NACA M12 AIRFOIL (m12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M12 AIRFOIL (m12-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.79 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m12-il-1000000.txt Download as CSV file: xf-m12-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -1.0633 0.04907 0.04644 -0.0536 1.0000 0.0183
-14.250 -1.0731 0.04494 0.04217 -0.0557 1.0000 0.0184
-14.000 -1.0774 0.04209 0.03921 -0.0562 1.0000 0.0185
-13.750 -1.0781 0.03996 0.03699 -0.0557 1.0000 0.0187
-13.500 -1.0779 0.03814 0.03507 -0.0545 1.0000 0.0188
-13.250 -1.0776 0.03650 0.03333 -0.0527 1.0000 0.0190
-13.000 -1.0753 0.03516 0.03188 -0.0505 1.0000 0.0192
-12.750 -1.0713 0.03402 0.03065 -0.0480 1.0000 0.0195
-12.500 -1.0633 0.03280 0.02932 -0.0461 1.0000 0.0198
-12.250 -1.0532 0.03157 0.02795 -0.0443 1.0000 0.0201
-12.000 -1.0417 0.03037 0.02660 -0.0426 1.0000 0.0205
-11.750 -1.0280 0.02935 0.02543 -0.0411 1.0000 0.0208
-11.500 -1.0119 0.02858 0.02453 -0.0397 1.0000 0.0210
-11.250 -1.0074 0.02595 0.02161 -0.0372 1.0000 0.0214
-11.000 -0.9932 0.02452 0.02009 -0.0357 1.0000 0.0218
-10.750 -0.9747 0.02384 0.01938 -0.0345 1.0000 0.0221
-10.500 -0.9557 0.02335 0.01885 -0.0332 1.0000 0.0224
-10.250 -0.9372 0.02287 0.01833 -0.0318 1.0000 0.0227
-10.000 -0.9193 0.02235 0.01776 -0.0302 1.0000 0.0231
-9.750 -0.9028 0.02169 0.01702 -0.0284 1.0000 0.0234
-9.500 -0.8878 0.02099 0.01624 -0.0262 1.0000 0.0238
-9.250 -0.8687 0.02027 0.01542 -0.0248 0.9995 0.0242
-9.000 -0.8372 0.01951 0.01455 -0.0260 0.9977 0.0246
-8.750 -0.8041 0.01908 0.01402 -0.0274 0.9958 0.0250
-8.500 -0.7720 0.01818 0.01299 -0.0288 0.9941 0.0255
-8.250 -0.7436 0.01648 0.01119 -0.0296 0.9913 0.0261
-8.000 -0.7115 0.01572 0.01041 -0.0309 0.9882 0.0265
-7.750 -0.6788 0.01511 0.00978 -0.0322 0.9848 0.0270
-7.500 -0.6479 0.01460 0.00924 -0.0331 0.9797 0.0275
-7.250 -0.6181 0.01414 0.00874 -0.0336 0.9728 0.0281
-7.000 -0.5902 0.01363 0.00818 -0.0337 0.9641 0.0285
-6.750 -0.5635 0.01316 0.00765 -0.0334 0.9543 0.0290
-6.500 -0.5386 0.01275 0.00719 -0.0328 0.9423 0.0294
-6.250 -0.5137 0.01240 0.00677 -0.0321 0.9301 0.0297
-6.000 -0.4885 0.01210 0.00640 -0.0314 0.9182 0.0300
-5.750 -0.4637 0.01173 0.00596 -0.0307 0.9065 0.0303
-5.500 -0.4407 0.01100 0.00516 -0.0298 0.8943 0.0312
-5.250 -0.4153 0.01063 0.00474 -0.0293 0.8828 0.0318
-5.000 -0.3895 0.01034 0.00440 -0.0288 0.8718 0.0324
