NACA M11 AIRFOIL (m11-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M11 AIRFOIL (m11-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.5 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m11-il-1000000-n5.txt Download as CSV file: xf-m11-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M11 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6171 0.16991 0.16814 0.0195 1.0000 0.0038
-15.000 -0.6112 0.16663 0.16485 0.0181 1.0000 0.0039
-12.000 -1.0568 0.02867 0.02560 -0.0374 1.0000 0.0054
-11.750 -1.0515 0.02596 0.02261 -0.0351 1.0000 0.0056
-11.500 -1.0415 0.02391 0.02034 -0.0330 1.0000 0.0059
-11.250 -1.0282 0.02232 0.01857 -0.0312 1.0000 0.0061
-11.000 -1.0131 0.02098 0.01707 -0.0295 1.0000 0.0064
-10.750 -0.9964 0.01988 0.01581 -0.0279 1.0000 0.0067
-10.500 -0.9791 0.01886 0.01465 -0.0264 1.0000 0.0071
-10.250 -0.9608 0.01796 0.01361 -0.0248 1.0000 0.0074
-10.000 -0.9420 0.01716 0.01269 -0.0234 1.0000 0.0077
-9.750 -0.9228 0.01642 0.01185 -0.0219 1.0000 0.0082
-9.500 -0.9034 0.01573 0.01108 -0.0205 1.0000 0.0089
-9.250 -0.8838 0.01511 0.01039 -0.0190 1.0000 0.0097
-9.000 -0.8643 0.01453 0.00972 -0.0175 1.0000 0.0106
-8.750 -0.8378 0.01416 0.00932 -0.0174 0.9992 0.0118
-8.500 -0.8059 0.01405 0.00924 -0.0185 0.9973 0.0132
-8.000 -0.7453 0.01337 0.00846 -0.0199 0.9912 0.0150
-7.750 -0.7126 0.01347 0.00861 -0.0210 0.9879 0.0158
-7.500 -0.6796 0.01350 0.00865 -0.0221 0.9847 0.0165
-7.250 -0.6479 0.01352 0.00866 -0.0230 0.9797 0.0174
-7.000 -0.6138 0.01336 0.00846 -0.0245 0.9759 0.0183
-6.750 -0.5817 0.01310 0.00815 -0.0255 0.9700 0.0191
-6.500 -0.5476 0.01290 0.00791 -0.0270 0.9640 0.0197
-6.250 -0.5146 0.01286 0.00782 -0.0282 0.9553 0.0201
-6.000 -0.4818 0.01278 0.00769 -0.0293 0.9444 0.0204
-5.750 -0.4554 0.01165 0.00641 -0.0292 0.9298 0.0214
-5.500 -0.4286 0.01129 0.00599 -0.0290 0.9128 0.0220
-5.250 -0.4026 0.01111 0.00574 -0.0286 0.8944 0.0226
-5.000 -0.3775 0.01087 0.00540 -0.0280 0.8756 0.0231
-4.750 -0.3526 0.01064 0.00508 -0.0273 0.8567 0.0236
-4.500 -0.3277 0.01042 0.00477 -0.0266 0.8387 0.0242
-4.250 -0.3032 0.01013 0.00438 -0.0259 0.8215 0.0245
-4.000 -0.2784 0.00987 0.00402 -0.0251 0.8055 0.0248
-3.750 -0.2536 0.00960 0.00367 -0.0244 0.7901 0.0251
-3.500 -0.2287 0.00936 0.00334 -0.0237 0.7754 0.0253
-3.250 -0.2037 0.00912 0.00302 -0.0231 0.7612 0.0255
-3.000 -0.1786 0.00891 0.00273 -0.0224 0.7474 0.0257
-2.750 -0.1533 0.00871 0.00247 -0.0218 0.7340 0.0259
-2.500 -0.1276 0.00858 0.00227 -0.0213 0.7205 0.0263
-2.250 -0.1021 0.00842 0.00205 -0.0207 0.7065 0.0266
-2.000 -0.0764 0.00829 0.00184 -0.0202 0.6927 0.0268
-1.750 -0.0506 0.00817 0.00166 -0.0197 0.6789 0.0271
-1.500 -0.0247 0.00807 0.00151 -0.0192 0.6659 0.0275
-1.250 0.0015 0.00799 0.00139 -0.0188 0.6530 0.0279
-1.000 0.0277 0.00794 0.00129 -0.0184 0.6405 0.0283
-0.750 0.0540 0.00790 0.00121 -0.0180 0.6269 0.0286
-0.500 0.0803 0.00782 0.00108 -0.0176 0.6141 0.0296
-0.250 0.1066 0.00778 0.00099 -0.0172 0.6007 0.0309
0.000 0.1330 0.00775 0.00093 -0.0168 0.5876 0.0324
0.250 0.1594 0.00774 0.00088 -0.0165 0.5748 0.0338
0.500 0.1859 0.00773 0.00085 -0.0161 0.5622 0.0357
0.750 0.2123 0.00773 0.00084 -0.0158 0.5494 0.0383
1.250 0.2624 0.00744 0.00084 -0.0147 0.5247 0.1674
1.500 0.2599 0.00547 0.00082 -0.0086 0.5155 0.8100
2.000 0.3848 0.00570 0.00129 -0.0241 0.4649 0.9768
