MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 200,000 Max Cl/Cd: 60.59 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh44-il-200000.txt Download as CSV file: xf-mh44-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 44 9.66%
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5459 0.12849 0.12496 0.0106 1.0000 0.0365
-11.000 -0.5483 0.12406 0.12058 0.0061 1.0000 0.0377
-5.750 -0.5319 0.02901 0.02277 -0.0178 1.0000 0.0283
-5.500 -0.5235 0.02566 0.01926 -0.0149 1.0000 0.0263
-5.250 -0.5123 0.02340 0.01670 -0.0120 1.0000 0.0251
-5.000 -0.4877 0.02115 0.01409 -0.0113 0.9978 0.0240
-4.750 -0.4498 0.01910 0.01177 -0.0129 0.9929 0.0235
-4.500 -0.4126 0.01748 0.01002 -0.0146 0.9872 0.0241
-4.250 -0.3730 0.01613 0.00859 -0.0168 0.9825 0.0260
-4.000 -0.3389 0.01479 0.00716 -0.0180 0.9751 0.0304
-3.750 -0.3006 0.01311 0.00567 -0.0201 0.9701 0.0771
-3.500 -0.2716 0.01164 0.00528 -0.0212 0.9618 0.2967
-3.250 -0.2330 0.01114 0.00506 -0.0236 0.9562 0.3825
-3.000 -0.2038 0.01072 0.00489 -0.0238 0.9463 0.4582
-2.750 -0.1761 0.01029 0.00477 -0.0235 0.9369 0.5444
-2.500 -0.1488 0.00990 0.00465 -0.0229 0.9282 0.6247
-2.250 -0.1268 0.00955 0.00458 -0.0210 0.9167 0.7041
-2.000 -0.1001 0.00924 0.00452 -0.0198 0.9064 0.7934
-1.750 -0.0486 0.00907 0.00445 -0.0234 0.9006 0.8820
-1.500 0.0063 0.00910 0.00441 -0.0282 0.8919 0.9295
-1.250 0.0525 0.00919 0.00437 -0.0312 0.8824 0.9575
-1.000 0.0999 0.00926 0.00429 -0.0346 0.8723 0.9782
-0.750 0.1501 0.00923 0.00415 -0.0390 0.8603 0.9959
-0.500 0.1785 0.00916 0.00395 -0.0392 0.8460 1.0000
-0.250 0.1978 0.00911 0.00379 -0.0373 0.8310 1.0000
0.000 0.2183 0.00908 0.00366 -0.0357 0.8160 1.0000
0.250 0.2399 0.00905 0.00353 -0.0342 0.8005 1.0000
0.500 0.2621 0.00903 0.00343 -0.0329 0.7840 1.0000
0.750 0.2848 0.00902 0.00334 -0.0317 0.7670 1.0000
1.000 0.3078 0.00901 0.00325 -0.0304 0.7497 1.0000
1.250 0.3310 0.00902 0.00317 -0.0292 0.7321 1.0000
1.500 0.3548 0.00905 0.00312 -0.0282 0.7130 1.0000
1.750 0.3787 0.00911 0.00308 -0.0272 0.6931 1.0000
2.000 0.4027 0.00919 0.00305 -0.0262 0.6739 1.0000
2.250 0.4271 0.00929 0.00310 -0.0253 0.6524 1.0000
2.500 0.4514 0.00943 0.00313 -0.0244 0.6323 1.0000
2.750 0.4761 0.00957 0.00320 -0.0237 0.6103 1.0000
3.000 0.5005 0.00974 0.00327 -0.0229 0.5896 1.0000
3.250 0.5253 0.00990 0.00341 -0.0222 0.5671 1.0000
3.500 0.5497 0.01011 0.00352 -0.0214 0.5457 1.0000
3.750 0.5744 0.01031 0.00367 -0.0207 0.5228 1.0000
