MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 92 15.49% (mh92-il) Reynolds number: 100,000 Max Cl/Cd: 33.81 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh92-il-100000.txt Download as CSV file: xf-mh92-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 92 15.49%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5211 0.11081 0.10631 0.0072 1.0000 0.1514
-10.500 -0.7073 0.06168 0.05671 -0.0264 1.0000 0.0699
-10.250 -0.7454 0.06621 0.06110 -0.0233 1.0000 0.0725
-10.000 -0.7786 0.06110 0.05563 -0.0203 1.0000 0.0659
-9.750 -0.8205 0.05589 0.04963 -0.0151 1.0000 0.0596
-9.500 -0.8118 0.05197 0.04560 -0.0141 1.0000 0.0580
-9.250 -0.8117 0.04811 0.04137 -0.0119 1.0000 0.0559
-9.000 -0.8235 0.04472 0.03694 -0.0069 1.0000 0.0527
-8.750 -0.8060 0.04168 0.03367 -0.0060 1.0000 0.0523
-8.500 -0.7881 0.03890 0.03064 -0.0049 1.0000 0.0521
-8.250 -0.7681 0.03648 0.02798 -0.0039 1.0000 0.0521
-8.000 -0.7472 0.03433 0.02553 -0.0030 1.0000 0.0525
-7.750 -0.7207 0.03187 0.02308 -0.0031 1.0000 0.0537
-7.500 -0.6991 0.03045 0.02174 -0.0026 1.0000 0.0565
-7.250 -0.6876 0.02942 0.02064 -0.0003 1.0000 0.0583
-7.000 -0.6889 0.02888 0.01993 0.0040 1.0000 0.0601
-6.500 -0.6218 0.02575 0.01695 0.0007 0.9877 0.0684
-6.250 -0.5733 0.02381 0.01523 -0.0037 0.9765 0.0807
-6.000 -0.5314 0.02186 0.01353 -0.0071 0.9634 0.1043
-5.750 -0.5127 0.01888 0.01173 -0.0072 0.9461 0.2282
-5.500 -0.5001 0.01742 0.01133 -0.0050 0.9278 0.4210
-5.250 -0.4816 0.01716 0.01132 -0.0028 0.9093 0.4986
-5.000 -0.4630 0.01711 0.01139 -0.0001 0.8919 0.5553
-4.750 -0.4431 0.01721 0.01162 0.0027 0.8757 0.6032
-4.500 -0.4233 0.01745 0.01189 0.0058 0.8605 0.6449
-4.250 -0.4013 0.01787 0.01232 0.0087 0.8450 0.6807
-4.000 -0.3770 0.01844 0.01287 0.0113 0.8296 0.7110
-3.750 -0.3497 0.01905 0.01341 0.0134 0.8148 0.7346
-3.500 -0.3204 0.01963 0.01387 0.0152 0.8004 0.7535
-3.250 -0.2914 0.02015 0.01424 0.0168 0.7869 0.7707
-3.000 -0.2626 0.02061 0.01454 0.0185 0.7736 0.7869
-2.750 -0.2336 0.02103 0.01483 0.0197 0.7586 0.8028
-2.500 -0.1908 0.02165 0.01528 0.0189 0.7436 0.8126
-2.250 -0.1566 0.02196 0.01543 0.0190 0.7296 0.8251
-2.000 -0.1277 0.02212 0.01540 0.0200 0.7172 0.8393
-1.750 -0.0786 0.02243 0.01554 0.0174 0.7016 0.8472
-1.500 -0.0433 0.02253 0.01551 0.0166 0.6864 0.8594
-1.250 -0.0151 0.02258 0.01543 0.0170 0.6725 0.8737
-1.000 0.0377 0.02265 0.01531 0.0132 0.6574 0.8804
-0.750 0.0682 0.02259 0.01507 0.0132 0.6450 0.8933
-0.500 0.1123 0.02258 0.01494 0.0105 0.6291 0.9030
-0.250 0.1499 0.02251 0.01477 0.0088 0.6141 0.9140
0.000 0.1822 0.02248 0.01461 0.0079 0.6006 0.9266
