NACA M12 AIRFOIL (m12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M12 AIRFOIL (m12-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.35 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m12-il-1000000-n5.txt Download as CSV file: xf-m12-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.3413 0.04668 0.04357 -0.0548 1.0000 0.0136
-17.000 -1.3535 0.04203 0.03876 -0.0571 1.0000 0.0137
-16.750 -1.3602 0.03865 0.03522 -0.0578 1.0000 0.0138
-16.500 -1.3629 0.03605 0.03250 -0.0576 1.0000 0.0140
-16.250 -1.3604 0.03414 0.03050 -0.0569 1.0000 0.0142
-16.000 -1.3541 0.03267 0.02897 -0.0559 1.0000 0.0145
-15.750 -1.3460 0.03143 0.02767 -0.0547 1.0000 0.0147
-15.500 -1.3366 0.03036 0.02653 -0.0534 1.0000 0.0150
-15.250 -1.3264 0.02939 0.02550 -0.0519 1.0000 0.0152
-15.000 -1.3160 0.02848 0.02451 -0.0503 1.0000 0.0155
-14.750 -1.3054 0.02762 0.02358 -0.0484 1.0000 0.0158
-14.500 -1.2942 0.02684 0.02271 -0.0465 1.0000 0.0161
-14.250 -1.2810 0.02609 0.02188 -0.0447 1.0000 0.0164
-14.000 -1.2653 0.02535 0.02105 -0.0434 1.0000 0.0167
-13.750 -1.2484 0.02464 0.02026 -0.0421 1.0000 0.0170
-13.500 -1.2306 0.02396 0.01949 -0.0410 1.0000 0.0172
-13.250 -1.2137 0.02318 0.01862 -0.0397 1.0000 0.0174
-13.000 -1.1953 0.02250 0.01789 -0.0386 1.0000 0.0177
-12.750 -1.1751 0.02197 0.01732 -0.0377 1.0000 0.0180
-12.500 -1.1538 0.02153 0.01685 -0.0369 1.0000 0.0182
-12.250 -1.1319 0.02115 0.01644 -0.0361 1.0000 0.0185
-12.000 -1.1099 0.02076 0.01601 -0.0354 1.0000 0.0188
-11.750 -1.0882 0.02035 0.01555 -0.0345 1.0000 0.0191
-11.500 -1.0670 0.01987 0.01502 -0.0336 1.0000 0.0194
-11.250 -1.0460 0.01939 0.01448 -0.0326 1.0000 0.0197
-11.000 -1.0249 0.01896 0.01399 -0.0316 1.0000 0.0201
-10.750 -1.0042 0.01853 0.01351 -0.0304 1.0000 0.0204
-10.500 -0.9842 0.01810 0.01301 -0.0291 1.0000 0.0206
-10.250 -0.9549 0.01764 0.01248 -0.0298 0.9975 0.0209
-10.000 -0.9242 0.01724 0.01202 -0.0307 0.9949 0.0211
-9.750 -0.8967 0.01649 0.01120 -0.0312 0.9905 0.0214
-9.500 -0.8685 0.01580 0.01045 -0.0317 0.9856 0.0218
-9.250 -0.8397 0.01532 0.00995 -0.0322 0.9795 0.0221
-9.000 -0.8100 0.01494 0.00953 -0.0329 0.9726 0.0225
-8.750 -0.7823 0.01454 0.00910 -0.0330 0.9626 0.0228
-8.500 -0.7557 0.01415 0.00865 -0.0329 0.9509 0.0230
-8.250 -0.7304 0.01378 0.00821 -0.0324 0.9372 0.0233
-8.000 -0.7058 0.01345 0.00781 -0.0318 0.9230 0.0236
-7.750 -0.6810 0.01315 0.00745 -0.0312 0.9094 0.0240
-7.500 -0.6561 0.01285 0.00706 -0.0306 0.8964 0.0243
-7.250 -0.6307 0.01253 0.00666 -0.0301 0.8840 0.0246
-7.000 -0.6051 0.01223 0.00629 -0.0296 0.8722 0.0248
-6.750 -0.5793 0.01195 0.00593 -0.0292 0.8606 0.0251
-6.500 -0.5533 0.01170 0.00561 -0.0289 0.8486 0.0253
