MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 100,000 Max Cl/Cd: 47.03 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh24-il-100000-n5.txt Download as CSV file: xf-mh24-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 24 9.01%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4728 0.10346 0.09835 -0.0321 1.0000 0.0239
-9.750 -0.4724 0.09993 0.09485 -0.0321 1.0000 0.0224
-9.500 -0.4744 0.09613 0.09111 -0.0329 1.0000 0.0214
-9.250 -0.4779 0.09228 0.08732 -0.0340 1.0000 0.0206
-9.000 -0.4836 0.08824 0.08335 -0.0352 1.0000 0.0199
-8.750 -0.4921 0.08406 0.07924 -0.0367 1.0000 0.0192
-8.500 -0.5042 0.07988 0.07515 -0.0385 1.0000 0.0188
-8.250 -0.5219 0.07622 0.07153 -0.0385 1.0000 0.0185
-8.000 -0.5407 0.07348 0.06881 -0.0362 1.0000 0.0183
-7.750 -0.5572 0.06970 0.06500 -0.0343 1.0000 0.0177
-7.500 -0.5721 0.06536 0.06056 -0.0321 1.0000 0.0168
-7.250 -0.5791 0.06099 0.05596 -0.0296 1.0000 0.0157
-6.750 -0.5813 0.05548 0.05013 -0.0241 1.0000 0.0149
-6.500 -0.5844 0.05204 0.04651 -0.0212 1.0000 0.0147
-6.250 -0.5841 0.04882 0.04308 -0.0184 1.0000 0.0144
-6.000 -0.5813 0.04559 0.03959 -0.0156 1.0000 0.0142
-5.750 -0.5762 0.04238 0.03606 -0.0128 1.0000 0.0140
-5.500 -0.5684 0.03932 0.03266 -0.0101 1.0000 0.0138
-5.250 -0.5579 0.03651 0.02947 -0.0075 1.0000 0.0136
-5.000 -0.5451 0.03371 0.02625 -0.0050 1.0000 0.0135
-4.750 -0.5297 0.03127 0.02339 -0.0028 1.0000 0.0134
-4.500 -0.5120 0.02899 0.02069 -0.0007 1.0000 0.0132
-4.250 -0.4922 0.02693 0.01813 0.0011 1.0000 0.0133
-4.000 -0.4712 0.02521 0.01608 0.0027 1.0000 0.0134
-3.750 -0.4460 0.02358 0.01417 0.0035 0.9990 0.0136
-3.500 -0.4160 0.02214 0.01250 0.0032 0.9963 0.0142
-3.250 -0.3857 0.02117 0.01137 0.0027 0.9933 0.0152
-3.000 -0.3586 0.02002 0.01015 0.0025 0.9898 0.0207
-2.750 -0.3285 0.01932 0.00923 0.0021 0.9859 0.0245
-2.500 -0.2990 0.01806 0.00815 0.0018 0.9826 0.0623
-2.250 -0.2833 0.01531 0.00787 0.0031 0.9796 0.5279
-2.000 -0.2157 0.01553 0.00902 -0.0012 0.9855 0.9369
-1.750 -0.1428 0.01602 0.00909 -0.0099 0.9893 0.9747
-1.500 -0.0663 0.01621 0.00892 -0.0200 0.9943 1.0000
-1.250 -0.0313 0.01621 0.00871 -0.0221 0.9886 1.0000
-1.000 0.0059 0.01629 0.00863 -0.0247 0.9832 1.0000
-0.750 0.0408 0.01632 0.00853 -0.0267 0.9770 1.0000
-0.500 0.0785 0.01637 0.00848 -0.0292 0.9710 1.0000
-0.250 0.1132 0.01639 0.00839 -0.0311 0.9639 1.0000
0.000 0.1523 0.01641 0.00835 -0.0338 0.9575 1.0000
0.250 0.1860 0.01640 0.00830 -0.0354 0.9493 1.0000
0.500 0.2282 0.01637 0.00827 -0.0386 0.9431 1.0000
