NACA M12 AIRFOIL (m12-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M12 AIRFOIL (m12-il) Reynolds number: 500,000 Max Cl/Cd: 77.16 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m12-il-500000-n5.txt Download as CSV file: xf-m12-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M12 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9833 0.05114 0.04800 -0.0528 1.0000 0.0194
-13.500 -1.0073 0.04528 0.04189 -0.0555 1.0000 0.0195
-13.250 -1.0226 0.04150 0.03788 -0.0553 1.0000 0.0197
-13.000 -1.0331 0.03863 0.03478 -0.0537 1.0000 0.0199
-12.750 -1.0403 0.03629 0.03221 -0.0510 1.0000 0.0202
-12.500 -1.0427 0.03443 0.03014 -0.0481 1.0000 0.0205
-12.250 -1.0372 0.03280 0.02827 -0.0460 1.0000 0.0209
-12.000 -1.0272 0.03149 0.02675 -0.0443 1.0000 0.0211
-11.750 -1.0181 0.02990 0.02504 -0.0425 1.0000 0.0215
-11.500 -1.0031 0.02894 0.02402 -0.0411 1.0000 0.0217
-11.250 -0.9867 0.02811 0.02312 -0.0398 1.0000 0.0220
-11.000 -0.9697 0.02731 0.02224 -0.0386 1.0000 0.0223
-10.750 -0.9520 0.02658 0.02144 -0.0374 1.0000 0.0226
-10.500 -0.9343 0.02584 0.02060 -0.0361 1.0000 0.0230
-10.250 -0.9171 0.02503 0.01969 -0.0346 1.0000 0.0234
-10.000 -0.9004 0.02417 0.01871 -0.0330 1.0000 0.0238
-9.750 -0.8840 0.02331 0.01771 -0.0313 1.0000 0.0242
-9.500 -0.8674 0.02253 0.01681 -0.0295 1.0000 0.0246
-9.250 -0.8449 0.02178 0.01593 -0.0289 0.9986 0.0250
-9.000 -0.8146 0.02104 0.01505 -0.0300 0.9953 0.0255
-8.750 -0.7843 0.02032 0.01419 -0.0309 0.9917 0.0257
-8.500 -0.7563 0.01906 0.01283 -0.0316 0.9870 0.0262
-8.250 -0.7268 0.01815 0.01186 -0.0324 0.9821 0.0266
-8.000 -0.6975 0.01750 0.01117 -0.0331 0.9756 0.0271
-7.750 -0.6676 0.01693 0.01055 -0.0339 0.9689 0.0276
-7.500 -0.6380 0.01635 0.00991 -0.0345 0.9607 0.0280
-7.250 -0.6099 0.01578 0.00928 -0.0347 0.9508 0.0284
-7.000 -0.5822 0.01526 0.00869 -0.0348 0.9403 0.0288
-6.500 -0.5304 0.01433 0.00761 -0.0340 0.9166 0.0296
-6.250 -0.5053 0.01392 0.00713 -0.0335 0.9046 0.0300
-6.000 -0.4801 0.01356 0.00668 -0.0329 0.8930 0.0305
-5.750 -0.4547 0.01325 0.00629 -0.0323 0.8811 0.0309
-5.500 -0.4290 0.01296 0.00594 -0.0319 0.8692 0.0312
-5.250 -0.4043 0.01249 0.00541 -0.0312 0.8576 0.0318
-5.000 -0.3790 0.01213 0.00499 -0.0307 0.8462 0.0325
-4.750 -0.3532 0.01183 0.00464 -0.0303 0.8343 0.0331
-4.500 -0.3270 0.01157 0.00433 -0.0299 0.8226 0.0337
-4.250 -0.3005 0.01135 0.00405 -0.0296 0.8113 0.0345
