NACA M3 AIRFOIL (m3-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M3 AIRFOIL (m3-il) Reynolds number: 200,000 Max Cl/Cd: 42.15 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m3-il-200000-n5.txt Download as CSV file: xf-m3-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M3 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.9835 0.08472 0.08023 -0.0226 1.0000 0.0264
-14.750 -1.0181 0.07475 0.06999 -0.0293 1.0000 0.0263
-14.500 -1.0391 0.06798 0.06301 -0.0333 1.0000 0.0264
-14.250 -1.0547 0.06261 0.05744 -0.0360 1.0000 0.0266
-14.000 -1.0670 0.05811 0.05275 -0.0377 1.0000 0.0268
-13.750 -1.0769 0.05426 0.04871 -0.0386 1.0000 0.0271
-13.500 -1.0848 0.05094 0.04520 -0.0388 1.0000 0.0275
-13.250 -1.0910 0.04804 0.04210 -0.0384 1.0000 0.0279
-13.000 -1.0953 0.04548 0.03932 -0.0374 1.0000 0.0284
-12.750 -1.0985 0.04316 0.03677 -0.0358 1.0000 0.0290
-12.500 -1.1003 0.04108 0.03444 -0.0339 1.0000 0.0295
-12.250 -1.1004 0.03925 0.03234 -0.0315 1.0000 0.0301
-12.000 -1.0987 0.03768 0.03051 -0.0289 1.0000 0.0305
-11.750 -1.0904 0.03583 0.02857 -0.0271 1.0000 0.0311
-11.500 -1.0792 0.03449 0.02719 -0.0255 1.0000 0.0317
-11.250 -1.0665 0.03334 0.02597 -0.0240 1.0000 0.0324
-11.000 -1.0529 0.03223 0.02474 -0.0225 1.0000 0.0332
-10.750 -1.0383 0.03108 0.02347 -0.0210 1.0000 0.0340
-10.500 -1.0226 0.02993 0.02216 -0.0196 1.0000 0.0348
-10.250 -1.0058 0.02880 0.02088 -0.0183 1.0000 0.0356
-10.000 -0.9883 0.02782 0.01974 -0.0170 1.0000 0.0364
-9.750 -0.9702 0.02682 0.01859 -0.0158 1.0000 0.0371
-9.500 -0.9528 0.02561 0.01738 -0.0146 1.0000 0.0380
-9.250 -0.9348 0.02468 0.01642 -0.0133 1.0000 0.0388
-9.000 -0.9165 0.02383 0.01553 -0.0120 1.0000 0.0396
-8.750 -0.8980 0.02305 0.01469 -0.0107 1.0000 0.0405
-8.500 -0.8793 0.02233 0.01390 -0.0093 1.0000 0.0416
-8.250 -0.8607 0.02164 0.01315 -0.0079 1.0000 0.0427
-8.000 -0.8421 0.02098 0.01242 -0.0064 1.0000 0.0437
-7.750 -0.8238 0.02036 0.01173 -0.0048 1.0000 0.0444
-7.500 -0.8075 0.01958 0.01094 -0.0029 1.0000 0.0456
-7.250 -0.7900 0.01896 0.01031 -0.0012 1.0000 0.0468
-7.000 -0.7718 0.01842 0.00975 0.0004 1.0000 0.0482
-6.750 -0.7532 0.01793 0.00923 0.0020 1.0000 0.0500
-6.500 -0.7343 0.01749 0.00873 0.0035 1.0000 0.0522
-6.250 -0.7161 0.01699 0.00823 0.0052 1.0000 0.0549
-6.000 -0.6973 0.01655 0.00780 0.0067 1.0000 0.0584
-5.500 -0.6592 0.01572 0.00698 0.0097 1.0000 0.0705
-5.250 -0.6400 0.01531 0.00662 0.0112 1.0000 0.0819
-5.000 -0.6121 0.01485 0.00624 0.0107 0.9978 0.1010
-4.750 -0.5789 0.01432 0.00588 0.0091 0.9943 0.1314
-4.500 -0.5467 0.01380 0.00554 0.0077 0.9901 0.1682
-4.250 -0.5135 0.01331 0.00525 0.0061 0.9858 0.2098
-4.000 -0.4802 0.01285 0.00498 0.0045 0.9817 0.2555
-3.750 -0.4485 0.01236 0.00474 0.0033 0.9762 0.3103
-3.500 -0.4143 0.01184 0.00453 0.0016 0.9722 0.3756
-3.250 -0.3846 0.01137 0.00435 0.0009 0.9655 0.4414
-3.000 -0.3517 0.01098 0.00421 -0.0003 0.9603 0.4977
-2.750 -0.3217 0.01068 0.00409 -0.0007 0.9533 0.5438
-2.500 -0.2904 0.01041 0.00401 -0.0013 0.9467 0.5905
-2.250 -0.2606 0.01018 0.00395 -0.0015 0.9392 0.6338
-2.000 -0.2300 0.01001 0.00388 -0.0019 0.9313 0.6664
-1.750 -0.2003 0.00987 0.00384 -0.0020 0.9227 0.6949
-1.500 -0.1701 0.00974 0.00378 -0.0021 0.9138 0.7222
-1.250 -0.1418 0.00965 0.00376 -0.0018 0.9031 0.7471