2.250 0.4193 0.00588 0.00137 -0.0256 0.4394 0.9807
2.500 0.4477 0.00610 0.00147 -0.0257 0.4095 0.9850
2.750 0.4860 0.00654 0.00162 -0.0283 0.3413 0.9885
3.000 0.5232 0.00679 0.00174 -0.0306 0.3097 0.9919
3.250 0.5526 0.00700 0.00184 -0.0310 0.2842 0.9936
3.500 0.5820 0.00723 0.00197 -0.0315 0.2558 0.9949
3.750 0.6121 0.00752 0.00210 -0.0323 0.2165 0.9959
4.000 0.6411 0.00796 0.00230 -0.0329 0.1625 0.9972
4.250 0.6706 0.00829 0.00249 -0.0335 0.1301 0.9984
4.500 0.7000 0.00866 0.00270 -0.0342 0.0960 0.9994
4.750 0.7270 0.00904 0.00293 -0.0343 0.0672 1.0000
5.000 0.7503 0.00927 0.00314 -0.0334 0.0574 1.0000
5.250 0.7736 0.00952 0.00335 -0.0326 0.0486 1.0000
5.500 0.7967 0.00977 0.00357 -0.0317 0.0417 1.0000
5.750 0.8202 0.00999 0.00379 -0.0309 0.0378 1.0000
6.000 0.8431 0.01026 0.00404 -0.0300 0.0322 1.0000
6.250 0.8663 0.01050 0.00428 -0.0292 0.0285 1.0000
6.500 0.8888 0.01081 0.00456 -0.0282 0.0228 1.0000
6.750 0.9113 0.01112 0.00486 -0.0273 0.0184 1.0000
7.000 0.9335 0.01146 0.00518 -0.0263 0.0146 1.0000
7.250 0.9555 0.01181 0.00554 -0.0252 0.0126 1.0000
7.500 0.9772 0.01218 0.00593 -0.0242 0.0107 1.0000
7.750 0.9993 0.01251 0.00629 -0.0232 0.0101 1.0000
8.000 1.0210 0.01286 0.00668 -0.0221 0.0094 1.0000
8.250 1.0420 0.01327 0.00711 -0.0210 0.0086 1.0000
8.500 1.0621 0.01376 0.00765 -0.0197 0.0077 1.0000
8.750 1.0830 0.01415 0.00809 -0.0185 0.0073 1.0000
9.000 1.1036 0.01457 0.00855 -0.0173 0.0069 1.0000
9.250 1.1236 0.01502 0.00905 -0.0161 0.0065 1.0000
9.500 1.1432 0.01550 0.00957 -0.0148 0.0062 1.0000
9.750 1.1624 0.01599 0.01010 -0.0134 0.0058 1.0000
10.000 1.1805 0.01657 0.01073 -0.0119 0.0055 1.0000
10.250 1.1963 0.01733 0.01159 -0.0100 0.0052 1.0000
10.500 1.2142 0.01787 0.01218 -0.0086 0.0051 1.0000
10.750 1.2313 0.01845 0.01283 -0.0069 0.0049 1.0000
11.000 1.2473 0.01910 0.01356 -0.0052 0.0048 1.0000
11.250 1.2622 0.01979 0.01433 -0.0033 0.0047 1.0000
11.500 1.2770 0.02045 0.01506 -0.0015 0.0045 1.0000
11.750 1.2904 0.02116 0.01584 0.0005 0.0043 1.0000
12.000 1.3041 0.02183 0.01657 0.0025 0.0041 1.0000
12.250 1.3138 0.02256 0.01740 0.0051 0.0040 1.0000
12.500 1.3199 0.02333 0.01823 0.0082 0.0039 1.0000
12.750 1.3239 0.02432 0.01932 0.0114 0.0039 1.0000
13.000 1.3313 0.02523 0.02029 0.0137 0.0037 1.0000
13.250 1.3354 0.02645 0.02161 0.0161 0.0036 1.0000
13.500 1.3321 0.02836 0.02365 0.0186 0.0034 1.0000
13.750 1.3356 0.02990 0.02530 0.0202 0.0034 1.0000
14.000 1.3377 0.03171 0.02723 0.0215 0.0034 1.0000
14.250 1.3416 0.03348 0.02911 0.0224 0.0034 1.0000
14.500 1.3419 0.03574 0.03149 0.0229 0.0033 1.0000
14.750 1.3399 0.03842 0.03430 0.0232 0.0033 1.0000
15.000 1.3410 0.04091 0.03690 0.0230 0.0033 1.0000
15.250 1.3328 0.04469 0.04083 0.0224 0.0032 1.0000
15.500 1.3237 0.04883 0.04512 0.0212 0.0032 1.0000
15.750 1.3189 0.05259 0.04901 0.0199 0.0032 1.0000
16.000 1.3057 0.05778 0.05435 0.0178 0.0032 1.0000
16.250 1.2935 0.06302 0.05972 0.0155 0.0031 1.0000
16.500 1.2786 0.06897 0.06581 0.0126 0.0031 1.0000
16.750 1.2583 0.07608 0.07306 0.0090 0.0031 1.0000
17.000 1.2385 0.08349 0.08061 0.0052 0.0031 1.0000
17.250 1.2152 0.09183 0.08909 0.0010 0.0030 1.0000
17.500 1.1878 0.10119 0.09857 -0.0038 0.0032 1.0000
17.750 1.1523 0.11255 0.11008 -0.0096 0.0032 1.0000
18.000 1.1178 0.12418 0.12185 -0.0154 0.0032 1.0000
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