MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 200,000 Max Cl/Cd: 87.59 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh122-il-200000-n5.txt Download as CSV file: xf-mh122-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 122 9.32%
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3373 0.08638 0.08289 -0.0602 0.9825 0.0159
-8.000 -0.3306 0.08076 0.07727 -0.0646 0.9758 0.0115
-7.500 -0.3222 0.07161 0.06816 -0.0728 0.9635 0.0103
-7.000 -0.3007 0.05738 0.05383 -0.0926 0.9490 0.0095
-6.750 -0.2827 0.05003 0.04624 -0.1018 0.9451 0.0088
-6.500 -0.2735 0.04419 0.04010 -0.1052 0.9376 0.0081
-6.250 -0.2505 0.03659 0.03193 -0.1097 0.9340 0.0070
-6.000 -0.2211 0.03240 0.02727 -0.1123 0.9323 0.0065
-5.750 -0.2012 0.02995 0.02447 -0.1123 0.9273 0.0063
-5.250 -0.1462 0.02441 0.01805 -0.1147 0.9222 0.0061
-5.000 -0.1148 0.02188 0.01508 -0.1161 0.9208 0.0060
-4.750 -0.0823 0.01983 0.01267 -0.1174 0.9196 0.0061
-4.500 -0.0495 0.01820 0.01078 -0.1186 0.9186 0.0062
-4.250 -0.0300 0.01688 0.00931 -0.1172 0.9137 0.0064
-4.000 -0.0013 0.01562 0.00787 -0.1178 0.9113 0.0071
-3.750 0.0303 0.01482 0.00686 -0.1188 0.9094 0.0082
-3.500 0.0627 0.01432 0.00626 -0.1200 0.9078 0.0121
-3.250 0.0961 0.01339 0.00544 -0.1215 0.9065 0.0526
-3.000 0.1282 0.01179 0.00503 -0.1241 0.9055 0.3474
-2.750 0.1505 0.01165 0.00507 -0.1231 0.9011 0.4371
-2.500 0.1783 0.01156 0.00504 -0.1232 0.8982 0.4921
-2.250 0.2083 0.01150 0.00496 -0.1237 0.8961 0.5310
-2.000 0.2390 0.01143 0.00493 -0.1243 0.8943 0.5699
-1.750 0.2711 0.01136 0.00483 -0.1252 0.8928 0.5911
-1.500 0.2978 0.01138 0.00482 -0.1251 0.8898 0.6038
-1.250 0.3225 0.01143 0.00483 -0.1245 0.8859 0.6156
-1.000 0.3517 0.01141 0.00480 -0.1249 0.8833 0.6276
-0.750 0.3825 0.01136 0.00476 -0.1256 0.8813 0.6402
-0.500 0.4143 0.01131 0.00471 -0.1265 0.8796 0.6535
-0.250 0.4397 0.01136 0.00479 -0.1260 0.8760 0.6669
0.000 0.4647 0.01140 0.00488 -0.1255 0.8718 0.6815
0.250 0.4943 0.01137 0.00490 -0.1259 0.8690 0.6972
0.500 0.5257 0.01129 0.00488 -0.1266 0.8667 0.7140
0.750 0.5513 0.01131 0.00498 -0.1262 0.8625 0.7320
1.000 0.5761 0.01132 0.00509 -0.1255 0.8576 0.7524
1.250 0.6061 0.01121 0.00507 -0.1258 0.8541 0.7746
1.500 0.6320 0.01114 0.00512 -0.1253 0.8492 0.8003
1.750 0.6560 0.01106 0.00515 -0.1242 0.8428 0.8311
2.000 0.6847 0.01084 0.00505 -0.1240 0.8375 0.8698
2.250 0.7100 0.01064 0.00504 -0.1230 0.8285 0.9460
2.500 0.7398 0.01051 0.00495 -0.1232 0.8178 1.0000
2.750 0.7679 0.01037 0.00482 -0.1230 0.8038 1.0000
3.000 0.7963 0.01021 0.00467 -0.1227 0.7863 1.0000
3.250 0.8204 0.01019 0.00472 -0.1217 0.7675 1.0000
3.500 0.8461 0.01017 0.00473 -0.1210 0.7467 1.0000
3.750 0.8710 0.01017 0.00474 -0.1201 0.7161 1.0000
4.000 0.8969 0.01024 0.00464 -0.1193 0.6560 1.0000
4.250 0.9124 0.01089 0.00470 -0.1164 0.5471 1.0000
4.500 0.9193 0.01194 0.00518 -0.1123 0.4423 1.0000
4.750 0.9265 0.01306 0.00579 -0.1086 0.3448 1.0000
5.000 0.9362 0.01416 0.00650 -0.1056 0.2560 1.0000
5.250 0.9500 0.01511 0.00713 -0.1034 0.1905 1.0000
5.500 0.9655 0.01601 0.00777 -0.1015 0.1395 1.0000
5.750 0.9825 0.01679 0.00840 -0.0998 0.1046 1.0000
6.000 1.0004 0.01749 0.00905 -0.0982 0.0836 1.0000
6.250 1.0182 0.01821 0.00972 -0.0966 0.0652 1.0000
6.500 1.0359 0.01895 0.01043 -0.0950 0.0512 1.0000
6.750 1.0537 0.01970 0.01125 -0.0934 0.0419 1.0000
7.000 1.0710 0.02053 0.01211 -0.0917 0.0330 1.0000
7.250 1.0866 0.02157 0.01315 -0.0898 0.0254 1.0000
7.500 1.1052 0.02231 0.01403 -0.0885 0.0182 1.0000
7.750 1.1215 0.02335 0.01515 -0.0868 0.0125 1.0000
8.000 1.1344 0.02492 0.01678 -0.0845 0.0087 1.0000
8.250 1.1494 0.02629 0.01836 -0.0825 0.0075 1.0000
8.500 1.1640 0.02794 0.02021 -0.0805 0.0065 1.0000
8.750 1.1795 0.02971 0.02217 -0.0787 0.0059 1.0000
9.000 1.1952 0.03158 0.02425 -0.0770 0.0055 1.0000
9.250 1.2092 0.03336 0.02623 -0.0753 0.0050 1.0000
9.500 1.2173 0.03652 0.02968 -0.0731 0.0042 1.0000
9.750 1.2307 0.03776 0.03118 -0.0713 0.0037 1.0000
10.000 1.2407 0.03953 0.03322 -0.0692 0.0031 1.0000
10.250 1.2468 0.04173 0.03571 -0.0668 0.0028 1.0000
10.500 1.2480 0.04452 0.03883 -0.0640 0.0027 1.0000
10.750 1.2454 0.04755 0.04220 -0.0610 0.0025 1.0000
11.000 1.2397 0.05070 0.04565 -0.0583 0.0024 1.0000
11.250 1.2299 0.05434 0.04962 -0.0556 0.0024 1.0000
11.500 1.2179 0.05821 0.05385 -0.0534 0.0023 1.0000
11.750 1.2016 0.06285 0.05879 -0.0518 0.0023 1.0000
12.000 1.1824 0.06810 0.06432 -0.0509 0.0023 1.0000
12.250 1.1618 0.07392 0.07040 -0.0512 0.0023 1.0000
12.500 1.1367 0.08117 0.07785 -0.0531 0.0024 1.0000
12.750 1.1124 0.08929 0.08618 -0.0568 0.0024 1.0000
13.000 1.0857 0.09974 0.09684 -0.0631 0.0025 1.0000
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Polar data table (+)
Polar graphs
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