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MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il)
Reynolds number: 100,000
Max Cl/Cd: 21.74 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-marske1-il-100000.txt
Download as CSV file: xf-marske1-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MARSKE XM-1D AIRFOIL (F14-3.0)                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5039   0.13926   0.13465   0.0293   1.0000   0.1109
 -11.750  -0.5053   0.13617   0.13161   0.0263   1.0000   0.1153
 -11.500  -0.5327   0.13286   0.12840   0.0194   1.0000   0.1176
 -11.250  -0.4930   0.12821   0.12377   0.0230   1.0000   0.1204
 -11.000  -0.4805   0.12492   0.12054   0.0221   1.0000   0.1243
 -10.750  -0.4984   0.12194   0.11764   0.0164   1.0000   0.1298
 -10.500  -0.4900   0.11710   0.11288   0.0150   1.0000   0.1325
 -10.250  -0.4633   0.11393   0.10976   0.0159   1.0000   0.1372
 -10.000  -0.4824   0.11097   0.10687   0.0103   0.8894   0.1442
  -9.750  -0.4609   0.10619   0.10181   0.0086   0.8329   0.1482
  -9.500  -0.4429   0.10358   0.09903   0.0091   0.8080   0.1537
  -9.000  -0.4462   0.09635   0.09173   0.0049   0.7830   0.1648
  -8.750  -0.4364   0.09363   0.08896   0.0046   0.7701   0.1712
  -8.500  -0.5280   0.08994   0.08532  -0.0044   0.7702   0.1765
  -8.250  -0.4441   0.08607   0.08142   0.0006   0.7516   0.1819
  -8.000  -0.4437   0.08292   0.07828  -0.0007   0.7422   0.1884
  -7.750  -0.5168   0.07913   0.07444  -0.0042   0.7404   0.1950
  -7.500  -0.4720   0.07579   0.07113  -0.0021   0.7275   0.1990
  -7.250  -0.4710   0.07326   0.06857  -0.0018   0.7182   0.2062
  -7.000  -0.4921   0.06985   0.06503  -0.0019   0.7126   0.2147
  -6.750  -0.4706   0.06734   0.06255  -0.0007   0.7016   0.2214
  -6.500  -0.4828   0.06447   0.05952  -0.0003   0.6953   0.2336
  -6.250  -0.4645   0.06223   0.05730   0.0008   0.6854   0.2431
  -6.000  -0.4599   0.05947   0.05447   0.0020   0.6776   0.2561
  -5.750  -0.4564   0.05723   0.05212   0.0033   0.6701   0.2731
  -5.500  -0.4492   0.05519   0.04999   0.0048   0.6615   0.2916
  -5.250  -0.4427   0.03946   0.03140   0.0026   0.6623   0.1162
  -5.000  -0.4214   0.03631   0.02795   0.0039   0.6549   0.1087
  -4.750  -0.3976   0.03430   0.02544   0.0052   0.6451   0.1025
  -4.500  -0.3740   0.03266   0.02348   0.0065   0.6378   0.1004
  -4.250  -0.3478   0.03128   0.02188   0.0071   0.6279   0.0996
  -4.000  -0.3222   0.03011   0.02041   0.0082   0.6207   0.0988
  -3.750  -0.2939   0.02901   0.01910   0.0086   0.6110   0.0975
  -3.500  -0.2663   0.02808   0.01791   0.0094   0.6037   0.0966
  -3.250  -0.2370   0.02728   0.01708   0.0095   0.5944   0.0964
  -3.000  -0.2087   0.02654   0.01627   0.0100   0.5874   0.0968
  -2.750  -0.1806   0.02599   0.01577   0.0101   0.5795   0.0984
  -2.500  -0.1534   0.02549   0.01527   0.0106   0.5717   0.1009
  -2.250  -0.1276   0.02504   0.01473   0.0116   0.5664   0.1032
  -2.000  -0.1008   0.02476   0.01455   0.0118   0.5571   0.1049
  -1.750  -0.0772   0.02424   0.01408   0.0130   0.5515   0.1074
  -1.500  -0.0536   0.02400   0.01386   0.0140   0.5458   0.1113
  -1.250  -0.0288   0.02392   0.01380   0.0146   0.5378   0.1171
