Airfoil Tools
Search 1638 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.53 at α=12°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-marske5-il-1000000-n5.txt
Download as CSV file: xf-marske5-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MARSKE MONARCH AIRFOIL (NACA 43012A)            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -1.1652   0.04952   0.04656  -0.0473   1.0000   0.0086
 -16.250  -1.1893   0.04440   0.04124  -0.0481   1.0000   0.0086
 -16.000  -1.2091   0.04039   0.03704  -0.0471   1.0000   0.0087
 -15.750  -1.2175   0.03772   0.03421  -0.0454   1.0000   0.0087
 -15.500  -1.2270   0.03514   0.03148  -0.0430   1.0000   0.0088
 -15.250  -1.2275   0.03338   0.02960  -0.0406   1.0000   0.0089
 -15.000  -1.2269   0.03174   0.02783  -0.0380   1.0000   0.0089
 -14.750  -1.2236   0.03035   0.02634  -0.0353   1.0000   0.0090
 -14.500  -1.2190   0.02906   0.02494  -0.0325   1.0000   0.0091
 -14.250  -1.2122   0.02795   0.02374  -0.0297   1.0000   0.0092
 -14.000  -1.2041   0.02695   0.02265  -0.0269   1.0000   0.0093
 -13.750  -1.1946   0.02607   0.02169  -0.0241   1.0000   0.0094
 -13.500  -1.1854   0.02519   0.02072  -0.0212   1.0000   0.0094
 -13.250  -1.1742   0.02439   0.01985  -0.0184   1.0000   0.0096
 -13.000  -1.1606   0.02360   0.01898  -0.0160   1.0000   0.0096
 -12.750  -1.1461   0.02279   0.01808  -0.0138   1.0000   0.0097
 -12.500  -1.1299   0.02208   0.01729  -0.0117   1.0000   0.0099
 -12.250  -1.1129   0.02142   0.01656  -0.0098   1.0000   0.0100
 -12.000  -1.0960   0.02070   0.01576  -0.0078   1.0000   0.0102
 -11.750  -1.0780   0.02006   0.01505  -0.0059   1.0000   0.0103
 -11.500  -1.0597   0.01943   0.01435  -0.0040   1.0000   0.0105
 -11.250  -1.0410   0.01883   0.01368  -0.0022   1.0000   0.0106
 -11.000  -1.0217   0.01827   0.01305  -0.0004   1.0000   0.0107
 -10.750  -1.0020   0.01775   0.01247   0.0013   1.0000   0.0108
 -10.500  -0.9827   0.01717   0.01185   0.0031   1.0000   0.0111
 -10.250  -0.9627   0.01667   0.01132   0.0048   1.0000   0.0114
 -10.000  -0.9422   0.01622   0.01084   0.0064   1.0000   0.0116
  -9.750  -0.9214   0.01582   0.01042   0.0080   1.0000   0.0118
  -9.500  -0.8938   0.01536   0.00994   0.0082   0.9965   0.0120
  -9.250  -0.8624   0.01489   0.00944   0.0076   0.9817   0.0124
  -9.000  -0.7769   0.01433   0.00844  -0.0044   0.8104   0.0130
  -8.750  -0.7575   0.01415   0.00802  -0.0024   0.7589   0.0131
  -8.500  -0.7350   0.01391   0.00765  -0.0011   0.7368   0.0134
  -8.250  -0.7124   0.01359   0.00725   0.0002   0.7183   0.0138
  -8.000  -0.6887   0.01335   0.00696   0.0014   0.7026   0.0141
  -7.750  -0.6644   0.01311   0.00667   0.0024   0.6910   0.0145
  -7.500  -0.6402   0.01288   0.00639   0.0034   0.6760   0.0150
  -7.250  -0.6159   0.01266   0.00610   0.0044   0.6597   0.0154
  -7.000  -0.5917   0.01245   0.00580   0.0055   0.6379   0.0160
  -6.750  -0.5677   0.01227   0.00551   0.0066   0.6077   0.0164
  -6.500  -0.5441   0.01216   0.00527   0.0077   0.5626   0.0170
  -6.250  -0.5201   0.01210   0.00507   0.0088   0.5166   0.0175
  -6.000  -0.4962   0.01207   0.00487   0.0099   0.4639   0.0182
  -5.750  -0.4731   0.01211   0.00465   0.0110   0.3886   0.0187
  -5.500  -0.4492   0.01212   0.00445   0.0121   0.3329   0.0193