0.750 0.2608 0.01630 0.00820 -0.0398 0.9332 1.0000
1.000 0.2977 0.01620 0.00812 -0.0418 0.9245 1.0000
1.250 0.3408 0.01603 0.00800 -0.0449 0.9167 1.0000
1.500 0.3725 0.01586 0.00791 -0.0456 0.9050 1.0000
1.750 0.4030 0.01566 0.00777 -0.0460 0.8924 1.0000
2.000 0.4321 0.01542 0.00760 -0.0460 0.8783 1.0000
2.250 0.4600 0.01515 0.00742 -0.0457 0.8627 1.0000
2.500 0.4780 0.01498 0.00733 -0.0435 0.8410 1.0000
2.750 0.5028 0.01473 0.00723 -0.0424 0.8183 1.0000
3.000 0.5328 0.01441 0.00700 -0.0423 0.7916 1.0000
3.250 0.5696 0.01403 0.00667 -0.0432 0.7571 1.0000
3.500 0.6064 0.01374 0.00634 -0.0441 0.7062 1.0000
3.750 0.6371 0.01375 0.00624 -0.0440 0.6428 1.0000
4.000 0.6599 0.01403 0.00630 -0.0425 0.5760 1.0000
4.250 0.6783 0.01448 0.00650 -0.0404 0.5107 1.0000
4.500 0.6945 0.01501 0.00680 -0.0381 0.4475 1.0000
4.750 0.7096 0.01560 0.00717 -0.0357 0.3874 1.0000
5.000 0.7241 0.01623 0.00759 -0.0333 0.3303 1.0000
5.250 0.7383 0.01691 0.00807 -0.0309 0.2756 1.0000
5.500 0.7523 0.01762 0.00859 -0.0285 0.2260 1.0000
5.750 0.7663 0.01838 0.00927 -0.0262 0.1792 1.0000
6.000 0.7801 0.01919 0.00993 -0.0239 0.1392 1.0000
6.250 0.7933 0.02008 0.01067 -0.0215 0.1044 1.0000
6.500 0.8062 0.02102 0.01151 -0.0190 0.0794 1.0000
6.750 0.8185 0.02202 0.01252 -0.0163 0.0625 1.0000
7.000 0.8310 0.02300 0.01350 -0.0137 0.0491 1.0000
7.250 0.8420 0.02415 0.01472 -0.0108 0.0421 1.0000
7.500 0.8535 0.02532 0.01602 -0.0080 0.0372 1.0000
7.750 0.8622 0.02700 0.01773 -0.0049 0.0336 1.0000
8.000 0.8773 0.02827 0.01927 -0.0026 0.0292 1.0000
8.250 0.8893 0.02954 0.02065 -0.0002 0.0248 1.0000
8.500 0.9016 0.03215 0.02342 0.0021 0.0224 1.0000
8.750 0.9149 0.03373 0.02538 0.0044 0.0186 1.0000
9.000 0.9245 0.03531 0.02730 0.0069 0.0161 1.0000
9.250 0.9304 0.03772 0.02992 0.0097 0.0147 1.0000
9.750 0.9295 0.04407 0.03701 0.0164 0.0131 1.0000
10.000 0.9245 0.04665 0.03993 0.0202 0.0128 1.0000
10.250 0.9148 0.04939 0.04299 0.0241 0.0125 1.0000
10.500 0.9030 0.05210 0.04604 0.0274 0.0114 1.0000
10.750 0.8889 0.05540 0.04959 0.0299 0.0118 1.0000
11.000 0.8729 0.05886 0.05330 0.0315 0.0109 1.0000
11.250 0.8538 0.06332 0.05796 0.0318 0.0119 1.0000
11.500 0.8346 0.06818 0.06303 0.0304 0.0113 1.0000
11.750 0.8160 0.07393 0.06890 0.0277 0.0123 1.0000
12.000 0.7960 0.08107 0.07615 0.0231 0.0127 1.0000
12.250 0.7775 0.08918 0.08433 0.0176 0.0130 1.0000
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Polar data table (+)
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