MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 500,000 Max Cl/Cd: 125.75 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh121-il-500000.txt Download as CSV file: xf-mh121-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4272 0.10526 0.10304 -0.0332 1.0000 0.0080
-9.250 -0.4318 0.10266 0.10048 -0.0324 1.0000 0.0083
-9.000 -0.4391 0.10030 0.09817 -0.0309 1.0000 0.0083
-8.750 -0.4322 0.09629 0.09418 -0.0339 0.9988 0.0086
-8.500 -0.4209 0.09157 0.08946 -0.0387 0.9968 0.0089
-8.250 -0.4090 0.08679 0.08468 -0.0439 0.9947 0.0092
-8.000 -0.3985 0.08196 0.07986 -0.0490 0.9919 0.0094
-7.750 -0.3886 0.07684 0.07475 -0.0549 0.9875 0.0096
-7.500 -0.3765 0.07094 0.06886 -0.0629 0.9833 0.0099
-7.250 -0.3609 0.06305 0.06097 -0.0754 0.9762 0.0099
-7.000 -0.3391 0.05374 0.05149 -0.0905 0.9711 0.0100
-6.750 -0.3216 0.04767 0.04522 -0.0972 0.9658 0.0104
-6.500 -0.3010 0.04226 0.03956 -0.1020 0.9609 0.0110
-6.250 -0.2731 0.03714 0.03413 -0.1065 0.9586 0.0119
-6.000 -0.2355 0.03586 0.03257 -0.1081 0.9575 0.0147
-5.250 -0.1611 0.02014 0.01539 -0.1134 0.9474 0.0101
-5.000 -0.1271 0.01664 0.01140 -0.1144 0.9464 0.0091
-4.750 -0.0932 0.01515 0.00971 -0.1159 0.9456 0.0103
-4.500 -0.0590 0.01451 0.00897 -0.1174 0.9447 0.0133
-4.250 -0.0255 0.01277 0.00706 -0.1186 0.9439 0.0127
-4.000 -0.0035 0.01171 0.00589 -0.1174 0.9386 0.0122
-3.750 0.0276 0.01072 0.00475 -0.1182 0.9363 0.0122
-3.500 0.0605 0.01001 0.00386 -0.1193 0.9346 0.0130
-3.250 0.0939 0.00860 0.00297 -0.1211 0.9331 0.1819
-3.000 0.1255 0.00747 0.00285 -0.1231 0.9317 0.4833
-2.750 0.1534 0.00743 0.00275 -0.1232 0.9285 0.5073
-2.500 0.1810 0.00740 0.00270 -0.1232 0.9250 0.5307
-2.250 0.2115 0.00733 0.00263 -0.1239 0.9225 0.5497
-2.000 0.2431 0.00726 0.00256 -0.1247 0.9204 0.5717
-1.750 0.2750 0.00721 0.00252 -0.1257 0.9186 0.5940
-1.500 0.3016 0.00722 0.00250 -0.1255 0.9150 0.6093
-1.250 0.3290 0.00721 0.00250 -0.1255 0.9115 0.6213
-1.000 0.3588 0.00716 0.00247 -0.1260 0.9087 0.6327
-0.750 0.3897 0.00711 0.00244 -0.1268 0.9064 0.6441
-0.500 0.4183 0.00711 0.00246 -0.1270 0.9033 0.6561
-0.250 0.4443 0.00711 0.00252 -0.1267 0.8988 0.6686
0.000 0.4735 0.00706 0.00252 -0.1270 0.8952 0.6823
0.250 0.5046 0.00701 0.00250 -0.1277 0.8920 0.6970
0.500 0.5290 0.00700 0.00257 -0.1270 0.8860 0.7127
0.750 0.5582 0.00694 0.00256 -0.1272 0.8810 0.7300
1.000 0.5847 0.00688 0.00262 -0.1268 0.8747 0.7484
1.500 0.6375 0.00672 0.00262 -0.1259 0.8594 0.7926
1.750 0.6635 0.00660 0.00259 -0.1252 0.8497 0.8189
2.000 0.6875 0.00647 0.00255 -0.1240 0.8378 0.8501
2.250 0.7093 0.00634 0.00253 -0.1223 0.8259 0.8898
2.500 0.7318 0.00617 0.00255 -0.1207 0.8138 0.9591
2.750 0.7600 0.00614 0.00254 -0.1207 0.7963 1.0000
3.000 0.7784 0.00619 0.00236 -0.1182 0.7301 1.0000
3.250 0.7711 0.00781 0.00267 -0.1107 0.4774 1.0000
3.500 0.7771 0.00934 0.00328 -0.1070 0.2873 1.0000
3.750 0.7923 0.01040 0.00377 -0.1050 0.1671 1.0000
4.000 0.8066 0.01165 0.00436 -0.1028 0.0461 1.0000
4.250 0.8266 0.01247 0.00499 -0.1013 0.0057 1.0000
4.500 0.8497 0.01300 0.00567 -0.1002 0.0049 1.0000
4.750 0.8714 0.01371 0.00658 -0.0989 0.0046 1.0000
5.000 0.8910 0.01468 0.00770 -0.0971 0.0045 1.0000
5.250 0.9091 0.01591 0.00907 -0.0950 0.0046 1.0000
5.500 0.9278 0.01753 0.01086 -0.0930 0.0048 1.0000
5.750 0.9510 0.01980 0.01332 -0.0917 0.0051 1.0000
6.000 0.9801 0.02429 0.01813 -0.0913 0.0061 1.0000
6.250 1.0048 0.02421 0.01809 -0.0904 0.0069 1.0000
10.250 0.8413 0.09612 0.09429 -0.0509 0.0146 1.0000
10.500 0.8199 0.10433 0.10258 -0.0560 0.0146 1.0000
10.750 0.8044 0.11332 0.11165 -0.0623 0.0146 1.0000
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Polar data table (+)
Polar graphs
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