  -5.250  -0.4247   0.01201   0.00426   0.0130   0.3069   0.0199
  -4.750  -0.3734   0.01185   0.00401   0.0145   0.2798   0.0214
  -4.500  -0.3478   0.01175   0.00385   0.0153   0.2701   0.0222
  -4.250  -0.3220   0.01164   0.00369   0.0160   0.2633   0.0228
  -4.000  -0.2969   0.01149   0.00351   0.0169   0.2550   0.0235
  -3.750  -0.2709   0.01138   0.00339   0.0176   0.2493   0.0243
  -3.500  -0.2449   0.01129   0.00327   0.0183   0.2433   0.0252
  -3.250  -0.2189   0.01122   0.00316   0.0190   0.2375   0.0261
  -3.000  -0.1927   0.01114   0.00304   0.0196   0.2332   0.0267
  -2.750  -0.1672   0.01098   0.00288   0.0204   0.2291   0.0276
  -2.500  -0.1412   0.01090   0.00278   0.0211   0.2244   0.0287
  -2.250  -0.1151   0.01084   0.00268   0.0217   0.2194   0.0297
  -2.000  -0.0888   0.01076   0.00259   0.0224   0.2161   0.0305
  -1.750  -0.0625   0.01069   0.00250   0.0230   0.2126   0.0314
  -1.500  -0.0366   0.01060   0.00240   0.0237   0.2087   0.0327
  -1.250  -0.0105   0.01056   0.00233   0.0243   0.2036   0.0339
  -1.000   0.0159   0.01052   0.00227   0.0249   0.2003   0.0351
  -0.750   0.0425   0.01048   0.00222   0.0255   0.1974   0.0365
  -0.500   0.0687   0.01043   0.00217   0.0261   0.1942   0.0390
  -0.250   0.0951   0.01041   0.00214   0.0266   0.1908   0.0418
   0.000   0.1213   0.01039   0.00211   0.0272   0.1874   0.0485
   0.250   0.1464   0.01026   0.00210   0.0280   0.1854   0.0850
   0.500   0.1621   0.00946   0.00201   0.0304   0.1839   0.3260
   0.750   0.1700   0.00840   0.00185   0.0343   0.1824   0.6036
   1.000   0.1768   0.00769   0.00186   0.0391   0.1808   0.8031
   1.250   0.2002   0.00766   0.00194   0.0404   0.1787   0.8441
   1.500   0.2261   0.00771   0.00201   0.0411   0.1763   0.8617
   1.750   0.2525   0.00779   0.00208   0.0417   0.1740   0.8745
   2.000   0.2789   0.00788   0.00216   0.0423   0.1715   0.8850
   2.250   0.3063   0.00795   0.00224   0.0427   0.1706   0.8940
   2.500   0.3330   0.00803   0.00232   0.0432   0.1696   0.9028
   2.750   0.3607   0.00811   0.00241   0.0435   0.1683   0.9103
   3.000   0.3881   0.00820   0.00249   0.0438   0.1669   0.9159
   3.250   0.4150   0.00830   0.00256   0.0442   0.1653   0.9192
   3.500   0.4424   0.00840   0.00264   0.0444   0.1637   0.9221
   3.750   0.4708   0.00851   0.00273   0.0444   0.1622   0.9248
   4.000   0.4988   0.00863   0.00284   0.0445   0.1607   0.9279
   4.250   0.5261   0.00876   0.00296   0.0447   0.1591   0.9315
   4.500   0.5522   0.00890   0.00309   0.0452   0.1576   0.9353
   4.750   0.5810   0.00902   0.00321   0.0451   0.1570   0.9381
   5.000   0.6102   0.00914   0.00334   0.0448   0.1564   0.9409
   5.250   0.6387   0.00926   0.00346   0.0447   0.1557   0.9443
   5.500   0.6656   0.00938   0.00359   0.0450   0.1549   0.9484
   5.750   0.6950   0.00951   0.00373   0.0447   0.1537   0.9512
   6.000   0.7255   0.00966   0.00388   0.0441   0.1525   0.9536
   6.250   0.7553   0.00981   0.00403   0.0437   0.1513   0.9563
   6.500   0.7833   0.00996   0.00418   0.0436   0.1501   0.9597
   6.750   0.8115   0.01012   0.00434   0.0434   0.1489   0.9628
   7.000   0.8430   0.01031   0.00453   0.0426   0.1476   0.9643
   7.250   0.8740   0.01052   0.00473   0.0418   0.1461   0.9660