-3.750 -0.2471 0.01095 0.00354 -0.0290 0.7885 0.0362
-3.500 -0.2202 0.01078 0.00331 -0.0288 0.7774 0.0371
-3.250 -0.1932 0.01062 0.00309 -0.0285 0.7664 0.0385
-3.000 -0.1662 0.01044 0.00289 -0.0283 0.7552 0.0411
-2.750 -0.1390 0.01029 0.00271 -0.0281 0.7446 0.0445
-2.500 -0.1121 0.01012 0.00254 -0.0279 0.7341 0.0521
-2.250 -0.0852 0.00991 0.00240 -0.0277 0.7231 0.0721
-2.000 -0.0581 0.00974 0.00228 -0.0276 0.7128 0.0924
-1.750 -0.0311 0.00960 0.00217 -0.0274 0.7022 0.1158
-1.500 -0.0039 0.00944 0.00208 -0.0273 0.6913 0.1396
-1.250 0.0230 0.00926 0.00199 -0.0272 0.6809 0.1731
-0.750 0.0743 0.00856 0.00181 -0.0266 0.6587 0.3393
-0.500 0.0993 0.00817 0.00172 -0.0262 0.6478 0.4385
-0.250 0.1218 0.00760 0.00165 -0.0253 0.6366 0.5898
0.000 0.1443 0.00718 0.00164 -0.0242 0.6247 0.7108
0.250 0.1681 0.00696 0.00169 -0.0230 0.6130 0.7938
0.500 0.1925 0.00690 0.00181 -0.0219 0.6008 0.8634
0.750 0.2186 0.00698 0.00192 -0.0210 0.5878 0.9037
1.000 0.2455 0.00711 0.00201 -0.0205 0.5720 0.9260
1.250 0.2741 0.00725 0.00209 -0.0204 0.5550 0.9398
1.500 0.3044 0.00741 0.00218 -0.0207 0.5408 0.9522
1.750 0.3359 0.00756 0.00228 -0.0214 0.5282 0.9620
2.000 0.3687 0.00770 0.00236 -0.0224 0.5159 0.9674
2.250 0.3975 0.00780 0.00241 -0.0226 0.5052 0.9720
2.500 0.4311 0.00793 0.00248 -0.0239 0.4932 0.9739
2.750 0.4647 0.00804 0.00255 -0.0252 0.4811 0.9758
3.000 0.4978 0.00816 0.00263 -0.0264 0.4702 0.9781
3.250 0.5294 0.00829 0.00271 -0.0273 0.4583 0.9809
3.750 0.5938 0.00855 0.00290 -0.0294 0.4333 0.9853
4.000 0.6268 0.00870 0.00301 -0.0307 0.4191 0.9870
4.250 0.6585 0.00891 0.00313 -0.0317 0.3972 0.9891
4.500 0.6894 0.00916 0.00327 -0.0326 0.3699 0.9915
4.750 0.7188 0.00950 0.00344 -0.0332 0.3347 0.9938
5.000 0.7497 0.00989 0.00365 -0.0343 0.2942 0.9954
5.250 0.7806 0.01021 0.00386 -0.0353 0.2675 0.9971
5.500 0.8111 0.01055 0.00409 -0.0362 0.2442 0.9988
5.750 0.8395 0.01088 0.00434 -0.0367 0.2236 1.0000
6.000 0.8605 0.01118 0.00457 -0.0355 0.2054 1.0000
6.250 0.8808 0.01152 0.00483 -0.0343 0.1849 1.0000
6.500 0.9005 0.01191 0.00512 -0.0329 0.1617 1.0000
6.750 0.9192 0.01237 0.00544 -0.0314 0.1362 1.0000
7.000 0.9376 0.01284 0.00580 -0.0299 0.1133 1.0000
7.250 0.9562 0.01330 0.00617 -0.0283 0.0958 1.0000
7.500 0.9750 0.01374 0.00655 -0.0268 0.0819 1.0000
7.750 0.9939 0.01418 0.00694 -0.0253 0.0705 1.0000
8.000 1.0126 0.01463 0.00735 -0.0239 0.0615 1.0000