-4.750 -0.3633 0.01009 0.00409 -0.0284 0.8604 0.0330
-4.500 -0.3366 0.00985 0.00381 -0.0281 0.8491 0.0337
-4.250 -0.3099 0.00964 0.00355 -0.0278 0.8381 0.0344
-3.750 -0.2556 0.00928 0.00309 -0.0274 0.8153 0.0357
-3.500 -0.2288 0.00904 0.00278 -0.0271 0.8042 0.0371
-3.250 -0.2018 0.00885 0.00256 -0.0269 0.7931 0.0390
-3.000 -0.1742 0.00870 0.00238 -0.0267 0.7818 0.0407
-2.750 -0.1465 0.00858 0.00222 -0.0266 0.7710 0.0425
-2.500 -0.1193 0.00841 0.00204 -0.0264 0.7603 0.0493
-2.250 -0.0925 0.00812 0.00189 -0.0262 0.7494 0.0817
-2.000 -0.0656 0.00789 0.00178 -0.0261 0.7389 0.1180
-1.500 -0.0111 0.00753 0.00160 -0.0259 0.7176 0.1872
-1.250 0.0149 0.00718 0.00150 -0.0257 0.7073 0.2698
-1.000 0.0401 0.00676 0.00141 -0.0253 0.6965 0.3780
-0.750 0.0641 0.00617 0.00132 -0.0248 0.6856 0.5284
0.000 0.1363 0.00522 0.00130 -0.0222 0.6510 0.8358
0.250 0.1626 0.00521 0.00134 -0.0216 0.6368 0.8716
0.500 0.1891 0.00525 0.00138 -0.0211 0.6212 0.8962
0.750 0.2156 0.00532 0.00143 -0.0205 0.6064 0.9154
1.000 0.2414 0.00541 0.00151 -0.0198 0.5936 0.9340
1.250 0.2671 0.00553 0.00159 -0.0190 0.5808 0.9485
1.500 0.2938 0.00564 0.00165 -0.0185 0.5676 0.9583
1.750 0.3217 0.00577 0.00174 -0.0183 0.5554 0.9672
2.000 0.3536 0.00591 0.00184 -0.0190 0.5431 0.9730
2.250 0.3909 0.00609 0.00196 -0.0210 0.5299 0.9778
2.500 0.4242 0.00626 0.00207 -0.0221 0.5178 0.9827
2.750 0.4609 0.00636 0.00213 -0.0241 0.5052 0.9835
3.000 0.4963 0.00647 0.00219 -0.0258 0.4928 0.9845
3.250 0.5312 0.00658 0.00226 -0.0275 0.4808 0.9856
3.500 0.5655 0.00670 0.00233 -0.0290 0.4671 0.9869
3.750 0.5991 0.00684 0.00240 -0.0304 0.4484 0.9885
4.000 0.6319 0.00701 0.00249 -0.0316 0.4273 0.9904
4.250 0.6635 0.00721 0.00258 -0.0326 0.4035 0.9924
4.500 0.6955 0.00740 0.00269 -0.0336 0.3807 0.9940
4.750 0.7292 0.00760 0.00280 -0.0351 0.3599 0.9949
5.000 0.7624 0.00781 0.00292 -0.0365 0.3347 0.9961
5.250 0.7949 0.00807 0.00307 -0.0378 0.3084 0.9973
5.500 0.8269 0.00837 0.00325 -0.0390 0.2800 0.9986
5.750 0.8584 0.00872 0.00346 -0.0401 0.2502 0.9997
6.000 0.8830 0.00903 0.00366 -0.0398 0.2253 1.0000
6.250 0.9043 0.00934 0.00387 -0.0387 0.2039 1.0000
6.500 0.9252 0.00966 0.00409 -0.0375 0.1809 1.0000
6.750 0.9445 0.01009 0.00437 -0.0361 0.1513 1.0000
7.000 0.9623 0.01061 0.00471 -0.0344 0.1194 1.0000
7.250 0.9798 0.01113 0.00508 -0.0327 0.0935 1.0000
7.500 0.9979 0.01158 0.00543 -0.0310 0.0748 1.0000
7.750 1.0157 0.01204 0.00580 -0.0293 0.0607 1.0000
