NACA M6 AIRFOIL (m6-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M6 AIRFOIL (m6-il) Reynolds number: 200,000 Max Cl/Cd: 63.44 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m6-il-200000-n5.txt Download as CSV file: xf-m6-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M6 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6050 0.08417 0.08055 -0.0164 1.0000 0.0330
-9.750 -0.6542 0.06925 0.06556 -0.0285 1.0000 0.0324
-9.500 -0.7051 0.05780 0.05377 -0.0294 1.0000 0.0321
-9.250 -0.7352 0.04921 0.04470 -0.0274 1.0000 0.0321
-9.000 -0.7417 0.04432 0.03942 -0.0253 1.0000 0.0322
-8.750 -0.7393 0.04060 0.03534 -0.0233 1.0000 0.0325
-8.500 -0.7315 0.03759 0.03201 -0.0215 1.0000 0.0328
-8.250 -0.7192 0.03525 0.02940 -0.0199 1.0000 0.0334
-8.000 -0.7056 0.03302 0.02687 -0.0184 1.0000 0.0340
-7.750 -0.6909 0.03086 0.02438 -0.0168 0.9996 0.0345
-7.500 -0.6647 0.02857 0.02169 -0.0174 0.9756 0.0349
-7.250 -0.6369 0.02668 0.01946 -0.0180 0.9567 0.0352
-7.000 -0.6097 0.02516 0.01762 -0.0182 0.9384 0.0356
-6.750 -0.5839 0.02390 0.01609 -0.0179 0.9206 0.0360
-6.500 -0.5594 0.02288 0.01482 -0.0172 0.9037 0.0364
-6.250 -0.5353 0.02211 0.01382 -0.0164 0.8874 0.0369
-6.000 -0.5117 0.02097 0.01258 -0.0156 0.8721 0.0375
-5.750 -0.4877 0.02013 0.01165 -0.0148 0.8575 0.0381
-5.500 -0.4634 0.01940 0.01082 -0.0140 0.8433 0.0386
-5.250 -0.4389 0.01874 0.01007 -0.0133 0.8298 0.0391
-5.000 -0.4141 0.01813 0.00936 -0.0126 0.8165 0.0396
-4.750 -0.3891 0.01756 0.00871 -0.0119 0.8034 0.0402
-4.500 -0.3640 0.01704 0.00811 -0.0113 0.7913 0.0409
-4.250 -0.3390 0.01656 0.00755 -0.0106 0.7797 0.0416
-4.000 -0.3137 0.01613 0.00703 -0.0100 0.7683 0.0424
-3.750 -0.2882 0.01574 0.00656 -0.0095 0.7574 0.0433
-3.500 -0.2627 0.01538 0.00613 -0.0089 0.7474 0.0446
-3.250 -0.2372 0.01499 0.00571 -0.0085 0.7372 0.0464
-3.000 -0.2112 0.01470 0.00537 -0.0080 0.7277 0.0483
-2.750 -0.1850 0.01444 0.00504 -0.0076 0.7184 0.0503
-2.500 -0.1585 0.01419 0.00474 -0.0073 0.7094 0.0530
-2.250 -0.1324 0.01393 0.00448 -0.0069 0.7008 0.0584
-2.000 -0.1060 0.01366 0.00424 -0.0065 0.6920 0.0709
-1.750 -0.0802 0.01337 0.00402 -0.0061 0.6840 0.0970
-1.500 -0.0543 0.01305 0.00388 -0.0058 0.6755 0.1420
-1.250 -0.0290 0.01275 0.00372 -0.0054 0.6678 0.1902
-1.000 -0.0048 0.01228 0.00359 -0.0049 0.6598 0.2772
-0.750 0.0124 0.01123 0.00336 -0.0031 0.6524 0.4911
-0.500 0.0448 0.01038 0.00391 -0.0026 0.6449 0.8706
-0.250 0.0810 0.01066 0.00412 -0.0036 0.6368 0.9106
0.000 0.1225 0.01109 0.00448 -0.0056 0.6289 0.9413
0.250 0.1711 0.01149 0.00478 -0.0094 0.6204 0.9597
0.500 0.2211 0.01177 0.00497 -0.0137 0.6120 0.9723
0.750 0.2688 0.01191 0.00501 -0.0178 0.6033 0.9799
1.000 0.3070 0.01196 0.00500 -0.0201 0.5950 0.9853
1.250 0.3440 0.01198 0.00494 -0.0221 0.5867 0.9888
1.500 0.3757 0.01198 0.00490 -0.0231 0.5783 0.9912
1.750 0.4066 0.01201 0.00486 -0.0239 0.5702 0.9936
2.000 0.4395 0.01200 0.00483 -0.0251 0.5613 0.9952
2.250 0.4716 0.01202 0.00479 -0.0261 0.5530 0.9969
2.500 0.5038 0.01203 0.00480 -0.0273 0.5433 0.9988
2.750 0.5335 0.01207 0.00480 -0.0278 0.5343 1.0000
3.000 0.5590 0.01210 0.00481 -0.0275 0.5241 1.0000
3.250 0.5845 0.01214 0.00484 -0.0272 0.5139 1.0000
3.500 0.6097 0.01221 0.00486 -0.0268 0.5040 1.0000
