NACA M11 AIRFOIL (m11-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M11 AIRFOIL (m11-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.59 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m11-il-1000000.txt Download as CSV file: xf-m11-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5343 0.08881 0.08716 -0.0142 1.0000 0.0149
-9.250 -0.5398 0.08339 0.08176 -0.0176 1.0000 0.0154
-9.000 -0.5463 0.07852 0.07691 -0.0207 1.0000 0.0149
-8.750 -0.5648 0.07234 0.07075 -0.0259 1.0000 0.0143
-8.500 -0.6072 0.05990 0.05820 -0.0314 1.0000 0.0135
-8.250 -0.6295 0.05011 0.04820 -0.0322 1.0000 0.0136
-8.000 -0.7215 0.02430 0.02086 -0.0217 1.0000 0.0158
-7.750 -0.7058 0.02335 0.01972 -0.0195 1.0000 0.0163
-7.500 -0.7037 0.02048 0.01651 -0.0155 1.0000 0.0170
-7.250 -0.6815 0.02111 0.01724 -0.0145 1.0000 0.0174
-7.000 -0.6473 0.02108 0.01721 -0.0163 0.9984 0.0179
-6.750 -0.6136 0.02086 0.01696 -0.0179 0.9963 0.0185
-6.500 -0.5821 0.01960 0.01551 -0.0191 0.9940 0.0195
-6.250 -0.5524 0.01847 0.01419 -0.0197 0.9905 0.0205
-6.000 -0.5175 0.01890 0.01456 -0.0211 0.9876 0.0212
-5.750 -0.4909 0.01573 0.01105 -0.0218 0.9844 0.0227
-5.500 -0.4587 0.01528 0.01057 -0.0230 0.9812 0.0235
-5.250 -0.4277 0.01464 0.00987 -0.0238 0.9762 0.0242
-5.000 -0.3940 0.01401 0.00917 -0.0252 0.9723 0.0252
-4.750 -0.3615 0.01338 0.00845 -0.0263 0.9665 0.0261
-4.500 -0.3294 0.01266 0.00763 -0.0271 0.9587 0.0267
-4.250 -0.2982 0.01215 0.00704 -0.0278 0.9487 0.0273
-4.000 -0.2679 0.01206 0.00688 -0.0282 0.9363 0.0278
-3.750 -0.2423 0.01066 0.00533 -0.0277 0.9212 0.0289
-3.500 -0.2172 0.00996 0.00454 -0.0270 0.9039 0.0293
-3.250 -0.1928 0.00946 0.00396 -0.0261 0.8857 0.0296
-2.750 -0.1446 0.00875 0.00308 -0.0243 0.8490 0.0305
-2.500 -0.1203 0.00849 0.00274 -0.0234 0.8309 0.0310
-2.250 -0.0957 0.00829 0.00247 -0.0226 0.8132 0.0321
-2.000 -0.0710 0.00810 0.00220 -0.0218 0.7965 0.0329
-1.750 -0.0460 0.00794 0.00196 -0.0210 0.7810 0.0337
-1.500 -0.0206 0.00781 0.00177 -0.0204 0.7664 0.0345
-1.250 0.0050 0.00769 0.00159 -0.0198 0.7521 0.0352
-1.000 0.0309 0.00760 0.00144 -0.0192 0.7386 0.0359
-0.750 0.0568 0.00752 0.00131 -0.0187 0.7255 0.0365
-0.500 0.0829 0.00746 0.00121 -0.0182 0.7124 0.0369
-0.250 0.1089 0.00738 0.00107 -0.0177 0.6997 0.0396
0.000 0.1349 0.00730 0.00099 -0.0172 0.6868 0.0472
0.250 0.1562 0.00675 0.00093 -0.0160 0.6739 0.2226
0.500 0.1668 0.00546 0.00086 -0.0128 0.6616 0.6289
0.750 0.1778 0.00468 0.00087 -0.0088 0.6495 0.8722
1.000 0.2738 0.00493 0.00126 -0.0238 0.6315 0.9712
1.250 0.3218 0.00522 0.00149 -0.0281 0.6151 0.9821
1.500 0.3721 0.00544 0.00162 -0.0330 0.5941 0.9876
1.750 0.4173 0.00562 0.00169 -0.0368 0.5705 0.9927
2.000 0.4604 0.00571 0.00170 -0.0402 0.5470 0.9960
2.250 0.4938 0.00580 0.00167 -0.0415 0.5183 0.9978
2.500 0.5267 0.00592 0.00166 -0.0428 0.4850 0.9995
2.750 0.5538 0.00602 0.00168 -0.0427 0.4605 1.0000
3.000 0.5766 0.00614 0.00172 -0.0417 0.4373 1.0000
3.250 0.5995 0.00629 0.00177 -0.0407 0.4115 1.0000
