MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 500,000 Max Cl/Cd: 114.87 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh122-il-500000-n5.txt Download as CSV file: xf-mh122-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3422 0.10965 0.10727 -0.0529 0.9934 0.0062
-10.000 -0.3397 0.10403 0.10167 -0.0559 0.9914 0.0064
-9.750 -0.3343 0.09927 0.09692 -0.0590 0.9892 0.0066
-9.500 -0.3259 0.09490 0.09256 -0.0623 0.9869 0.0067
-9.250 -0.3169 0.09045 0.08812 -0.0660 0.9847 0.0069
-9.000 -0.3061 0.08647 0.08411 -0.0698 0.9829 0.0071
-7.750 -0.2742 0.06311 0.06082 -0.0906 0.9510 0.0072
-7.500 -0.2546 0.05092 0.04849 -0.1109 0.9439 0.0070
-7.250 -0.2365 0.04406 0.04140 -0.1198 0.9368 0.0070
-7.000 -0.2118 0.03798 0.03500 -0.1262 0.9323 0.0067
-6.750 -0.1912 0.03540 0.03227 -0.1287 0.9264 0.0053
-6.500 -0.1712 0.02961 0.02603 -0.1323 0.9204 0.0046
-6.250 -0.1531 0.02173 0.01735 -0.1329 0.9134 0.0034
-6.000 -0.1267 0.01941 0.01465 -0.1333 0.9088 0.0032
-5.750 -0.0983 0.01783 0.01277 -0.1340 0.9055 0.0031
-5.250 -0.0479 0.01463 0.00901 -0.1339 0.8972 0.0030
-5.000 -0.0207 0.01326 0.00741 -0.1340 0.8939 0.0029
-4.750 0.0064 0.01217 0.00615 -0.1341 0.8907 0.0029
-4.500 0.0321 0.01133 0.00518 -0.1339 0.8868 0.0030
-4.250 0.0593 0.01066 0.00436 -0.1340 0.8835 0.0030
-4.000 0.0876 0.01001 0.00358 -0.1343 0.8807 0.0031
-3.750 0.1164 0.00954 0.00295 -0.1346 0.8782 0.0035
-3.500 0.1435 0.00925 0.00259 -0.1346 0.8748 0.0044
-3.250 0.1713 0.00901 0.00230 -0.1347 0.8716 0.0092
-3.000 0.1991 0.00835 0.00204 -0.1353 0.8689 0.1088
-2.750 0.2268 0.00740 0.00181 -0.1362 0.8665 0.3305
-2.500 0.2548 0.00721 0.00173 -0.1365 0.8638 0.3913
-2.250 0.2820 0.00707 0.00172 -0.1366 0.8608 0.4451
-2.000 0.3099 0.00701 0.00170 -0.1367 0.8580 0.4756
-1.750 0.3381 0.00695 0.00169 -0.1368 0.8554 0.5087
-1.500 0.3668 0.00692 0.00166 -0.1371 0.8531 0.5304
-1.250 0.3950 0.00691 0.00166 -0.1372 0.8506 0.5438
-1.000 0.4223 0.00690 0.00166 -0.1372 0.8475 0.5537
-0.750 0.4501 0.00690 0.00167 -0.1373 0.8445 0.5635
-0.500 0.4783 0.00689 0.00168 -0.1374 0.8417 0.5734
-0.250 0.5072 0.00689 0.00168 -0.1377 0.8389 0.5833
0.000 0.5339 0.00689 0.00172 -0.1375 0.8346 0.5936
0.250 0.5612 0.00689 0.00174 -0.1374 0.8297 0.6045
0.500 0.5897 0.00689 0.00175 -0.1376 0.8251 0.6162
0.750 0.6155 0.00687 0.00180 -0.1372 0.8181 0.6280
1.000 0.6432 0.00687 0.00181 -0.1371 0.8115 0.6408
1.250 0.6688 0.00685 0.00185 -0.1367 0.8023 0.6541
1.500 0.6949 0.00684 0.00188 -0.1362 0.7918 0.6685
1.750 0.7203 0.00683 0.00191 -0.1357 0.7782 0.6840
2.000 0.7451 0.00683 0.00196 -0.1349 0.7593 0.7004
2.250 0.7695 0.00685 0.00201 -0.1341 0.7382 0.7185
2.500 0.7935 0.00692 0.00208 -0.1332 0.7133 0.7385