-1.000 -0.1122 0.00956 0.00372 -0.0017 0.8929 0.7691
-0.750 -0.0835 0.00950 0.00370 -0.0014 0.8809 0.7885
-0.500 -0.0557 0.00946 0.00368 -0.0010 0.8674 0.8064
-0.250 -0.0279 0.00943 0.00367 -0.0005 0.8533 0.8230
0.000 0.0000 0.00942 0.00366 0.0000 0.8386 0.8386
0.250 0.0279 0.00943 0.00367 0.0005 0.8231 0.8533
0.500 0.0557 0.00946 0.00368 0.0010 0.8064 0.8674
0.750 0.0835 0.00950 0.00370 0.0014 0.7885 0.8809
1.000 0.1122 0.00956 0.00372 0.0017 0.7690 0.8929
1.250 0.1418 0.00965 0.00376 0.0018 0.7472 0.9031
1.500 0.1701 0.00974 0.00378 0.0021 0.7222 0.9138
1.750 0.2003 0.00987 0.00383 0.0020 0.6949 0.9227
2.000 0.2300 0.01001 0.00388 0.0019 0.6664 0.9313
2.250 0.2606 0.01018 0.00395 0.0015 0.6338 0.9392
2.500 0.2904 0.01041 0.00401 0.0013 0.5904 0.9467
2.750 0.3217 0.01068 0.00409 0.0007 0.5438 0.9533
3.000 0.3517 0.01098 0.00421 0.0003 0.4976 0.9603
3.250 0.3846 0.01137 0.00435 -0.0009 0.4415 0.9655
3.500 0.4143 0.01184 0.00453 -0.0016 0.3755 0.9722
3.750 0.4485 0.01235 0.00474 -0.0033 0.3104 0.9762
4.000 0.4802 0.01285 0.00498 -0.0045 0.2554 0.9817
4.250 0.5136 0.01331 0.00525 -0.0061 0.2098 0.9859
4.500 0.5467 0.01380 0.00554 -0.0077 0.1683 0.9901
4.750 0.5790 0.01432 0.00588 -0.0091 0.1315 0.9943
5.000 0.6122 0.01484 0.00624 -0.0107 0.1010 0.9978
5.250 0.6399 0.01531 0.00662 -0.0111 0.0820 1.0000
5.500 0.6591 0.01572 0.00698 -0.0097 0.0705 1.0000
6.000 0.6972 0.01654 0.00780 -0.0067 0.0584 1.0000
6.250 0.7160 0.01699 0.00823 -0.0051 0.0549 1.0000
6.500 0.7342 0.01749 0.00872 -0.0035 0.0522 1.0000
6.750 0.7531 0.01793 0.00922 -0.0019 0.0500 1.0000
7.000 0.7717 0.01842 0.00974 -0.0004 0.0482 1.0000
7.250 0.7899 0.01895 0.01031 0.0013 0.0468 1.0000
7.500 0.8075 0.01957 0.01094 0.0029 0.0456 1.0000
7.750 0.8238 0.02035 0.01172 0.0048 0.0444 1.0000
8.000 0.8421 0.02098 0.01242 0.0064 0.0437 1.0000
8.250 0.8607 0.02164 0.01315 0.0079 0.0427 1.0000
8.500 0.8794 0.02233 0.01390 0.0093 0.0416 1.0000
8.750 0.8980 0.02305 0.01469 0.0106 0.0405 1.0000
9.000 0.9166 0.02383 0.01553 0.0120 0.0396 1.0000
9.250 0.9349 0.02468 0.01642 0.0133 0.0388 1.0000
9.500 0.9530 0.02561 0.01738 0.0145 0.0380 1.0000
9.750 0.9704 0.02682 0.01860 0.0158 0.0371 1.0000
10.000 0.9885 0.02782 0.01974 0.0170 0.0364 1.0000
10.250 1.0061 0.02881 0.02089 0.0183 0.0356 1.0000
10.500 1.0228 0.02993 0.02216 0.0196 0.0348 1.0000
10.750 1.0386 0.03109 0.02347 0.0210 0.0340 1.0000
11.000 1.0533 0.03223 0.02475 0.0224 0.0332 1.0000
11.250 1.0669 0.03335 0.02598 0.0239 0.0324 1.0000
11.500 1.0797 0.03450 0.02719 0.0254 0.0317 1.0000
11.750 1.0910 0.03584 0.02858 0.0270 0.0311 1.0000
12.000 1.0992 0.03769 0.03053 0.0288 0.0305 1.0000
12.250 1.1010 0.03926 0.03236 0.0314 0.0301 1.0000
12.500 1.1010 0.04109 0.03446 0.0337 0.0295 1.0000
12.750 1.0993 0.04318 0.03679 0.0357 0.0290 1.0000
13.000 1.0962 0.04549 0.03934 0.0372 0.0284 1.0000
13.250 1.0919 0.04804 0.04210 0.0382 0.0279 1.0000
13.500 1.0858 0.05095 0.04521 0.0386 0.0275 1.0000
13.750 1.0781 0.05427 0.04872 0.0384 0.0271 1.0000
14.000 1.0682 0.05813 0.05277 0.0375 0.0268 1.0000
14.250 1.0559 0.06262 0.05745 0.0358 0.0266 1.0000
14.500 1.0408 0.06795 0.06297 0.0331 0.0264 1.0000
14.750 1.0199 0.07469 0.06993 0.0291 0.0263 1.0000
15.000 0.9860 0.08455 0.08006 0.0225 0.0264 1.0000
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