MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 200,000 Max Cl/Cd: 71.96 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh117-il-200000-n5.txt Download as CSV file: xf-mh117-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4660 0.08478 0.08124 -0.0335 1.0000 0.0103
-9.500 -0.5632 0.05815 0.05464 -0.0480 1.0000 0.0084
-9.250 -0.5854 0.04977 0.04625 -0.0557 1.0000 0.0081
-9.000 -0.6034 0.04369 0.03995 -0.0595 1.0000 0.0076
-8.750 -0.6135 0.03883 0.03467 -0.0604 1.0000 0.0081
-8.500 -0.6154 0.03512 0.03062 -0.0596 1.0000 0.0080
-8.250 -0.6105 0.03229 0.02737 -0.0585 1.0000 0.0084
-8.000 -0.6044 0.02955 0.02425 -0.0569 1.0000 0.0087
-7.750 -0.5846 0.02688 0.02126 -0.0577 0.9970 0.0090
-7.500 -0.5543 0.02458 0.01863 -0.0598 0.9915 0.0093
-7.250 -0.5234 0.02267 0.01645 -0.0615 0.9857 0.0097
-7.000 -0.4915 0.02103 0.01453 -0.0632 0.9802 0.0101
-6.750 -0.4606 0.01962 0.01290 -0.0645 0.9734 0.0108
-6.500 -0.4271 0.01833 0.01138 -0.0661 0.9684 0.0117
-6.250 -0.3968 0.01723 0.01009 -0.0669 0.9603 0.0128
-6.000 -0.3636 0.01617 0.00890 -0.0685 0.9544 0.0152
-5.750 -0.3331 0.01532 0.00798 -0.0692 0.9457 0.0206
-5.500 -0.3005 0.01446 0.00706 -0.0704 0.9386 0.0322
-5.250 -0.2687 0.01384 0.00649 -0.0714 0.9303 0.0513
-5.000 -0.2367 0.01345 0.00607 -0.0723 0.9217 0.0697
-4.750 -0.2043 0.01305 0.00567 -0.0733 0.9137 0.0865
-4.500 -0.1743 0.01270 0.00529 -0.0738 0.9035 0.1010
-4.250 -0.1442 0.01237 0.00491 -0.0742 0.8938 0.1154
-3.750 -0.0860 0.01179 0.00428 -0.0746 0.8734 0.1498
-3.500 -0.0580 0.01153 0.00402 -0.0746 0.8629 0.1704
-3.250 -0.0301 0.01130 0.00377 -0.0745 0.8528 0.1931
-3.000 -0.0026 0.01108 0.00357 -0.0744 0.8428 0.2204
-2.750 0.0244 0.01088 0.00340 -0.0741 0.8322 0.2492
-2.500 0.0515 0.01070 0.00325 -0.0739 0.8224 0.2812
-2.250 0.0785 0.01051 0.00311 -0.0737 0.8130 0.3169
-2.000 0.1052 0.01033 0.00301 -0.0734 0.8028 0.3558
-1.750 0.1318 0.01015 0.00292 -0.0731 0.7933 0.4000
-1.500 0.1583 0.00998 0.00285 -0.0727 0.7844 0.4495
-1.250 0.1844 0.00979 0.00281 -0.0723 0.7745 0.5040
-1.000 0.2102 0.00962 0.00279 -0.0717 0.7653 0.5631
-0.500 0.2600 0.00927 0.00280 -0.0700 0.7466 0.6928
-0.250 0.2838 0.00912 0.00282 -0.0686 0.7371 0.7606
0.000 0.3078 0.00901 0.00283 -0.0672 0.7279 0.8286
0.250 0.3365 0.00894 0.00282 -0.0668 0.7174 0.8954
0.500 0.3757 0.00890 0.00277 -0.0689 0.7069 0.9547
0.750 0.4166 0.00891 0.00271 -0.0716 0.6962 1.0000
1.250 0.4679 0.00910 0.00274 -0.0705 0.6744 1.0000
1.500 0.4937 0.00919 0.00278 -0.0701 0.6631 1.0000
1.750 0.5197 0.00930 0.00282 -0.0696 0.6516 1.0000
2.000 0.5457 0.00941 0.00289 -0.0692 0.6396 1.0000
2.250 0.5717 0.00953 0.00295 -0.0687 0.6271 1.0000
2.500 0.5977 0.00965 0.00303 -0.0682 0.6139 1.0000
2.750 0.6236 0.00978 0.00312 -0.0678 0.5999 1.0000
3.000 0.6495 0.00992 0.00324 -0.0673 0.5850 1.0000
3.250 0.6753 0.01007 0.00335 -0.0668 0.5689 1.0000
3.500 0.7009 0.01023 0.00348 -0.0663 0.5513 1.0000
3.750 0.7263 0.01041 0.00362 -0.0658 0.5321 1.0000
4.000 0.7514 0.01061 0.00379 -0.0652 0.5106 1.0000