2.750 0.8144 0.00709 0.00217 -0.1317 0.6693 0.7601
3.000 0.8281 0.00759 0.00240 -0.1286 0.5900 0.7847
3.250 0.8388 0.00829 0.00277 -0.1251 0.5012 0.8144
3.500 0.8502 0.00894 0.00315 -0.1219 0.4194 0.8532
3.750 0.8598 0.00939 0.00346 -0.1181 0.3534 0.9264
4.000 0.8780 0.01013 0.00385 -0.1165 0.2718 1.0000
4.250 0.8967 0.01077 0.00423 -0.1151 0.2133 1.0000
4.500 0.9158 0.01142 0.00462 -0.1137 0.1611 1.0000
4.750 0.9359 0.01198 0.00504 -0.1124 0.1220 1.0000
5.000 0.9572 0.01246 0.00542 -0.1114 0.0977 1.0000
5.250 0.9784 0.01294 0.00581 -0.1104 0.0759 1.0000
5.500 0.9998 0.01339 0.00621 -0.1093 0.0601 1.0000
5.750 1.0214 0.01383 0.00662 -0.1083 0.0485 1.0000
6.000 1.0427 0.01429 0.00705 -0.1073 0.0384 1.0000
6.250 1.0635 0.01474 0.00750 -0.1061 0.0301 1.0000
6.500 1.0834 0.01523 0.00798 -0.1048 0.0219 1.0000
6.750 1.1026 0.01578 0.00849 -0.1035 0.0146 1.0000
7.000 1.1214 0.01637 0.00906 -0.1020 0.0094 1.0000
7.250 1.1397 0.01701 0.00978 -0.1004 0.0055 1.0000
7.500 1.1573 0.01775 0.01057 -0.0987 0.0033 1.0000
7.750 1.1754 0.01843 0.01128 -0.0972 0.0022 1.0000
8.000 1.1924 0.01927 0.01222 -0.0955 0.0018 1.0000
8.250 1.2102 0.02001 0.01306 -0.0939 0.0016 1.0000
8.500 1.2273 0.02082 0.01399 -0.0922 0.0014 1.0000
8.750 1.2440 0.02168 0.01496 -0.0906 0.0012 1.0000
9.000 1.2601 0.02260 0.01600 -0.0888 0.0011 1.0000
9.250 1.2755 0.02359 0.01711 -0.0870 0.0010 1.0000
9.500 1.2906 0.02461 0.01824 -0.0853 0.0009 1.0000
9.750 1.3036 0.02588 0.01966 -0.0833 0.0008 1.0000
10.000 1.3117 0.02783 0.02189 -0.0806 0.0007 1.0000
10.250 1.3178 0.03000 0.02432 -0.0777 0.0006 1.0000
10.500 1.3271 0.03162 0.02614 -0.0754 0.0006 1.0000
10.750 1.3343 0.03345 0.02820 -0.0729 0.0006 1.0000
11.000 1.3383 0.03561 0.03061 -0.0702 0.0006 1.0000
11.250 1.3398 0.03800 0.03327 -0.0674 0.0006 1.0000
11.500 1.3377 0.04074 0.03628 -0.0646 0.0005 1.0000
11.750 1.3331 0.04370 0.03953 -0.0618 0.0005 1.0000
12.000 1.3250 0.04709 0.04319 -0.0591 0.0005 1.0000
12.250 1.3130 0.05098 0.04737 -0.0567 0.0005 1.0000
12.500 1.2987 0.05528 0.05194 -0.0548 0.0005 1.0000
12.750 1.2806 0.06029 0.05721 -0.0537 0.0005 1.0000
13.000 1.2623 0.06564 0.06281 -0.0534 0.0005 1.0000
13.250 1.2426 0.07170 0.06908 -0.0543 0.0005 1.0000
13.500 1.2215 0.07871 0.07630 -0.0567 0.0005 1.0000
13.750 1.1998 0.08693 0.08470 -0.0607 0.0005 1.0000
14.000 1.1763 0.09729 0.09524 -0.0672 0.0005 1.0000
14.250 1.1549 0.10960 0.10771 -0.0754 0.0006 1.0000
14.500 1.1273 0.12592 0.12415 -0.0847 0.0006 1.0000
14.750 1.0952 0.14188 0.14015 -0.0929 0.0006 1.0000
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Polar data table (+)
Polar graphs
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