4.000 0.5989 0.01053 0.00383 -0.0200 0.5004 1.0000
4.250 0.6233 0.01078 0.00403 -0.0193 0.4774 1.0000
4.500 0.6477 0.01103 0.00424 -0.0186 0.4536 1.0000
4.750 0.6718 0.01131 0.00446 -0.0179 0.4298 1.0000
5.000 0.6957 0.01162 0.00471 -0.0172 0.4054 1.0000
5.250 0.7196 0.01193 0.00500 -0.0165 0.3793 1.0000
5.500 0.7432 0.01227 0.00530 -0.0158 0.3529 1.0000
5.750 0.7665 0.01265 0.00563 -0.0150 0.3263 1.0000
6.000 0.7895 0.01308 0.00600 -0.0143 0.2993 1.0000
6.250 0.8121 0.01354 0.00642 -0.0135 0.2723 1.0000
6.500 0.8343 0.01405 0.00687 -0.0127 0.2460 1.0000
6.750 0.8560 0.01463 0.00736 -0.0118 0.2210 1.0000
7.000 0.8775 0.01522 0.00790 -0.0109 0.1967 1.0000
7.250 0.8987 0.01584 0.00849 -0.0100 0.1732 1.0000
7.500 0.9188 0.01658 0.00914 -0.0090 0.1521 1.0000
7.750 0.9392 0.01728 0.00987 -0.0080 0.1316 1.0000
8.000 0.9577 0.01817 0.01067 -0.0069 0.1141 1.0000
8.250 0.9767 0.01901 0.01152 -0.0057 0.0974 1.0000
8.500 0.9946 0.01994 0.01246 -0.0044 0.0832 1.0000
8.750 1.0112 0.02099 0.01352 -0.0030 0.0713 1.0000
9.000 1.0253 0.02232 0.01481 -0.0013 0.0618 1.0000
9.250 1.0421 0.02329 0.01591 0.0002 0.0540 1.0000
9.500 1.0550 0.02481 0.01748 0.0020 0.0480 1.0000
9.750 1.0697 0.02592 0.01871 0.0036 0.0429 1.0000
10.000 1.0803 0.02820 0.02101 0.0055 0.0393 1.0000
10.250 1.0946 0.02949 0.02251 0.0072 0.0364 1.0000
10.500 1.1064 0.03070 0.02384 0.0089 0.0333 1.0000
10.750 1.1154 0.03286 0.02603 0.0106 0.0307 1.0000
11.000 1.1221 0.03539 0.02883 0.0127 0.0289 1.0000
11.250 1.1251 0.03679 0.03046 0.0153 0.0271 1.0000
11.500 1.1264 0.03827 0.03210 0.0175 0.0251 1.0000
11.750 1.1274 0.04021 0.03415 0.0192 0.0237 1.0000
12.000 1.1251 0.04309 0.03709 0.0206 0.0220 1.0000
12.250 1.1132 0.04669 0.04099 0.0218 0.0209 1.0000
12.500 1.1068 0.04955 0.04411 0.0223 0.0203 1.0000
12.750 1.0984 0.05279 0.04759 0.0222 0.0193 1.0000
13.000 1.0890 0.05657 0.05158 0.0214 0.0187 1.0000
13.250 1.0765 0.06110 0.05631 0.0199 0.0180 1.0000
13.500 1.0613 0.06645 0.06189 0.0176 0.0181 1.0000
13.750 1.0450 0.07229 0.06792 0.0146 0.0178 1.0000
14.000 1.0258 0.07903 0.07487 0.0107 0.0180 1.0000
14.250 1.0008 0.08745 0.08350 0.0057 0.0188 1.0000
14.500 0.9768 0.09631 0.09253 0.0001 0.0191 1.0000
14.750 0.9495 0.10664 0.10301 -0.0065 0.0197 1.0000
15.000 0.9174 0.11826 0.11469 -0.0126 0.0213 1.0000
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Polar data table (+)
Polar graphs
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