-6.250 -0.5269 0.01145 0.00530 -0.0286 0.8365 0.0255
-6.000 -0.5003 0.01123 0.00501 -0.0283 0.8248 0.0257
-5.750 -0.4740 0.01098 0.00469 -0.0280 0.8130 0.0259
-5.500 -0.4481 0.01064 0.00428 -0.0276 0.8007 0.0265
-5.250 -0.4214 0.01038 0.00398 -0.0274 0.7888 0.0271
-5.000 -0.3945 0.01018 0.00372 -0.0272 0.7776 0.0275
-4.750 -0.3675 0.01000 0.00349 -0.0270 0.7665 0.0280
-4.500 -0.3401 0.00983 0.00327 -0.0269 0.7554 0.0284
-4.250 -0.3127 0.00967 0.00307 -0.0267 0.7448 0.0289
-4.000 -0.2853 0.00953 0.00288 -0.0266 0.7342 0.0293
-3.750 -0.2576 0.00939 0.00271 -0.0266 0.7239 0.0298
-3.500 -0.2299 0.00927 0.00254 -0.0265 0.7142 0.0304
-3.250 -0.2022 0.00917 0.00239 -0.0264 0.7038 0.0309
-3.000 -0.1743 0.00906 0.00226 -0.0264 0.6939 0.0313
-2.750 -0.1466 0.00894 0.00210 -0.0264 0.6840 0.0328
-2.500 -0.1187 0.00883 0.00198 -0.0263 0.6733 0.0345
-2.250 -0.0908 0.00874 0.00187 -0.0263 0.6633 0.0367
-2.000 -0.0630 0.00865 0.00176 -0.0263 0.6526 0.0414
-1.750 -0.0354 0.00849 0.00166 -0.0262 0.6414 0.0584
-1.500 -0.0078 0.00836 0.00158 -0.0262 0.6307 0.0787
-1.250 0.0199 0.00825 0.00151 -0.0262 0.6193 0.0975
-1.000 0.0474 0.00813 0.00145 -0.0262 0.6071 0.1238
-0.750 0.0752 0.00804 0.00140 -0.0262 0.5952 0.1479
-0.500 0.1027 0.00792 0.00135 -0.0261 0.5831 0.1806
-0.250 0.1296 0.00774 0.00131 -0.0261 0.5708 0.2349
0.000 0.1561 0.00751 0.00127 -0.0259 0.5573 0.3116
0.250 0.1819 0.00723 0.00124 -0.0257 0.5403 0.4089
0.500 0.2065 0.00683 0.00121 -0.0253 0.5236 0.5403
0.750 0.2320 0.00657 0.00120 -0.0249 0.5106 0.6347
1.000 0.2557 0.00620 0.00122 -0.0241 0.5000 0.7542
1.250 0.2796 0.00601 0.00130 -0.0230 0.4898 0.8421
1.500 0.3048 0.00599 0.00140 -0.0222 0.4801 0.8902
1.750 0.3317 0.00605 0.00147 -0.0218 0.4700 0.9109
2.000 0.3584 0.00613 0.00154 -0.0214 0.4595 0.9265
2.250 0.3851 0.00622 0.00163 -0.0210 0.4500 0.9408
2.500 0.4125 0.00632 0.00171 -0.0207 0.4404 0.9516
2.750 0.4394 0.00644 0.00178 -0.0205 0.4293 0.9591
3.000 0.4690 0.00653 0.00185 -0.0208 0.4188 0.9623
3.250 0.4979 0.00665 0.00193 -0.0211 0.4079 0.9661
3.500 0.5256 0.00678 0.00201 -0.0211 0.3959 0.9706
3.750 0.5552 0.00694 0.00211 -0.0215 0.3792 0.9735
4.000 0.5848 0.00719 0.00223 -0.0221 0.3506 0.9760
4.250 0.6136 0.00748 0.00238 -0.0225 0.3173 0.9790
4.500 0.6405 0.00786 0.00256 -0.0225 0.2764 0.9827
4.750 0.6702 0.00820 0.00275 -0.0232 0.2462 0.9846
5.000 0.7016 0.00846 0.00293 -0.0242 0.2275 0.9861
5.250 0.7331 0.00872 0.00312 -0.0252 0.2105 0.9875
5.500 0.7640 0.00898 0.00331 -0.0261 0.1935 0.9891
5.750 0.7938 0.00930 0.00353 -0.0269 0.1716 0.9909
6.000 0.8222 0.00969 0.00379 -0.0273 0.1461 0.9928
6.250 0.8509 0.01010 0.00407 -0.0279 0.1212 0.9943
6.500 0.8804 0.01053 0.00439 -0.0287 0.0992 0.9953