   7.500   0.9037   0.01076   0.00497   0.0412   0.1445   0.9681
   7.750   0.9325   0.01093   0.00517   0.0409   0.1438   0.9707
   8.000   0.9600   0.01108   0.00534   0.0408   0.1431   0.9737
   8.250   0.9922   0.01126   0.00554   0.0397   0.1423   0.9746
   8.500   1.0238   0.01144   0.00575   0.0387   0.1414   0.9757
   8.750   1.0547   0.01164   0.00597   0.0379   0.1405   0.9770
   9.000   1.0847   0.01185   0.00620   0.0372   0.1396   0.9786
   9.250   1.1136   0.01205   0.00643   0.0367   0.1385   0.9805
   9.500   1.1403   0.01227   0.00666   0.0367   0.1374   0.9832
   9.750   1.1692   0.01249   0.00691   0.0362   0.1363   0.9847
  10.000   1.1994   0.01274   0.00717   0.0353   0.1351   0.9857
  10.250   1.2290   0.01301   0.00745   0.0346   0.1337   0.9870
  10.500   1.2577   0.01332   0.00779   0.0340   0.1322   0.9885
  10.750   1.2865   0.01354   0.00806   0.0334   0.1316   0.9901
  11.000   1.3148   0.01377   0.00834   0.0329   0.1308   0.9919
  11.250   1.3421   0.01402   0.00863   0.0326   0.1299   0.9937
  11.500   1.3716   0.01427   0.00893   0.0318   0.1286   0.9950
  11.750   1.4008   0.01453   0.00923   0.0310   0.1272   0.9964
  12.000   1.4296   0.01481   0.00953   0.0303   0.1252   0.9977
  12.250   1.4578   0.01513   0.00987   0.0296   0.1232   0.9989
  12.500   1.4856   0.01550   0.01026   0.0289   0.1209   0.9998
  12.750   1.5046   0.01576   0.01057   0.0301   0.1197   1.0000
  13.000   1.5205   0.01603   0.01089   0.0320   0.1180   1.0000
  13.250   1.5360   0.01633   0.01123   0.0338   0.1160   1.0000
  13.500   1.5507   0.01667   0.01159   0.0357   0.1136   1.0000
  13.750   1.5638   0.01710   0.01202   0.0378   0.1099   1.0000
  14.000   1.5775   0.01750   0.01245   0.0398   0.1066   1.0000
  14.250   1.5843   0.01802   0.01296   0.0429   0.1020   1.0000
  14.500   1.5907   0.01855   0.01351   0.0459   0.0985   1.0000
  14.750   1.5978   0.01917   0.01416   0.0485   0.0953   1.0000
  15.000   1.6041   0.01995   0.01496   0.0509   0.0923   1.0000
  15.250   1.6126   0.02070   0.01577   0.0527   0.0902   1.0000
  15.500   1.6204   0.02159   0.01671   0.0544   0.0881   1.0000
  15.750   1.6256   0.02274   0.01791   0.0558   0.0856   1.0000
  16.000   1.6293   0.02416   0.01938   0.0569   0.0835   1.0000
  16.250   1.6337   0.02570   0.02099   0.0575   0.0810   1.0000
  16.500   1.6395   0.02727   0.02264   0.0577   0.0799   1.0000
  16.750   1.6404   0.02938   0.02483   0.0576   0.0776   1.0000
  17.000   1.6361   0.03213   0.02764   0.0573   0.0752   1.0000
  17.250   1.6303   0.03517   0.03077   0.0566   0.0732   1.0000
  17.500   1.6268   0.03812   0.03382   0.0557   0.0718   1.0000
  17.750   1.6160   0.04202   0.03784   0.0543   0.0700   1.0000
  18.000   1.5987   0.04695   0.04289   0.0522   0.0688   1.0000
  18.250   1.5597   0.05501   0.05111   0.0484   0.0672   1.0000
  18.500   1.5152   0.06432   0.06063   0.0439   0.0677   1.0000
  18.750   1.4660   0.07445   0.07099   0.0391   0.0696   1.0000
  19.000   1.3947   0.08772   0.08446   0.0327   0.0707   1.0000
<< Back to MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il)

Polar data table (+)

Polar graphs


<< Back to MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il)