3.500 0.6223 0.00648 0.00185 -0.0398 0.3793 1.0000
3.750 0.6452 0.00668 0.00195 -0.0388 0.3483 1.0000
4.000 0.6677 0.00695 0.00207 -0.0378 0.3108 1.0000
4.250 0.6892 0.00734 0.00223 -0.0368 0.2567 1.0000
4.500 0.7098 0.00786 0.00245 -0.0355 0.1912 1.0000
4.750 0.7306 0.00838 0.00273 -0.0343 0.1387 1.0000
5.000 0.7518 0.00886 0.00301 -0.0332 0.0968 1.0000
5.250 0.7736 0.00926 0.00328 -0.0321 0.0700 1.0000
5.500 0.7961 0.00959 0.00354 -0.0312 0.0556 1.0000
5.750 0.8188 0.00989 0.00382 -0.0302 0.0463 1.0000
6.000 0.8412 0.01024 0.00412 -0.0292 0.0384 1.0000
6.250 0.8643 0.01048 0.00437 -0.0283 0.0339 1.0000
6.500 0.8864 0.01085 0.00472 -0.0273 0.0282 1.0000
6.750 0.9088 0.01118 0.00504 -0.0263 0.0244 1.0000
7.000 0.9303 0.01160 0.00549 -0.0251 0.0212 1.0000
7.250 0.9527 0.01192 0.00581 -0.0241 0.0192 1.0000
7.500 0.9730 0.01245 0.00636 -0.0228 0.0169 1.0000
7.750 0.9943 0.01286 0.00682 -0.0216 0.0159 1.0000
8.000 1.0156 0.01325 0.00725 -0.0205 0.0150 1.0000
8.250 1.0364 0.01367 0.00771 -0.0193 0.0141 1.0000
8.500 1.0559 0.01423 0.00830 -0.0179 0.0132 1.0000
8.750 1.0706 0.01523 0.00941 -0.0157 0.0122 1.0000
9.000 1.0908 0.01567 0.00989 -0.0144 0.0119 1.0000
9.250 1.1103 0.01616 0.01046 -0.0130 0.0115 1.0000
9.500 1.1296 0.01665 0.01099 -0.0117 0.0109 1.0000
9.750 1.1480 0.01718 0.01157 -0.0102 0.0104 1.0000
10.000 1.1651 0.01782 0.01225 -0.0086 0.0100 1.0000
10.250 1.1789 0.01871 0.01321 -0.0064 0.0095 1.0000
10.500 1.1823 0.02054 0.01521 -0.0028 0.0090 1.0000
10.750 1.1975 0.02125 0.01600 -0.0009 0.0089 1.0000
11.000 1.2121 0.02194 0.01678 0.0009 0.0087 1.0000
11.250 1.2248 0.02276 0.01769 0.0031 0.0085 1.0000
11.500 1.2362 0.02364 0.01866 0.0054 0.0082 1.0000
11.750 1.2403 0.02468 0.01982 0.0088 0.0082 1.0000
12.000 1.2435 0.02574 0.02098 0.0122 0.0080 1.0000
12.250 1.2486 0.02679 0.02213 0.0150 0.0078 1.0000
12.500 1.2536 0.02795 0.02340 0.0174 0.0076 1.0000
12.750 1.2590 0.02917 0.02471 0.0194 0.0075 1.0000
13.000 1.2625 0.03064 0.02628 0.0212 0.0073 1.0000
13.250 1.2706 0.03176 0.02745 0.0223 0.0071 1.0000
13.500 1.2661 0.03430 0.03014 0.0237 0.0070 1.0000
13.750 1.2688 0.03620 0.03211 0.0243 0.0068 1.0000
14.000 1.2654 0.03896 0.03501 0.0248 0.0068 1.0000
14.250 1.2507 0.04324 0.03946 0.0246 0.0066 1.0000
14.500 1.2289 0.04882 0.04528 0.0236 0.0065 1.0000
14.750 1.2181 0.05329 0.04990 0.0221 0.0064 1.0000
15.000 1.2070 0.05810 0.05486 0.0202 0.0064 1.0000
15.250 1.1874 0.06445 0.06140 0.0173 0.0064 1.0000
15.500 1.1609 0.07240 0.06954 0.0132 0.0064 1.0000
15.750 1.1519 0.07777 0.07501 0.0103 0.0064 1.0000
16.000 1.1479 0.08248 0.07980 0.0078 0.0065 1.0000
16.250 1.1147 0.09299 0.09051 0.0019 0.0064 1.0000
16.500 1.0756 0.10551 0.10323 -0.0051 0.0064 1.0000
16.750 1.0640 0.11251 0.11030 -0.0088 0.0064 1.0000
17.000 1.0733 0.11487 0.11267 -0.0099 0.0065 1.0000
17.250 1.0437 0.12634 0.12428 -0.0159 0.0066 1.0000
17.500 1.0141 0.13830 0.13636 -0.0220 0.0066 1.0000
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