4.250 0.7761 0.01085 0.00396 -0.0645 0.4861 1.0000
4.500 0.8002 0.01112 0.00416 -0.0638 0.4581 1.0000
4.750 0.8238 0.01145 0.00440 -0.0630 0.4254 1.0000
5.000 0.8465 0.01186 0.00467 -0.0621 0.3897 1.0000
5.250 0.8688 0.01232 0.00499 -0.0612 0.3531 1.0000
5.500 0.8907 0.01283 0.00535 -0.0603 0.3185 1.0000
5.750 0.9126 0.01336 0.00576 -0.0594 0.2847 1.0000
6.000 0.9344 0.01390 0.00621 -0.0585 0.2539 1.0000
6.250 0.9563 0.01445 0.00667 -0.0577 0.2267 1.0000
6.500 0.9779 0.01502 0.00716 -0.0568 0.2012 1.0000
6.750 0.9990 0.01563 0.00768 -0.0559 0.1764 1.0000
7.000 1.0202 0.01622 0.00823 -0.0550 0.1551 1.0000
7.250 1.0410 0.01685 0.00884 -0.0541 0.1362 1.0000
7.500 1.0615 0.01750 0.00945 -0.0531 0.1183 1.0000
7.750 1.0815 0.01817 0.01010 -0.0520 0.1031 1.0000
8.000 1.1011 0.01885 0.01078 -0.0509 0.0906 1.0000
8.250 1.1202 0.01957 0.01150 -0.0498 0.0797 1.0000
8.500 1.1384 0.02033 0.01228 -0.0485 0.0709 1.0000
8.750 1.1564 0.02108 0.01307 -0.0472 0.0632 1.0000
9.000 1.1737 0.02187 0.01395 -0.0458 0.0568 1.0000
9.250 1.1897 0.02271 0.01483 -0.0443 0.0511 1.0000
9.500 1.2047 0.02359 0.01580 -0.0427 0.0464 1.0000
9.750 1.2191 0.02441 0.01670 -0.0410 0.0413 1.0000
10.000 1.2291 0.02544 0.01776 -0.0387 0.0371 1.0000
10.250 1.2427 0.02625 0.01870 -0.0370 0.0326 1.0000
10.500 1.2515 0.02738 0.01985 -0.0348 0.0286 1.0000
10.750 1.2623 0.02842 0.02101 -0.0330 0.0253 1.0000
11.000 1.2720 0.02956 0.02222 -0.0313 0.0217 1.0000
11.250 1.2783 0.03100 0.02377 -0.0294 0.0189 1.0000
11.500 1.2859 0.03240 0.02530 -0.0278 0.0164 1.0000
11.750 1.2887 0.03426 0.02721 -0.0261 0.0142 1.0000
12.000 1.2932 0.03606 0.02916 -0.0247 0.0124 1.0000
12.250 1.2979 0.03792 0.03113 -0.0237 0.0105 1.0000
12.500 1.2970 0.04038 0.03370 -0.0226 0.0097 1.0000
12.750 1.2952 0.04307 0.03654 -0.0218 0.0091 1.0000
13.000 1.2946 0.04578 0.03944 -0.0213 0.0084 1.0000
13.250 1.2913 0.04892 0.04276 -0.0211 0.0077 1.0000
13.500 1.2877 0.05224 0.04624 -0.0212 0.0073 1.0000
13.750 1.2826 0.05590 0.05007 -0.0217 0.0070 1.0000
14.000 1.2756 0.06000 0.05433 -0.0226 0.0068 1.0000
14.250 1.2668 0.06456 0.05906 -0.0240 0.0066 1.0000
14.500 1.2560 0.06966 0.06432 -0.0258 0.0064 1.0000
14.750 1.2426 0.07549 0.07032 -0.0283 0.0063 1.0000
15.000 1.2323 0.08112 0.07612 -0.0308 0.0063 1.0000
15.250 1.2146 0.08844 0.08360 -0.0344 0.0061 1.0000
15.500 1.2017 0.09524 0.09057 -0.0380 0.0061 1.0000
15.750 1.1878 0.10254 0.09804 -0.0419 0.0061 1.0000
16.000 1.1735 0.11019 0.10585 -0.0461 0.0061 1.0000
16.250 1.1581 0.11838 0.11421 -0.0508 0.0061 1.0000
16.500 1.1436 0.12658 0.12255 -0.0555 0.0061 1.0000
16.750 1.1282 0.13531 0.13143 -0.0605 0.0061 1.0000
17.250 1.1010 0.15259 0.14899 -0.0706 0.0062 1.0000
17.500 1.0873 0.16179 0.15832 -0.0760 0.0063 1.0000
17.750 1.0715 0.17198 0.16863 -0.0819 0.0064 1.0000
18.000 1.0508 0.18449 0.18127 -0.0890 0.0065 1.0000
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Polar data table (+)
Polar graphs
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