Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA M12 (nacam12-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M12 (nacam12-il)
Reynolds number: 500,000
Max Cl/Cd: 62.65 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacam12-il-500000-n5.txt
Download as CSV file: xf-nacam12-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M12                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -1.0198   0.05439   0.05125  -0.0510   1.0000   0.0190
 -14.250  -1.0441   0.04803   0.04466  -0.0547   1.0000   0.0190
 -14.000  -1.0534   0.04462   0.04112  -0.0552   1.0000   0.0192
 -13.750  -1.0568   0.04225   0.03864  -0.0546   1.0000   0.0193
 -13.500  -1.0548   0.04059   0.03691  -0.0535   1.0000   0.0195
 -13.250  -1.0519   0.03914   0.03537  -0.0519   1.0000   0.0197
 -13.000  -1.0485   0.03781   0.03395  -0.0498   1.0000   0.0199
 -12.750  -1.0436   0.03657   0.03262  -0.0476   1.0000   0.0201
 -12.500  -1.0355   0.03520   0.03111  -0.0459   1.0000   0.0203
 -12.250  -1.0254   0.03388   0.02966  -0.0444   1.0000   0.0206
 -12.000  -1.0139   0.03257   0.02820  -0.0429   1.0000   0.0210
 -11.750  -1.0014   0.03126   0.02673  -0.0414   1.0000   0.0215
 -11.500  -0.9882   0.02994   0.02523  -0.0399   1.0000   0.0219
 -11.250  -0.9738   0.02868   0.02379  -0.0384   1.0000   0.0224
 -11.000  -0.9584   0.02751   0.02243  -0.0370   1.0000   0.0227
 -10.750  -0.9417   0.02652   0.02127  -0.0356   1.0000   0.0230
 -10.500  -0.9237   0.02576   0.02036  -0.0343   1.0000   0.0232
 -10.250  -0.9107   0.02423   0.01870  -0.0325   1.0000   0.0237
 -10.000  -0.8940   0.02338   0.01780  -0.0309   1.0000   0.0241
  -9.750  -0.8769   0.02266   0.01703  -0.0293   1.0000   0.0244
  -9.500  -0.8599   0.02199   0.01628  -0.0276   1.0000   0.0247
  -9.250  -0.8304   0.02121   0.01542  -0.0285   0.9968   0.0251
  -9.000  -0.7995   0.02049   0.01462  -0.0297   0.9938   0.0256
  -8.750  -0.7700   0.01976   0.01380  -0.0305   0.9894   0.0262
  -8.500  -0.7400   0.01899   0.01292  -0.0315   0.9847   0.0266
  -8.250  -0.7105   0.01826   0.01209  -0.0322   0.9790   0.0270
  -8.000  -0.6804   0.01757   0.01131  -0.0330   0.9727   0.0274
  -7.750  -0.6512   0.01696   0.01062  -0.0335   0.9650   0.0278
  -7.500  -0.6209   0.01645   0.01002  -0.0342   0.9568   0.0282
  -7.250  -0.5931   0.01600   0.00950  -0.0343   0.9460   0.0285
  -7.000  -0.5674   0.01523   0.00865  -0.0341   0.9347   0.0289
  -6.750  -0.5422   0.01461   0.00797  -0.0337   0.9232   0.0294
  -6.500  -0.5174   0.01413   0.00743  -0.0331   0.9108   0.0298
  -6.250  -0.4924   0.01372   0.00697  -0.0325   0.8992   0.0303
  -6.000  -0.4673   0.01336   0.00654  -0.0320   0.8876   0.0307
  -5.750  -0.4420   0.01302   0.00614  -0.0315   0.8757   0.0312
  -5.500  -0.4164   0.01271   0.00577  -0.0310   0.8642   0.0317
  -5.250  -0.3906   0.01243   0.00542  -0.0305   0.8530   0.0323
  -5.000  -0.3646   0.01217   0.00510  -0.0301   0.8411   0.0330
  -4.750  -0.3382   0.01193   0.00480  -0.0298   0.8297   0.0337