0.250 0.2277 0.02229 0.01426 0.0047 0.5867 0.9358
0.500 0.2661 0.02209 0.01392 0.0027 0.5733 0.9464
0.750 0.3024 0.02197 0.01373 0.0008 0.5587 0.9576
1.000 0.3454 0.02171 0.01339 -0.0024 0.5444 0.9670
1.250 0.3866 0.02144 0.01299 -0.0053 0.5314 0.9760
1.500 0.4267 0.02114 0.01255 -0.0080 0.5193 0.9851
1.750 0.4684 0.02089 0.01228 -0.0114 0.5052 0.9937
2.000 0.5078 0.02063 0.01197 -0.0143 0.4925 1.0000
2.250 0.5278 0.02063 0.01182 -0.0133 0.4839 1.0000
2.500 0.5485 0.02078 0.01201 -0.0128 0.4728 1.0000
2.750 0.5688 0.02084 0.01192 -0.0118 0.4649 1.0000
3.000 0.5896 0.02103 0.01219 -0.0113 0.4541 1.0000
3.250 0.6103 0.02117 0.01221 -0.0104 0.4464 1.0000
3.500 0.6310 0.02140 0.01250 -0.0098 0.4365 1.0000
3.750 0.6520 0.02157 0.01255 -0.0089 0.4292 1.0000
4.000 0.6725 0.02188 0.01298 -0.0083 0.4197 1.0000
4.250 0.6939 0.02205 0.01298 -0.0073 0.4133 1.0000
4.500 0.7137 0.02247 0.01356 -0.0066 0.4037 1.0000
4.750 0.7350 0.02265 0.01363 -0.0057 0.3971 1.0000
5.000 0.7544 0.02317 0.01430 -0.0049 0.3888 1.0000
5.250 0.7750 0.02345 0.01453 -0.0039 0.3819 1.0000
5.500 0.7945 0.02394 0.01507 -0.0030 0.3750 1.0000
5.750 0.8133 0.02439 0.01559 -0.0019 0.3673 1.0000
6.000 0.8348 0.02469 0.01573 -0.0009 0.3619 1.0000
6.250 0.8502 0.02550 0.01679 0.0003 0.3542 1.0000
6.500 0.8696 0.02586 0.01713 0.0015 0.3480 1.0000
6.750 0.8877 0.02647 0.01776 0.0027 0.3421 1.0000
7.000 0.9023 0.02723 0.01868 0.0042 0.3352 1.0000
7.250 0.9223 0.02757 0.01896 0.0055 0.3299 1.0000
7.500 0.9358 0.02849 0.02002 0.0071 0.3239 1.0000
7.750 0.9493 0.02923 0.02088 0.0089 0.3176 1.0000
8.000 0.9701 0.02954 0.02110 0.0101 0.3126 1.0000
8.250 0.9783 0.03071 0.02247 0.0123 0.3069 1.0000
8.500 0.9895 0.03151 0.02338 0.0144 0.3009 1.0000
8.750 1.0117 0.03173 0.02348 0.0155 0.2960 1.0000
9.000 1.0149 0.03310 0.02508 0.0183 0.2906 1.0000
9.250 1.0226 0.03402 0.02614 0.0207 0.2848 1.0000
9.500 1.0476 0.03409 0.02607 0.0215 0.2798 1.0000
9.750 1.0473 0.03565 0.02785 0.0245 0.2747 1.0000
10.000 1.0505 0.03685 0.02921 0.0271 0.2691 1.0000
10.250 1.0793 0.03677 0.02900 0.0276 0.2639 1.0000
10.500 1.0769 0.03853 0.03095 0.0304 0.2591 1.0000
10.750 1.0705 0.04040 0.03304 0.0333 0.2538 1.0000
11.000 1.1066 0.03993 0.03244 0.0331 0.2482 1.0000
11.250 1.1017 0.04197 0.03465 0.0356 0.2438 1.0000
11.500 1.0632 0.04561 0.03858 0.0399 0.2399 1.0000
11.750 1.0245 0.04949 0.04259 0.0429 0.2367 1.0000
12.000 0.9548 0.05778 0.05101 0.0425 0.2335 1.0000
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Polar data table (+)
Polar graphs
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