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MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) (marske2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) (marske2-il)
Reynolds number: 50,000
Max Cl/Cd: 18.94 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-marske2-il-50000.txt
Download as CSV file: xf-marske2-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYB
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5412   0.14660   0.13931   0.0173   1.0000   0.2111
 -12.000  -0.5129   0.14062   0.13331   0.0190   1.0000   0.2214
 -11.750  -0.5412   0.14056   0.13338   0.0156   1.0000   0.2282
 -11.500  -0.5117   0.13496   0.12776   0.0175   1.0000   0.2428
 -11.250  -0.4972   0.13077   0.12359   0.0180   1.0000   0.2547
 -11.000  -0.4956   0.12751   0.12039   0.0176   1.0000   0.2667
 -10.750  -0.5185   0.12689   0.11987   0.0159   1.0000   0.2786
 -10.500  -0.4999   0.12257   0.11557   0.0170   1.0000   0.2948
 -10.250  -0.4848   0.11862   0.11165   0.0179   1.0000   0.3107
 -10.000  -0.4782   0.11540   0.10847   0.0185   1.0000   0.3278
  -9.750  -0.4809   0.11302   0.10616   0.0190   1.0000   0.3462
  -9.500  -0.4514   0.10838   0.10152   0.0208   1.0000   0.3707
  -9.250  -0.4496   0.10614   0.09934   0.0220   1.0000   0.3956
  -9.000  -0.4334   0.10251   0.09575   0.0232   1.0000   0.4196
  -8.750  -0.4300   0.10040   0.09370   0.0249   1.0000   0.4472
  -8.500  -0.4061   0.09633   0.08964   0.0259   1.0000   0.4721
  -8.250  -0.4015   0.09401   0.08739   0.0278   1.0000   0.5026
  -8.000  -0.3859   0.09126   0.08468   0.0292   1.0000   0.5331
  -6.750  -0.5582   0.06450   0.05854   0.0111   1.0000   0.3498
  -6.500  -0.6012   0.05373   0.04667   0.0033   1.0000   0.2235
  -6.250  -0.5951   0.04909   0.04136   0.0048   1.0000   0.1892
  -6.000  -0.5842   0.04573   0.03747   0.0072   1.0000   0.1729
  -5.750  -0.5742   0.04293   0.03408   0.0101   1.0000   0.1638
  -5.500  -0.5587   0.04083   0.03156   0.0126   1.0000   0.1599
  -5.250  -0.5409   0.03824   0.02880   0.0145   1.0000   0.1571
  -5.000  -0.5224   0.03598   0.02628   0.0165   1.0000   0.1539
  -4.750  -0.5037   0.03411   0.02416   0.0185   1.0000   0.1537
  -4.500  -0.4846   0.03248   0.02231   0.0204   1.0000   0.1552
  -4.250  -0.4644   0.03097   0.02059   0.0221   1.0000   0.1560
  -4.000  -0.4432   0.02963   0.01908   0.0237   1.0000   0.1570
  -3.750  -0.4236   0.02864   0.01789   0.0254   1.0000   0.1604
  -3.500  -0.3977   0.02727   0.01659   0.0259   1.0000   0.1652
  -3.250  -0.3692   0.02627   0.01566   0.0261   1.0000   0.1705
  -3.000   0.0269   0.02271   0.01465  -0.0200   1.0000   1.0000
  -2.750   0.0415   0.02237   0.01424  -0.0190   1.0000   1.0000
  -2.500   0.0546   0.02215   0.01398  -0.0177   1.0000   1.0000
  -2.250   0.0638   0.02208   0.01394  -0.0160   1.0000   1.0000
  -2.000   0.0628   0.02239   0.01434  -0.0132   1.0000   1.0000
  -1.750   0.0570   0.02314   0.01515  -0.0110   0.9922   1.0000
  -1.500   0.2072   0.02169   0.01341  -0.0329   0.8963   1.0000
  -1.250   0.2532   0.02153   0.01271  -0.0341   0.7919   1.0000
  -1.000   0.2678   0.02197   0.01265  -0.0302   0.7169   1.0000
  -0.750   0.2834   0.02238   0.01266  -0.0271   0.6582   1.0000
  -0.500   0.3012   0.02266   0.01264  -0.0249   0.6131   1.0000
  -0.250   0.3204   0.02290   0.01260  -0.0231   0.5791   1.0000
   0.000   0.3404   0.02318   0.01265  -0.0216   0.5519   1.0000
   0.250   0.3608   0.02353   0.01280  -0.0202   0.5299   1.0000
   0.500   0.3820   0.02392   0.01302  -0.0191   0.5110   1.0000
   0.750   0.4035   0.02436   0.01333  -0.0181   0.4940   1.0000
   1.000   0.4251   0.02488   0.01375  -0.0172   0.4797   1.0000
   1.250   0.4466   0.02543   0.01420  -0.0162   0.4678   1.0000
   1.500   0.4679   0.02601   0.01469  -0.0152   0.4564   1.0000
   1.750   0.4887   0.02672   0.01544  -0.0143   0.4454   1.0000
   2.000   0.5098   0.02735   0.01590  -0.0132   0.4367   1.0000
   2.250   0.5297   0.02830   0.01702  -0.0125   0.4277   1.0000
   2.500   0.5505   0.02907   0.01771  -0.0114   0.4210   1.0000
   2.750   0.5690   0.03026   0.01908  -0.0106   0.4135   1.0000
   3.000   0.5883   0.03119   0.02002  -0.0095   0.4065   1.0000
   3.250   0.6067   0.03231   0.02116  -0.0084   0.4004   1.0000
   3.500   0.6223   0.03389   0.02298  -0.0076   0.3945   1.0000
   3.750   0.6392   0.03525   0.02442  -0.0065   0.3898   1.0000
   4.000   0.6587   0.03631   0.02537  -0.0051   0.3855   1.0000
   4.250   0.6659   0.03884   0.02829  -0.0042   0.3808   1.0000
   4.500   0.6750   0.04102   0.03066  -0.0030   0.3761   1.0000
   4.750   0.6862   0.04295   0.03269  -0.0017   0.3724   1.0000
   5.000   0.6988   0.04484   0.03461  -0.0003   0.3698   1.0000
   5.250   0.7020   0.04778   0.03770   0.0010   0.3677   1.0000
   5.500   0.6892   0.05216   0.04232   0.0021   0.3666   1.0000
   5.750   0.6706   0.05695   0.04724   0.0032   0.3666   1.0000
   6.000   0.6570   0.06139   0.05173   0.0042   0.3677   1.0000
   6.250   0.3683   0.08552   0.07570  -0.0084   0.5705   1.0000
   6.500   0.3873   0.08819   0.07835  -0.0083   0.5596   1.0000
   6.750   0.3847   0.08968   0.07980  -0.0066   0.5464   1.0000
   7.000   0.3934   0.09207   0.08216  -0.0058   0.5351   1.0000
   7.250   0.4246   0.09579   0.08590  -0.0064   0.5240   1.0000
   7.500   0.4137   0.09662   0.08667  -0.0044   0.5109   1.0000
   7.750   0.4232   0.09941   0.08945  -0.0041   0.5027   1.0000
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