  -4.500  -0.3118   0.01172   0.00452  -0.0295   0.8183   0.0343
  -4.250  -0.2852   0.01152   0.00425  -0.0292   0.8068   0.0348
  -4.000  -0.2586   0.01127   0.00396  -0.0289   0.7951   0.0358
  -3.750  -0.2318   0.01109   0.00374  -0.0286   0.7841   0.0371
  -3.500  -0.2048   0.01094   0.00355  -0.0284   0.7727   0.0385
  -3.250  -0.1775   0.01081   0.00338  -0.0282   0.7615   0.0403
  -3.000  -0.1503   0.01069   0.00322  -0.0280   0.7507   0.0430
  -2.750  -0.1233   0.01052   0.00306  -0.0279   0.7395   0.0495
  -2.500  -0.0967   0.01029   0.00289  -0.0277   0.7287   0.0673
  -2.250  -0.0655   0.01080   0.00357  -0.0281   0.7178   0.1000
  -2.000  -0.0388   0.01060   0.00329  -0.0279   0.7067   0.1148
  -1.750  -0.0106   0.01064   0.00325  -0.0279   0.6957   0.1194
  -1.500   0.0182   0.01080   0.00335  -0.0280   0.6847   0.1231
  -1.250   0.0465   0.01086   0.00333  -0.0280   0.6730   0.1261
  -1.000   0.0744   0.01085   0.00328  -0.0280   0.6617   0.1276
  -0.750   0.1023   0.01088   0.00327  -0.0279   0.6501   0.1297
  -0.500   0.1303   0.01091   0.00325  -0.0279   0.6378   0.1321
  -0.250   0.1586   0.01100   0.00328  -0.0280   0.6257   0.1347
   0.000   0.1858   0.01090   0.00317  -0.0279   0.6135   0.1369
   0.250   0.2131   0.01086   0.00310  -0.0278   0.6011   0.1381
   0.500   0.2405   0.01081   0.00303  -0.0277   0.5883   0.1385
   0.750   0.2680   0.01078   0.00298  -0.0277   0.5762   0.1395
   1.000   0.2954   0.01076   0.00294  -0.0276   0.5639   0.1404
   1.500   0.3500   0.01074   0.00287  -0.0274   0.5394   0.1410
   1.750   0.3773   0.01073   0.00285  -0.0274   0.5276   0.1410
   2.000   0.4044   0.01074   0.00284  -0.0273   0.5151   0.1410
   2.250   0.4313   0.01077   0.00284  -0.0271   0.4997   0.1411
   2.500   0.4582   0.01081   0.00285  -0.0270   0.4837   0.1412
   2.750   0.4854   0.01084   0.00287  -0.0269   0.4705   0.1413
   3.000   0.5126   0.01087   0.00290  -0.0269   0.4589   0.1414
   3.250   0.5396   0.01092   0.00295  -0.0268   0.4467   0.1416
   3.500   0.5666   0.01098   0.00300  -0.0267   0.4347   0.1418
   3.750   0.5937   0.01104   0.00307  -0.0266   0.4220   0.1420
   4.000   0.6206   0.01112   0.00315  -0.0265   0.4094   0.1422
   4.250   0.6472   0.01123   0.00324  -0.0263   0.3945   0.1425
   4.500   0.6726   0.01144   0.00336  -0.0260   0.3668   0.1427
   4.750   0.6978   0.01169   0.00351  -0.0257   0.3354   0.1430
   5.000   0.7229   0.01195   0.00367  -0.0254   0.3061   0.1433
   5.250   0.7479   0.01221   0.00386  -0.0250   0.2791   0.1436
   5.500   0.7724   0.01251   0.00406  -0.0246   0.2521   0.1440
   5.750   0.7970   0.01282   0.00428  -0.0242   0.2258   0.1445
   6.000   0.8212   0.01315   0.00454  -0.0238   0.2017   0.1450
   6.250   0.8453   0.01350   0.00482  -0.0234   0.1788   0.1455
   6.500   0.8691   0.01388   0.00512  -0.0229   0.1584   0.1461
   6.750   0.8928   0.01425   0.00543  -0.0224   0.1382   0.1467
   7.250   0.9375   0.01522   0.00620  -0.0210   0.0907   0.1481
   7.500   0.9595   0.01572   0.00662  -0.0203   0.0739   0.1489
