MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.71 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh121-il-1000000-n5.txt Download as CSV file: xf-mh121-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 121 8.76%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3646 0.08955 0.08787 -0.0567 0.9918 0.0016
-9.000 -0.3591 0.08482 0.08315 -0.0602 0.9896 0.0016
-8.750 -0.3522 0.08001 0.07835 -0.0643 0.9870 0.0015
-8.500 -0.3448 0.07462 0.07297 -0.0695 0.9842 0.0015
-8.000 -0.3368 0.06378 0.06217 -0.0800 0.9710 0.0014
-7.750 -0.3295 0.05391 0.05226 -0.0958 0.9575 0.0014
-7.500 -0.3133 0.04443 0.04254 -0.1086 0.9483 0.0013
-7.250 -0.2878 0.03604 0.03379 -0.1179 0.9421 0.0012
-7.000 -0.2660 0.02796 0.02520 -0.1226 0.9322 0.0011
-6.750 -0.2504 0.01939 0.01585 -0.1233 0.9204 0.0010
-6.500 -0.2289 0.01561 0.01153 -0.1230 0.9125 0.0011
-6.250 -0.2044 0.01358 0.00916 -0.1229 0.9060 0.0012
-6.000 -0.1791 0.01239 0.00776 -0.1228 0.9004 0.0014
-5.750 -0.1532 0.01156 0.00678 -0.1227 0.8952 0.0017
-5.500 -0.1265 0.01097 0.00607 -0.1227 0.8910 0.0019
-5.250 -0.0992 0.01095 0.00598 -0.1229 0.8866 0.0022
-5.000 -0.0725 0.01049 0.00544 -0.1229 0.8822 0.0023
-4.750 -0.0473 0.00927 0.00401 -0.1227 0.8782 0.0027
-4.500 -0.0207 0.00875 0.00342 -0.1228 0.8744 0.0034
-4.250 0.0065 0.00845 0.00308 -0.1229 0.8707 0.0041
-4.000 0.0341 0.00801 0.00252 -0.1229 0.8672 0.0041
-3.750 0.0619 0.00767 0.00206 -0.1230 0.8641 0.0042
-3.500 0.0898 0.00744 0.00173 -0.1231 0.8609 0.0044
-3.250 0.1179 0.00726 0.00148 -0.1232 0.8576 0.0058
-3.000 0.1453 0.00675 0.00123 -0.1235 0.8545 0.0882
-2.750 0.1724 0.00605 0.00102 -0.1241 0.8517 0.2447
-2.500 0.2000 0.00574 0.00092 -0.1244 0.8488 0.3222
-2.250 0.2277 0.00552 0.00086 -0.1246 0.8457 0.3855
-2.000 0.2557 0.00543 0.00082 -0.1248 0.8428 0.4185
-1.750 0.2838 0.00536 0.00079 -0.1250 0.8402 0.4503
-1.500 0.3118 0.00528 0.00077 -0.1252 0.8375 0.4805
-1.250 0.3398 0.00524 0.00077 -0.1253 0.8345 0.5014
-1.000 0.3678 0.00521 0.00077 -0.1255 0.8313 0.5163
-0.750 0.3958 0.00521 0.00076 -0.1256 0.8277 0.5269
-0.500 0.4236 0.00520 0.00077 -0.1256 0.8232 0.5352
0.000 0.4786 0.00520 0.00079 -0.1256 0.8110 0.5514
0.250 0.5059 0.00520 0.00081 -0.1256 0.8034 0.5596
0.500 0.5330 0.00521 0.00083 -0.1255 0.7952 0.5686
0.750 0.5599 0.00523 0.00085 -0.1253 0.7854 0.5776
1.000 0.5865 0.00526 0.00090 -0.1251 0.7729 0.5868
1.500 0.6368 0.00541 0.00097 -0.1239 0.7240 0.6071
1.750 0.6578 0.00568 0.00105 -0.1225 0.6676 0.6176
2.000 0.6744 0.00628 0.00127 -0.1202 0.5716 0.6285
2.250 0.6783 0.00793 0.00185 -0.1158 0.3247 0.6393
2.500 0.6875 0.00947 0.00241 -0.1127 0.0986 0.6510
2.750 0.7126 0.00968 0.00264 -0.1123 0.0794 0.6648
3.000 0.7343 0.01020 0.00295 -0.1113 0.0240 0.6797
3.250 0.7582 0.01053 0.00322 -0.1106 0.0041 0.6959
3.500 0.7833 0.01074 0.00347 -0.1102 0.0015 0.7140
3.750 0.8085 0.01092 0.00375 -0.1097 0.0012 0.7337
4.250 0.8577 0.01138 0.00444 -0.1085 0.0011 0.7816
4.500 0.8812 0.01168 0.00494 -0.1076 0.0011 0.8104
4.750 0.9034 0.01202 0.00546 -0.1065 0.0011 0.8470
5.000 0.9210 0.01235 0.00605 -0.1041 0.0011 0.9104
5.250 0.9412 0.01289 0.00677 -0.1025 0.0011 1.0000
5.500 0.9615 0.01377 0.00779 -0.1009 0.0011 1.0000
5.750 0.9808 0.01490 0.00906 -0.0991 0.0012 1.0000
6.000 1.0004 0.01631 0.01064 -0.0974 0.0013 1.0000
6.250 1.0217 0.01817 0.01269 -0.0959 0.0014 1.0000
6.500 1.0447 0.02073 0.01551 -0.0946 0.0015 1.0000
6.750 1.0662 0.02375 0.01886 -0.0930 0.0017 1.0000
7.750 1.1214 0.03963 0.03619 -0.0811 0.0032 1.0000
8.000 1.1277 0.04315 0.03996 -0.0779 0.0031 1.0000
8.250 1.1306 0.04694 0.04401 -0.0745 0.0030 1.0000
8.500 1.1305 0.05074 0.04804 -0.0710 0.0030 1.0000
8.750 1.1273 0.05446 0.05197 -0.0675 0.0029 1.0000
9.000 1.1207 0.05808 0.05577 -0.0639 0.0028 1.0000
9.250 1.1073 0.06140 0.05926 -0.0594 0.0028 1.0000
9.500 1.0897 0.06473 0.06273 -0.0550 0.0028 1.0000
9.750 1.0717 0.06821 0.06633 -0.0517 0.0028 1.0000
10.000 1.0506 0.07273 0.07099 -0.0496 0.0028 1.0000
10.250 1.0282 0.07800 0.07639 -0.0489 0.0028 1.0000
10.500 1.0067 0.08376 0.08226 -0.0500 0.0028 1.0000
10.750 0.9824 0.09153 0.09014 -0.0534 0.0029 1.0000
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Polar data table (+)
Polar graphs
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