  -1.000  -0.0056   0.02352   0.01343   0.0160   0.5327   0.1286
  -0.750   0.0161   0.02308   0.01338   0.0172   0.5274   0.1747
  -0.500   0.0471   0.02122   0.01425   0.0180   0.5200   0.8200
  -0.250   0.1052   0.02207   0.01495   0.0157   0.5139   0.9044
   0.000   0.1957   0.02335   0.01606   0.0060   0.5036   0.9448
   0.250   0.2814   0.02360   0.01603  -0.0034   0.4965   0.9743
   0.500   0.3704   0.02362   0.01592  -0.0152   0.4873   1.0000
   0.750   0.3917   0.02379   0.01602  -0.0144   0.4820   1.0000
   1.000   0.4125   0.02379   0.01589  -0.0132   0.4783   1.0000
   1.250   0.4336   0.02402   0.01603  -0.0123   0.4746   1.0000
   1.500   0.4555   0.02484   0.01696  -0.0125   0.4674   1.0000
   1.750   0.4764   0.02495   0.01700  -0.0115   0.4629   1.0000
   2.000   0.4972   0.02491   0.01683  -0.0101   0.4596   1.0000
   2.250   0.5177   0.02579   0.01778  -0.0099   0.4541   1.0000
   2.500   0.5378   0.02673   0.01879  -0.0097   0.4483   1.0000
   2.750   0.5580   0.02699   0.01900  -0.0086   0.4446   1.0000
   3.000   0.5787   0.02698   0.01887  -0.0070   0.4417   1.0000
   3.250   0.5963   0.02841   0.02044  -0.0069   0.4355   1.0000
   3.500   0.6136   0.02966   0.02178  -0.0066   0.4297   1.0000
   3.750   0.6330   0.03002   0.02211  -0.0053   0.4263   1.0000
   4.000   0.6536   0.03007   0.02207  -0.0036   0.4239   1.0000
   4.250   0.6650   0.03249   0.02468  -0.0037   0.4177   1.0000
   4.500   0.6752   0.03468   0.02701  -0.0036   0.4110   1.0000
   4.750   0.6941   0.03490   0.02719  -0.0018   0.4079   1.0000
   5.000   0.7159   0.03475   0.02695   0.0001   0.4058   1.0000
   5.250   0.7382   0.03469   0.02678   0.0020   0.4040   1.0000
   5.500   0.6956   0.04429   0.03690  -0.0007   0.3907   1.0000
   5.750   0.7211   0.04349   0.03604   0.0018   0.3886   1.0000
   6.000   0.7515   0.04221   0.03467   0.0042   0.3871   1.0000
   6.250   0.5643   0.06334   0.05598   0.0008   0.3747   1.0000
   6.500   0.6515   0.05883   0.05150   0.0022   0.3701   1.0000
   6.750   0.7274   0.05300   0.04563   0.0064   0.3688   1.0000
   7.000   0.7939   0.04734   0.03987   0.0102   0.3682   1.0000
   7.250   0.5821   0.07078   0.06334   0.0052   0.3541   1.0000
   7.500   0.6941   0.06302   0.05561   0.0091   0.3504   1.0000
   7.750   0.5639   0.07753   0.07007   0.0054   0.3429   1.0000
   8.000   0.5967   0.07688   0.06942   0.0072   0.3364   1.0000
   9.000   0.5968   0.08764   0.08019   0.0075   0.3088   1.0000
   9.250   0.6290   0.08690   0.07947   0.0094   0.3025   1.0000
   9.500   0.6166   0.09110   0.08367   0.0085   0.2941   1.0000
   9.750   0.6275   0.09284   0.08543   0.0089   0.2877   1.0000
  10.000   0.6835   0.08922   0.08184   0.0125   0.2841   1.0000
  10.250   0.6278   0.09903   0.09166   0.0080   0.2738   1.0000
  10.500   0.6763   0.09600   0.08865   0.0112   0.2689   1.0000
  10.750   0.6358   0.10458   0.09724   0.0075   0.2612   1.0000
  11.000   0.6538   0.10555   0.09823   0.0082   0.2554   1.0000
  11.250   0.6649   0.10748   0.10018   0.0085   0.2496   1.0000
  11.500   0.6407   0.11427   0.10700   0.0056   0.2448   1.0000
  11.750   0.6726   0.11346   0.10622   0.0074   0.2390   1.0000
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