8.250 1.0320 0.01504 0.00774 -0.0225 0.0553 1.0000
8.500 1.0514 0.01547 0.00817 -0.0211 0.0504 1.0000
8.750 1.0711 0.01589 0.00860 -0.0199 0.0465 1.0000
9.000 1.0902 0.01638 0.00908 -0.0186 0.0432 1.0000
9.250 1.1104 0.01678 0.00952 -0.0175 0.0410 1.0000
9.500 1.1297 0.01725 0.01002 -0.0163 0.0388 1.0000
9.750 1.1479 0.01780 0.01058 -0.0149 0.0367 1.0000
10.000 1.1667 0.01829 0.01110 -0.0137 0.0352 1.0000
10.250 1.1852 0.01877 0.01164 -0.0124 0.0337 1.0000
10.500 1.2024 0.01932 0.01223 -0.0110 0.0322 1.0000
10.750 1.2170 0.01993 0.01287 -0.0092 0.0308 1.0000
11.000 1.2297 0.02058 0.01356 -0.0071 0.0296 1.0000
11.250 1.2443 0.02117 0.01421 -0.0054 0.0285 1.0000
11.500 1.2583 0.02183 0.01493 -0.0037 0.0273 1.0000
11.750 1.2714 0.02259 0.01574 -0.0021 0.0261 1.0000
12.000 1.2827 0.02351 0.01670 -0.0004 0.0250 1.0000
12.250 1.2947 0.02442 0.01768 0.0010 0.0241 1.0000
12.500 1.3073 0.02534 0.01867 0.0023 0.0231 1.0000
12.750 1.3192 0.02635 0.01975 0.0035 0.0220 1.0000
13.000 1.3298 0.02750 0.02095 0.0046 0.0210 1.0000
13.250 1.3383 0.02888 0.02238 0.0057 0.0201 1.0000
13.500 1.3482 0.03020 0.02380 0.0066 0.0194 1.0000
13.750 1.3569 0.03167 0.02536 0.0074 0.0186 1.0000
14.000 1.3648 0.03328 0.02704 0.0080 0.0178 1.0000
14.250 1.3716 0.03505 0.02888 0.0086 0.0172 1.0000
14.500 1.3764 0.03707 0.03097 0.0090 0.0166 1.0000
14.750 1.3800 0.03928 0.03326 0.0094 0.0160 1.0000
15.000 1.3839 0.04154 0.03564 0.0095 0.0155 1.0000
15.250 1.3866 0.04397 0.03817 0.0096 0.0150 1.0000
15.500 1.3883 0.04659 0.04088 0.0095 0.0146 1.0000
15.750 1.3887 0.04944 0.04382 0.0092 0.0141 1.0000
16.000 1.3874 0.05253 0.04701 0.0087 0.0138 1.0000
16.250 1.3843 0.05596 0.05053 0.0081 0.0134 1.0000
16.500 1.3791 0.05980 0.05447 0.0072 0.0131 1.0000
16.750 1.3728 0.06388 0.05865 0.0061 0.0129 1.0000
17.000 1.3675 0.06792 0.06282 0.0049 0.0127 1.0000
17.250 1.3612 0.07220 0.06722 0.0036 0.0125 1.0000
17.500 1.3535 0.07678 0.07192 0.0020 0.0123 1.0000
17.750 1.3449 0.08155 0.07682 0.0003 0.0121 1.0000
18.000 1.3353 0.08659 0.08198 -0.0016 0.0119 1.0000
18.250 1.3249 0.09186 0.08738 -0.0036 0.0118 1.0000
18.500 1.3137 0.09731 0.09294 -0.0058 0.0116 1.0000
18.750 1.3019 0.10297 0.09871 -0.0082 0.0115 1.0000
19.000 1.2895 0.10885 0.10472 -0.0108 0.0114 1.0000
19.250 1.2768 0.11488 0.11085 -0.0136 0.0112 1.0000
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