3.750 0.6351 0.01226 0.00493 -0.0264 0.4934 1.0000
4.000 0.6603 0.01234 0.00500 -0.0260 0.4837 1.0000
4.250 0.6853 0.01243 0.00509 -0.0256 0.4740 1.0000
4.500 0.7102 0.01253 0.00521 -0.0252 0.4641 1.0000
4.750 0.7347 0.01265 0.00532 -0.0246 0.4529 1.0000
5.000 0.7588 0.01279 0.00544 -0.0240 0.4404 1.0000
5.250 0.7828 0.01293 0.00559 -0.0234 0.4271 1.0000
5.500 0.8066 0.01310 0.00576 -0.0228 0.4135 1.0000
5.750 0.8300 0.01329 0.00595 -0.0221 0.3977 1.0000
6.000 0.8527 0.01352 0.00614 -0.0213 0.3792 1.0000
6.250 0.8749 0.01379 0.00636 -0.0205 0.3552 1.0000
6.500 0.8959 0.01416 0.00662 -0.0195 0.3256 1.0000
6.750 0.9165 0.01456 0.00694 -0.0184 0.2986 1.0000
7.000 0.9371 0.01497 0.00729 -0.0174 0.2751 1.0000
7.250 0.9566 0.01545 0.00768 -0.0162 0.2512 1.0000
7.500 0.9750 0.01600 0.00815 -0.0149 0.2250 1.0000
7.750 0.9926 0.01661 0.00866 -0.0134 0.1981 1.0000
8.000 1.0090 0.01729 0.00923 -0.0118 0.1714 1.0000
8.250 1.0240 0.01804 0.00986 -0.0101 0.1429 1.0000
8.500 1.0366 0.01895 0.01059 -0.0080 0.1109 1.0000
8.750 1.0482 0.01987 0.01139 -0.0058 0.0904 1.0000
9.000 1.0602 0.02071 0.01219 -0.0036 0.0786 1.0000
9.250 1.0714 0.02154 0.01301 -0.0013 0.0702 1.0000
9.500 1.0828 0.02231 0.01381 0.0010 0.0632 1.0000
9.750 1.0928 0.02312 0.01465 0.0034 0.0580 1.0000
10.000 1.1020 0.02394 0.01552 0.0058 0.0538 1.0000
10.250 1.1064 0.02490 0.01649 0.0089 0.0507 1.0000
10.500 1.1122 0.02580 0.01747 0.0116 0.0480 1.0000
10.750 1.1176 0.02690 0.01863 0.0139 0.0455 1.0000
11.000 1.1216 0.02829 0.02004 0.0158 0.0435 1.0000
11.250 1.1272 0.02972 0.02155 0.0173 0.0416 1.0000
11.500 1.1340 0.03119 0.02313 0.0185 0.0397 1.0000
11.750 1.1400 0.03283 0.02484 0.0195 0.0380 1.0000
12.000 1.1438 0.03476 0.02682 0.0203 0.0366 1.0000
12.250 1.1458 0.03694 0.02905 0.0209 0.0354 1.0000
12.500 1.1516 0.03884 0.03108 0.0214 0.0341 1.0000
12.750 1.1565 0.04089 0.03323 0.0218 0.0328 1.0000
13.000 1.1604 0.04308 0.03552 0.0221 0.0316 1.0000
13.250 1.1629 0.04546 0.03796 0.0222 0.0306 1.0000
13.500 1.1626 0.04815 0.04069 0.0223 0.0298 1.0000
13.750 1.1650 0.05060 0.04324 0.0224 0.0290 1.0000
14.000 1.1679 0.05306 0.04584 0.0225 0.0281 1.0000
14.250 1.1698 0.05565 0.04854 0.0224 0.0272 1.0000
14.500 1.1710 0.05836 0.05134 0.0221 0.0264 1.0000
14.750 1.1716 0.06122 0.05428 0.0217 0.0257 1.0000
15.000 1.1715 0.06423 0.05737 0.0212 0.0250 1.0000
15.250 1.1704 0.06737 0.06056 0.0207 0.0244 1.0000
15.500 1.1705 0.07052 0.06384 0.0201 0.0238 1.0000
15.750 1.1702 0.07379 0.06727 0.0194 0.0232 1.0000
16.000 1.1691 0.07721 0.07083 0.0186 0.0227 1.0000
16.250 1.1674 0.08081 0.07456 0.0176 0.0222 1.0000
16.500 1.1651 0.08456 0.07843 0.0164 0.0217 1.0000
16.750 1.1624 0.08844 0.08243 0.0151 0.0212 1.0000
17.000 1.1593 0.09246 0.08654 0.0136 0.0208 1.0000
17.250 1.1558 0.09658 0.09075 0.0119 0.0205 1.0000
17.500 1.1523 0.10074 0.09498 0.0102 0.0201 1.0000
17.750 1.1486 0.10491 0.09922 0.0086 0.0198 1.0000
18.000 1.1399 0.11030 0.10482 0.0061 0.0195 1.0000
18.250 1.1303 0.11595 0.11066 0.0034 0.0192 1.0000
18.500 1.1194 0.12203 0.11692 0.0004 0.0189 1.0000
18.750 1.1072 0.12853 0.12361 -0.0031 0.0186 1.0000
19.000 1.0934 0.13557 0.13083 -0.0070 0.0184 1.0000
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