   7.750   0.9819   0.01616   0.00704  -0.0196   0.0635   0.1497
   8.000   1.0047   0.01654   0.00744  -0.0190   0.0570   0.1506
   8.250   1.0267   0.01699   0.00788  -0.0182   0.0516   0.1515
   8.500   1.0493   0.01735   0.00828  -0.0175   0.0483   0.1529
   8.750   1.0707   0.01779   0.00875  -0.0167   0.0449   0.1548
   9.000   1.0919   0.01823   0.00923  -0.0159   0.0423   0.1567
   9.250   1.1134   0.01862   0.00968  -0.0151   0.0404   0.1586
   9.500   1.1338   0.01907   0.01017  -0.0141   0.0384   0.1605
   9.750   1.1529   0.01959   0.01072  -0.0130   0.0364   0.1636
  10.000   1.1714   0.02011   0.01132  -0.0118   0.0349   0.1695
  10.250   1.1905   0.02047   0.01190  -0.0108   0.0336   0.2867
  10.500   1.2078   0.02094   0.01247  -0.0094   0.0322   0.3152
  11.000   1.2365   0.02086   0.01396  -0.0059   0.0294   1.0000
  11.500   1.2639   0.02221   0.01544  -0.0025   0.0274   1.0000
  11.750   1.2776   0.02295   0.01623  -0.0010   0.0262   1.0000
  12.000   1.2904   0.02378   0.01710   0.0004   0.0250   1.0000
  12.250   1.3012   0.02480   0.01815   0.0019   0.0238   1.0000
  12.500   1.3129   0.02580   0.01923   0.0032   0.0229   1.0000
  12.750   1.3245   0.02685   0.02036   0.0043   0.0220   1.0000
  13.000   1.3353   0.02801   0.02159   0.0054   0.0210   1.0000
  13.250   1.3451   0.02930   0.02293   0.0064   0.0201   1.0000
  13.500   1.3532   0.03080   0.02447   0.0073   0.0192   1.0000
  13.750   1.3611   0.03237   0.02612   0.0080   0.0185   1.0000
  14.000   1.3688   0.03401   0.02787   0.0087   0.0178   1.0000
  14.250   1.3757   0.03580   0.02973   0.0091   0.0170   1.0000
  14.500   1.3814   0.03775   0.03176   0.0095   0.0163   1.0000
  14.750   1.3854   0.03995   0.03402   0.0098   0.0157   1.0000
  15.000   1.3868   0.04249   0.03664   0.0099   0.0152   1.0000
  15.250   1.3884   0.04507   0.03932   0.0099   0.0148   1.0000
  15.500   1.3892   0.04782   0.04218   0.0097   0.0145   1.0000
  15.750   1.3888   0.05078   0.04525   0.0094   0.0141   1.0000
  16.000   1.3873   0.05394   0.04852   0.0089   0.0138   1.0000
  16.250   1.3847   0.05735   0.05204   0.0082   0.0135   1.0000
  16.500   1.3812   0.06099   0.05579   0.0073   0.0131   1.0000
  16.750   1.3763   0.06491   0.05980   0.0063   0.0129   1.0000
  17.000   1.3698   0.06914   0.06414   0.0050   0.0126   1.0000
  17.250   1.3620   0.07367   0.06877   0.0035   0.0124   1.0000
  17.500   1.3522   0.07859   0.07380   0.0017   0.0122   1.0000
  17.750   1.3404   0.08389   0.07921  -0.0002   0.0120   1.0000
  18.000   1.3288   0.08929   0.08472  -0.0023   0.0118   1.0000
  18.250   1.3186   0.09457   0.09012  -0.0044   0.0117   1.0000
  18.500   1.3075   0.10005   0.09573  -0.0067   0.0116   1.0000
  18.750   1.2960   0.10570   0.10150  -0.0091   0.0114   1.0000
  19.000   1.2842   0.11151   0.10743  -0.0117   0.0113   1.0000
  19.250   1.2718   0.11751   0.11355  -0.0144   0.0112   1.0000
<< Back to NACA M12 (nacam12-il)

Polar data table (+)

Polar graphs


<< Back to NACA M12 (nacam12-il)