NACA M3 (nacam3-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M3 (nacam3-il) Reynolds number: 500,000 Max Cl/Cd: 54.88 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam3-il-500000.txt Download as CSV file: xf-nacam3-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M3
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8710 0.12388 0.12132 0.0042 1.0000 0.0250
-15.500 -1.0296 0.08375 0.08067 -0.0219 1.0000 0.0232
-15.250 -1.0697 0.07282 0.06947 -0.0292 1.0000 0.0231
-15.000 -1.0957 0.06531 0.06174 -0.0336 1.0000 0.0231
-14.750 -1.1142 0.05954 0.05578 -0.0365 1.0000 0.0232
-14.500 -1.1290 0.05481 0.05085 -0.0383 1.0000 0.0234
-14.250 -1.1411 0.05079 0.04664 -0.0391 1.0000 0.0236
-14.000 -1.1512 0.04732 0.04299 -0.0391 1.0000 0.0239
-13.750 -1.1592 0.04441 0.03987 -0.0384 1.0000 0.0242
-13.500 -1.1653 0.04194 0.03720 -0.0370 1.0000 0.0246
-13.250 -1.1697 0.03996 0.03501 -0.0351 1.0000 0.0249
-13.000 -1.1725 0.03854 0.03338 -0.0325 1.0000 0.0252
-12.750 -1.1779 0.03616 0.03077 -0.0294 1.0000 0.0256
-12.500 -1.1708 0.03388 0.02841 -0.0277 1.0000 0.0262
-12.250 -1.1615 0.03269 0.02718 -0.0257 1.0000 0.0266
-12.000 -1.1505 0.03160 0.02600 -0.0239 1.0000 0.0271
-11.750 -1.1371 0.03054 0.02485 -0.0224 1.0000 0.0277
-11.500 -1.1227 0.02946 0.02367 -0.0209 1.0000 0.0283
-11.250 -1.1075 0.02845 0.02254 -0.0194 1.0000 0.0290
-11.000 -1.0914 0.02756 0.02151 -0.0180 1.0000 0.0297
-10.750 -1.0745 0.02690 0.02069 -0.0165 1.0000 0.0302
-10.500 -1.0578 0.02510 0.01874 -0.0153 1.0000 0.0309
-10.250 -1.0393 0.02365 0.01727 -0.0143 1.0000 0.0316
-10.000 -1.0202 0.02277 0.01637 -0.0132 1.0000 0.0323
-9.750 -1.0007 0.02206 0.01561 -0.0121 1.0000 0.0331
-9.500 -0.9809 0.02137 0.01488 -0.0109 1.0000 0.0340
-9.250 -0.9611 0.02068 0.01412 -0.0097 1.0000 0.0347
-9.000 -0.9414 0.01999 0.01337 -0.0084 1.0000 0.0354
-8.750 -0.9218 0.01940 0.01270 -0.0070 1.0000 0.0359
-8.500 -0.9034 0.01866 0.01190 -0.0054 1.0000 0.0365
-8.250 -0.8885 0.01755 0.01077 -0.0033 1.0000 0.0376
-8.000 -0.8711 0.01691 0.01013 -0.0016 1.0000 0.0385
-7.750 -0.8533 0.01637 0.00957 0.0002 1.0000 0.0393
-7.500 -0.8354 0.01588 0.00905 0.0020 1.0000 0.0402
-7.250 -0.8175 0.01542 0.00856 0.0038 1.0000 0.0411
-7.000 -0.7992 0.01502 0.00812 0.0055 1.0000 0.0421
-6.750 -0.7805 0.01468 0.00773 0.0072 1.0000 0.0429
-6.500 -0.7641 0.01408 0.00711 0.0092 1.0000 0.0442
-6.250 -0.7463 0.01360 0.00663 0.0110 1.0000 0.0457
-6.000 -0.7272 0.01326 0.00628 0.0126 1.0000 0.0473
-5.750 -0.7075 0.01297 0.00596 0.0140 1.0000 0.0492
-5.500 -0.6743 0.01258 0.00556 0.0126 0.9982 0.0522
-5.250 -0.6389 0.01216 0.00519 0.0108 0.9958 0.0586
-5.000 -0.6033 0.01163 0.00478 0.0088 0.9938 0.0775
-4.750 -0.5706 0.01098 0.00440 0.0074 0.9905 0.1234
-4.500 -0.5363 0.01043 0.00410 0.0055 0.9873 0.1721
-4.250 -0.5005 0.00992 0.00384 0.0035 0.9847 0.2260
-4.000 -0.4638 0.00942 0.00361 0.0012 0.9828 0.2850
-3.750 -0.4322 0.00899 0.00340 0.0001 0.9778 0.3375
-3.500 -0.3969 0.00858 0.00321 -0.0017 0.9745 0.3910
-3.250 -0.3604 0.00817 0.00304 -0.0038 0.9719 0.4502
-3.000 -0.3258 0.00783 0.00289 -0.0053 0.9684 0.5003
-2.750 -0.2968 0.00750 0.00277 -0.0056 0.9614 0.5501
-2.500 -0.2645 0.00722 0.00264 -0.0064 0.9566 0.5926
-2.250 -0.2375 0.00701 0.00256 -0.0060 0.9481 0.6312
-2.000 -0.2089 0.00679 0.00247 -0.0059 0.9409 0.6668
-1.750 -0.1837 0.00663 0.00242 -0.0050 0.9303 0.7007
-1.500 -0.1575 0.00649 0.00236 -0.0043 0.9205 0.7300
-1.250 -0.1314 0.00638 0.00231 -0.0035 0.9095 0.7521