6.750 0.9098 0.01092 0.00469 -0.0294 0.0834 0.9966
7.000 0.9389 0.01129 0.00499 -0.0300 0.0704 0.9979
7.250 0.9677 0.01167 0.00531 -0.0306 0.0592 0.9991
7.500 0.9945 0.01203 0.00563 -0.0308 0.0513 1.0000
7.750 1.0142 0.01233 0.00590 -0.0293 0.0463 1.0000
8.000 1.0342 0.01263 0.00619 -0.0279 0.0423 1.0000
8.250 1.0543 0.01292 0.00648 -0.0266 0.0394 1.0000
8.500 1.0743 0.01325 0.00680 -0.0253 0.0365 1.0000
8.750 1.0951 0.01353 0.00709 -0.0241 0.0351 1.0000
9.000 1.1159 0.01384 0.00741 -0.0229 0.0335 1.0000
9.250 1.1365 0.01418 0.00776 -0.0218 0.0318 1.0000
9.500 1.1571 0.01457 0.00815 -0.0207 0.0301 1.0000
9.750 1.1787 0.01489 0.00849 -0.0198 0.0292 1.0000
10.000 1.2001 0.01523 0.00886 -0.0189 0.0280 1.0000
10.250 1.2210 0.01562 0.00926 -0.0179 0.0267 1.0000
10.500 1.2411 0.01605 0.00971 -0.0169 0.0254 1.0000
10.750 1.2611 0.01648 0.01016 -0.0159 0.0244 1.0000
11.000 1.2814 0.01687 0.01059 -0.0149 0.0234 1.0000
11.250 1.3007 0.01731 0.01104 -0.0138 0.0221 1.0000
11.500 1.3184 0.01780 0.01155 -0.0124 0.0208 1.0000
11.750 1.3340 0.01830 0.01208 -0.0107 0.0198 1.0000
12.000 1.3492 0.01880 0.01263 -0.0090 0.0189 1.0000
12.250 1.3638 0.01938 0.01323 -0.0072 0.0178 1.0000
12.500 1.3775 0.02004 0.01391 -0.0056 0.0167 1.0000
12.750 1.3912 0.02074 0.01465 -0.0040 0.0159 1.0000
13.000 1.4048 0.02149 0.01545 -0.0026 0.0150 1.0000
13.250 1.4172 0.02234 0.01633 -0.0011 0.0142 1.0000
13.500 1.4286 0.02331 0.01734 0.0003 0.0134 1.0000
13.750 1.4396 0.02435 0.01843 0.0016 0.0128 1.0000
14.000 1.4509 0.02542 0.01956 0.0027 0.0124 1.0000
14.250 1.4612 0.02660 0.02081 0.0038 0.0119 1.0000
14.500 1.4704 0.02793 0.02220 0.0048 0.0115 1.0000
14.750 1.4784 0.02941 0.02374 0.0057 0.0111 1.0000
15.000 1.4852 0.03106 0.02545 0.0065 0.0107 1.0000
15.250 1.4905 0.03292 0.02738 0.0071 0.0103 1.0000
15.500 1.4964 0.03478 0.02931 0.0077 0.0100 1.0000
15.750 1.5018 0.03674 0.03136 0.0080 0.0098 1.0000
16.000 1.5060 0.03891 0.03361 0.0083 0.0095 1.0000
16.250 1.5087 0.04127 0.03605 0.0084 0.0093 1.0000
16.500 1.5100 0.04383 0.03870 0.0084 0.0090 1.0000
16.750 1.5098 0.04665 0.04160 0.0083 0.0088 1.0000
17.000 1.5084 0.04968 0.04472 0.0079 0.0086 1.0000
17.250 1.5052 0.05302 0.04815 0.0074 0.0084 1.0000
17.500 1.5009 0.05662 0.05184 0.0067 0.0083 1.0000
17.750 1.4948 0.06059 0.05590 0.0057 0.0081 1.0000
18.000 1.4869 0.06484 0.06026 0.0046 0.0079 1.0000
18.250 1.4778 0.06940 0.06492 0.0032 0.0078 1.0000
18.500 1.4697 0.07391 0.06955 0.0017 0.0078 1.0000
18.750 1.4602 0.07870 0.07444 0.0001 0.0077 1.0000
19.000 1.4489 0.08382 0.07968 -0.0018 0.0076 1.0000
19.250 1.4367 0.08918 0.08516 -0.0038 0.0076 1.0000
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