8.000 1.0343 0.01244 0.00615 -0.0276 0.0522 1.0000
8.250 1.0538 0.01278 0.00648 -0.0262 0.0471 1.0000
8.500 1.0726 0.01320 0.00687 -0.0246 0.0429 1.0000
8.750 1.0929 0.01351 0.00721 -0.0234 0.0406 1.0000
9.000 1.1130 0.01387 0.00756 -0.0221 0.0383 1.0000
9.250 1.1318 0.01435 0.00804 -0.0206 0.0358 1.0000
9.500 1.1526 0.01471 0.00844 -0.0195 0.0344 1.0000
9.750 1.1738 0.01506 0.00881 -0.0185 0.0330 1.0000
10.000 1.1939 0.01549 0.00925 -0.0174 0.0314 1.0000
10.250 1.2109 0.01616 0.00994 -0.0159 0.0294 1.0000
10.500 1.2321 0.01650 0.01033 -0.0150 0.0287 1.0000
10.750 1.2522 0.01692 0.01078 -0.0139 0.0275 1.0000
11.000 1.2712 0.01739 0.01126 -0.0128 0.0263 1.0000
11.250 1.2859 0.01809 0.01198 -0.0110 0.0249 1.0000
11.500 1.3011 0.01863 0.01257 -0.0092 0.0241 1.0000
11.750 1.3168 0.01910 0.01310 -0.0075 0.0233 1.0000
12.000 1.3318 0.01965 0.01369 -0.0058 0.0224 1.0000
12.250 1.3456 0.02032 0.01437 -0.0041 0.0216 1.0000
12.500 1.3547 0.02130 0.01540 -0.0020 0.0207 1.0000
12.750 1.3658 0.02222 0.01638 -0.0003 0.0200 1.0000
13.000 1.3803 0.02296 0.01718 0.0009 0.0194 1.0000
13.250 1.3936 0.02381 0.01809 0.0020 0.0188 1.0000
13.500 1.4060 0.02477 0.01908 0.0032 0.0181 1.0000
13.750 1.4160 0.02595 0.02030 0.0044 0.0175 1.0000
14.000 1.4187 0.02777 0.02219 0.0059 0.0169 1.0000
14.250 1.4269 0.02924 0.02375 0.0068 0.0165 1.0000
14.500 1.4365 0.03065 0.02523 0.0075 0.0161 1.0000
14.750 1.4445 0.03225 0.02691 0.0081 0.0157 1.0000
15.000 1.4516 0.03401 0.02874 0.0086 0.0154 1.0000
15.250 1.4578 0.03589 0.03069 0.0090 0.0150 1.0000
15.500 1.4622 0.03802 0.03289 0.0093 0.0146 1.0000
15.750 1.4637 0.04053 0.03547 0.0094 0.0143 1.0000
16.000 1.4601 0.04365 0.03867 0.0094 0.0140 1.0000
16.250 1.4507 0.04755 0.04268 0.0092 0.0137 1.0000
16.500 1.4490 0.05070 0.04593 0.0087 0.0135 1.0000
16.750 1.4492 0.05370 0.04903 0.0082 0.0133 1.0000
17.000 1.4478 0.05699 0.05242 0.0075 0.0131 1.0000
17.250 1.4450 0.06056 0.05609 0.0066 0.0129 1.0000
17.500 1.4408 0.06438 0.06001 0.0056 0.0127 1.0000
17.750 1.4350 0.06849 0.06421 0.0043 0.0125 1.0000
18.000 1.4279 0.07289 0.06871 0.0029 0.0124 1.0000
18.250 1.4195 0.07755 0.07348 0.0013 0.0122 1.0000
18.500 1.4097 0.08247 0.07850 -0.0004 0.0121 1.0000
18.750 1.3991 0.08761 0.08374 -0.0024 0.0120 1.0000
19.000 1.3873 0.09305 0.08928 -0.0045 0.0119 1.0000
19.250 1.3746 0.09866 0.09499 -0.0068 0.0118 1.0000
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