-1.000 -0.1054 0.00630 0.00227 -0.0028 0.8974 0.7726
-0.750 -0.0791 0.00624 0.00224 -0.0021 0.8854 0.7928
-0.500 -0.0528 0.00619 0.00222 -0.0014 0.8730 0.8117
-0.250 -0.0265 0.00617 0.00220 -0.0007 0.8595 0.8288
0.000 0.0000 0.00616 0.00220 0.0000 0.8446 0.8446
0.250 0.0264 0.00617 0.00220 0.0007 0.8288 0.8595
0.500 0.0528 0.00619 0.00222 0.0014 0.8117 0.8729
0.750 0.0791 0.00624 0.00224 0.0021 0.7928 0.8854
1.000 0.1054 0.00630 0.00227 0.0028 0.7726 0.8974
1.250 0.1314 0.00638 0.00231 0.0035 0.7521 0.9096
1.500 0.1574 0.00649 0.00236 0.0043 0.7299 0.9205
1.750 0.1837 0.00663 0.00242 0.0050 0.7008 0.9303
2.000 0.2089 0.00679 0.00247 0.0059 0.6670 0.9409
2.250 0.2375 0.00701 0.00256 0.0060 0.6311 0.9481
2.500 0.2645 0.00722 0.00264 0.0064 0.5925 0.9566
2.750 0.2968 0.00750 0.00277 0.0056 0.5499 0.9615
3.000 0.3258 0.00783 0.00289 0.0053 0.4999 0.9685
3.250 0.3605 0.00817 0.00304 0.0038 0.4502 0.9719
3.500 0.3969 0.00858 0.00321 0.0017 0.3910 0.9745
3.750 0.4322 0.00899 0.00340 -0.0001 0.3374 0.9779
4.000 0.4639 0.00942 0.00361 -0.0012 0.2850 0.9828
4.250 0.5006 0.00992 0.00384 -0.0035 0.2261 0.9847
4.500 0.5364 0.01043 0.00410 -0.0056 0.1721 0.9873
4.750 0.5707 0.01098 0.00439 -0.0074 0.1234 0.9906
5.000 0.6034 0.01162 0.00478 -0.0088 0.0775 0.9939
5.250 0.6390 0.01215 0.00518 -0.0108 0.0586 0.9959
5.500 0.6744 0.01258 0.00556 -0.0126 0.0523 0.9982
5.750 0.7073 0.01296 0.00596 -0.0140 0.0492 1.0000
6.000 0.7271 0.01325 0.00627 -0.0125 0.0474 1.0000
6.250 0.7462 0.01360 0.00663 -0.0110 0.0457 1.0000
6.500 0.7640 0.01407 0.00710 -0.0092 0.0442 1.0000
6.750 0.7804 0.01468 0.00773 -0.0072 0.0429 1.0000
7.000 0.7991 0.01502 0.00812 -0.0055 0.0421 1.0000
7.250 0.8174 0.01542 0.00855 -0.0038 0.0411 1.0000
7.500 0.8353 0.01588 0.00905 -0.0020 0.0402 1.0000
7.750 0.8532 0.01637 0.00957 -0.0002 0.0393 1.0000
8.000 0.8710 0.01691 0.01013 0.0016 0.0385 1.0000
8.250 0.8884 0.01754 0.01077 0.0034 0.0376 1.0000
8.500 0.9033 0.01867 0.01190 0.0054 0.0365 1.0000
8.750 0.9218 0.01940 0.01269 0.0070 0.0359 1.0000
9.000 0.9415 0.01999 0.01337 0.0084 0.0354 1.0000
9.250 0.9612 0.02067 0.01411 0.0097 0.0347 1.0000
9.500 0.9810 0.02137 0.01488 0.0109 0.0340 1.0000
9.750 1.0008 0.02206 0.01561 0.0120 0.0331 1.0000
10.000 1.0204 0.02277 0.01637 0.0131 0.0323 1.0000
10.250 1.0395 0.02365 0.01727 0.0142 0.0316 1.0000
10.500 1.0580 0.02511 0.01875 0.0152 0.0309 1.0000
10.750 1.0747 0.02689 0.02068 0.0165 0.0302 1.0000
11.000 1.0917 0.02757 0.02151 0.0179 0.0297 1.0000
11.250 1.1078 0.02844 0.02253 0.0194 0.0289 1.0000
11.500 1.1231 0.02946 0.02367 0.0208 0.0282 1.0000
11.750 1.1375 0.03054 0.02485 0.0223 0.0276 1.0000
12.000 1.1509 0.03160 0.02600 0.0239 0.0271 1.0000
12.250 1.1621 0.03269 0.02717 0.0256 0.0266 1.0000
12.500 1.1716 0.03388 0.02841 0.0276 0.0262 1.0000
12.750 1.1784 0.03625 0.03086 0.0293 0.0256 1.0000
13.000 1.1732 0.03852 0.03337 0.0324 0.0252 1.0000
13.250 1.1703 0.03998 0.03503 0.0350 0.0249 1.0000
13.500 1.1661 0.04196 0.03722 0.0369 0.0246 1.0000
13.750 1.1600 0.04442 0.03989 0.0382 0.0242 1.0000
14.000 1.1521 0.04735 0.04301 0.0389 0.0239 1.0000
14.250 1.1422 0.05079 0.04665 0.0389 0.0236 1.0000
14.500 1.1305 0.05477 0.05082 0.0381 0.0234 1.0000
14.750 1.1162 0.05946 0.05569 0.0363 0.0232 1.0000
15.000 1.0980 0.06518 0.06160 0.0335 0.0231 1.0000
15.250 1.0723 0.07266 0.06930 0.0290 0.0230 1.0000
15.500 1.0308 0.08385 0.08078 0.0215 0.0232 1.0000
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