.250 -0.3817 0.08595 0.07963 -0.0161 1.0000 0.3021
-7.000 -0.3833 0.08327 0.07705 -0.0145 1.0000 0.3180
-6.750 -0.4541 0.06793 0.06183 -0.0427 1.0000 0.1399
-6.500 -0.4587 0.06065 0.05438 -0.0463 1.0000 0.1236
-6.250 -0.4557 0.05622 0.04981 -0.0464 1.0000 0.1224
-6.000 -0.4524 0.05145 0.04480 -0.0470 1.0000 0.1220
-5.750 -0.4461 0.04656 0.03946 -0.0477 1.0000 0.1229
-5.500 -0.4353 0.04156 0.03376 -0.0483 1.0000 0.1244
-5.250 -0.4212 0.03918 0.03139 -0.0469 1.0000 0.1352
-5.000 -0.4051 0.03621 0.02809 -0.0461 1.0000 0.1472
-4.750 -0.3869 0.03361 0.02499 -0.0455 1.0000 0.1654
-4.500 -0.3684 0.03160 0.02286 -0.0445 1.0000 0.1845
-4.250 -0.3484 0.02987 0.02089 -0.0436 1.0000 0.2052
-4.000 -0.3286 0.02851 0.01939 -0.0426 1.0000 0.2288
-3.750 -0.3065 0.02710 0.01767 -0.0419 1.0000 0.2513
-3.500 -0.2863 0.02612 0.01666 -0.0409 1.0000 0.2769
-3.250 -0.2647 0.02511 0.01558 -0.0401 1.0000 0.3034
-3.000 -0.2432 0.02431 0.01470 -0.0394 1.0000 0.3381
-2.750 -0.2233 0.02356 0.01408 -0.0382 1.0000 0.3748
-2.500 -0.2032 0.02292 0.01352 -0.0370 1.0000 0.4231
-2.250 -0.1830 0.02231 0.01314 -0.0358 1.0000 0.4839
-2.000 -0.1649 0.02170 0.01286 -0.0339 1.0000 0.5622
-1.750 -0.1513 0.02103 0.01273 -0.0306 1.0000 0.6679
-1.500 -0.1455 0.02013 0.01265 -0.0244 1.0000 0.8536
-1.250 -0.1024 0.01992 0.01184 -0.0300 1.0000 1.0000
-1.000 -0.0803 0.02030 0.01179 -0.0306 1.0000 1.0000
-0.750 -0.0596 0.02073 0.01187 -0.0308 1.0000 1.0000
-0.500 -0.0395 0.02121 0.01207 -0.0309 1.0000 1.0000
-0.250 -0.0198 0.02172 0.01235 -0.0309 1.0000 1.0000
0.000 -0.0003 0.02228 0.01270 -0.0309 1.0000 1.0000
0.250 0.0189 0.02288 0.01309 -0.0308 1.0000 1.0000
0.500 0.0576 0.02393 0.01394 -0.0345 0.9912 1.0000
0.750 0.1015 0.02508 0.01491 -0.0390 0.9790 1.0000
1.000 0.1443 0.02618 0.01586 -0.0432 0.9665 1.0000
1.250 0.1862 0.02723 0.01680 -0.0470 0.9536 1.0000
1.500 0.2271 0.02823 0.01772 -0.0506 0.9403 1.0000
1.750 0.2669 0.02919 0.01862 -0.0539 0.9263 1.0000
2.000 0.3050 0.03010 0.01950 -0.0567 0.9121 1.0000
2.250 0.3408 0.03096 0.02035 -0.0590 0.8971 1.0000
2.500 0.3751 0.03179 0.02121 -0.0610 0.8814 1.0000
2.750 0.4091 0.03260 0.02205 -0.0627 0.8651 1.0000
3.000 0.4445 0.03338 0.02288 -0.0645 0.8484 1.0000
3.250 0.4830 0.03408 0.02368 -0.0665 0.8315 1.0000
3.500 0.5271 0.03460 0.02431 -0.0690 0.8144 1.0000
3.750 0.5578 0.03524 0.02504 -0.0695 0.7955 1.0000
4.000 0.5940 0.03566 0.02562 -0.0705 0.7759 1.0000
4.250 0.6479 0.03542 0.02559 -0.0730 0.7576 1.0000
4.500 0.6767 0.03576 0.02607 -0.0724 0.7361 1.0000
4.750 0.7243 0.03509 0.02565 -0.0730 0.7164 1.0000
5.000 0.7574 0.03486 0.02561 -0.0720 0.6941 1.0000
5.250 0.8054 0.03349 0.02446 -0.0715 0.6729 1.0000
5.500 0.8368 0.03289 0.02409 -0.0696 0.6476 1.0000
5.750 0.8725 0.03183 0.02320 -0.0676 0.6210 1.0000
6.000 0.9080 0.03060 0.02210 -0.0653 0.5916 1.0000
6.250 0.9443 0.02918 0.02077 -0.0630 0.5590 1.0000
6.500 0.9689 0.02867 0.02030 -0.0601 0.5205 1.0000
6.750 0.9939 0.02821 0.01976 -0.0573 0.4786 1.0000
7.000 1.0165 0.02817 0.01952 -0.0546 0.4338 1.0000
7.250 1.0367 0.02869 0.01976 -0.0520 0.3886 1.0000
7.500 1.0540 0.02980 0.02069 -0.0496 0.3450 1.0000
7.750 1.0721 0.03123 0.02186 -0.0476 0.3056 1.0000
8.000 1.0894 0.03303 0.02360 -0.0457 0.2721 1.0000
8.250 1.1080 0.03497 0.02546 -0.0441 0.2436 1.0000
8.500 1.1284 0.03697 0.02733 -0.0428 0.2192 1.0000
8.750 1.1455 0.03945 0.03004 -0.0412 0.2007 1.0000
9.000 1.1626 0.04165 0.03230 -0.0398 0.1829 1.0000
9.250 1.1786 0.04458 0.03549 -0.0383 0.1702 1.0000
9.500 1.1904 0.04761 0.03887 -0.0365 0.1589 1.0000
9.750 1.2015 0.05052 0.04197 -0.0348 0.1479 1.0000
10.000 1.2158 0.05393 0.04556 -0.0334 0.1396 1.0000
10.250 1.2102 0.05803 0.05018 -0.0307 0.1351 1.0000
10.500 1.2010 0.06185 0.05444 -0.0280 0.1306 1.0000
10.750 1.2100 0.06547 0.05808 -0.0268 0.1233 1.0000
11.000 1.1915 0.07004 0.06305 -0.0243 0.1229 1.0000
11.250 1.1691 0.07453 0.06781 -0.0220 0.1230 1.0000
11.500 1.1445 0.07919 0.07265 -0.0205 0.1234 1.0000
11.750 1.1203 0.08450 0.07811 -0.0203 0.1240 1.0000
12.000 1.0984 0.09054 0.08425 -0.0214 0.1247 1.0000
12.250 0.6879 0.14971 0.14312 -0.0641 0.3328 1.0000
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Polar data table (+)
Polar graphs
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