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MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID) (marske3-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID) (marske3-il)
Reynolds number: 50,000
Max Cl/Cd: 18.99 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-marske3-il-50000.txt
Download as CSV file: xf-marske3-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4326   0.09892   0.09234   0.0207   1.0000   0.4012
  -8.500  -0.4460   0.09747   0.09102   0.0225   1.0000   0.4275
  -6.750  -0.4934   0.06868   0.06290   0.0165   1.0000   0.3992
  -6.500  -0.6029   0.05556   0.04816   0.0036   1.0000   0.1943
  -6.250  -0.5844   0.05040   0.04283   0.0045   1.0000   0.1720
  -6.000  -0.5744   0.04670   0.03861   0.0069   1.0000   0.1560
  -5.750  -0.5647   0.04382   0.03500   0.0103   1.0000   0.1443
  -5.500  -0.5485   0.04095   0.03195   0.0122   1.0000   0.1419
  -5.250  -0.5329   0.03854   0.02927   0.0145   1.0000   0.1409
  -5.000  -0.5154   0.03631   0.02676   0.0167   1.0000   0.1399
  -4.750  -0.4958   0.03419   0.02438   0.0186   1.0000   0.1384
  -4.500  -0.4751   0.03232   0.02226   0.0203   1.0000   0.1378
  -4.250  -0.4549   0.03081   0.02056   0.0220   1.0000   0.1401
  -4.000  -0.4352   0.02956   0.01911   0.0237   1.0000   0.1433
  -3.750  -0.4154   0.02853   0.01787   0.0254   1.0000   0.1456
  -3.500  -0.3861   0.02707   0.01659   0.0252   1.0000   0.1504
  -3.250   0.0111   0.02282   0.01476  -0.0217   1.0000   1.0000
  -3.000   0.0281   0.02252   0.01436  -0.0208   1.0000   1.0000
  -2.750   0.0441   0.02231   0.01410  -0.0198   1.0000   1.0000
  -2.500   0.0571   0.02227   0.01407  -0.0186   1.0000   1.0000
  -2.250   0.0591   0.02266   0.01457  -0.0163   1.0000   1.0000
  -2.000   0.0916   0.02314   0.01505  -0.0210   0.9710   1.0000
  -1.750   0.2142   0.02194   0.01344  -0.0383   0.8774   1.0000
  -1.500   0.2503   0.02200   0.01299  -0.0384   0.8002   1.0000
  -1.250   0.2680   0.02245   0.01303  -0.0355   0.7435   1.0000
  -1.000   0.2857   0.02292   0.01318  -0.0330   0.6979   1.0000
  -0.750   0.3042   0.02332   0.01334  -0.0309   0.6588   1.0000
  -0.500   0.3234   0.02363   0.01346  -0.0291   0.6265   1.0000
  -0.250   0.3426   0.02390   0.01348  -0.0272   0.6012   1.0000
   0.000   0.3623   0.02421   0.01368  -0.0258   0.5768   1.0000
   0.250   0.3830   0.02453   0.01383  -0.0244   0.5566   1.0000
   0.500   0.4041   0.02489   0.01405  -0.0233   0.5389   1.0000
   0.750   0.4253   0.02533   0.01439  -0.0222   0.5228   1.0000
   1.000   0.4463   0.02583   0.01481  -0.0211   0.5082   1.0000
   1.250   0.4671   0.02635   0.01526  -0.0200   0.4953   1.0000
   1.500   0.4880   0.02682   0.01557  -0.0187   0.4844   1.0000
   1.750   0.5085   0.02761   0.01645  -0.0181   0.4728   1.0000
   2.000   0.5288   0.02835   0.01717  -0.0171   0.4634   1.0000
   2.250   0.5489   0.02908   0.01788  -0.0160   0.4538   1.0000
   2.500   0.5678   0.03006   0.01895  -0.0151   0.4449   1.0000
   2.750   0.5872   0.03092   0.01980  -0.0140   0.4372   1.0000
   3.000   0.6053   0.03210   0.02107  -0.0130   0.4306   1.0000
   3.250   0.6217   0.03347   0.02258  -0.0121   0.4235   1.0000
   3.500   0.6415   0.03423   0.02326  -0.0107   0.4177   1.0000
   3.750   0.6529   0.03625   0.02556  -0.0099   0.4109   1.0000
   4.000   0.6666   0.03784   0.02727  -0.0087   0.4054   1.0000
   4.250   0.6839   0.03901   0.02842  -0.0073   0.4012   1.0000
   4.500   0.6887   0.04177   0.03144  -0.0063   0.3972   1.0000
   4.750   0.6879   0.04496   0.03487  -0.0051   0.3929   1.0000
   5.000   0.6910   0.04747   0.03750  -0.0036   0.3887   1.0000
   5.250   0.7070   0.04866   0.03866  -0.0018   0.3847   1.0000
   5.500   0.7056   0.05186   0.04196  -0.0003   0.3830   1.0000
   5.750   0.6855   0.05672   0.04696   0.0010   0.3829   1.0000
   6.000   0.6636   0.06160   0.05191   0.0022   0.3836   1.0000
   6.250   0.3665   0.08441   0.07447  -0.0071   0.5772   1.0000
   6.500   0.3947   0.08798   0.07804  -0.0078   0.5677   1.0000
   6.750   0.3932   0.08918   0.07921  -0.0060   0.5545   1.0000
   7.000   0.3927   0.09100   0.08098  -0.0046   0.5428   1.0000
   7.250   0.4156   0.09442   0.08441  -0.0049   0.5334   1.0000
   7.750   0.4218   0.09792   0.08788  -0.0025   0.5067   1.0000
   8.000   0.4360   0.10110   0.09105  -0.0025   0.4989   1.0000
   8.250   0.4493   0.10352   0.09348  -0.0020   0.4863   1.0000
   8.500   0.4455   0.10513   0.09506  -0.0009   0.4736   1.0000
   8.750   0.4582   0.10823   0.09816  -0.0007   0.4645   1.0000
   9.000   0.4705   0.11076   0.10073  -0.0004   0.4532   1.0000
   9.250   0.4667   0.11278   0.10272   0.0001   0.4441   1.0000
   9.500   0.4956   0.11696   0.10696  -0.0002   0.4348   1.0000
   9.750   0.4827   0.11788   0.10784   0.0006   0.4234   1.0000
  10.000   0.5095   0.12259   0.11259   0.0002   0.4163   1.0000
  10.250   0.4991   0.12329   0.11328   0.0008   0.4051   1.0000
  10.500   0.5292   0.12874   0.11881   0.0002   0.3999   1.0000
  10.750   0.5106   0.12863   0.11866   0.0007   0.3894   1.0000
  11.000   0.5421   0.13427   0.12437   0.0002   0.3831   1.0000
  11.250   0.5246   0.13410   0.12417   0.0005   0.3724   1.0000
  11.500   0.5630   0.14073   0.13092   0.0000   0.3668   1.0000
  11.750   0.5357   0.13958   0.12969  -0.0001   0.3580   1.0000
  12.000   0.5570   0.14379   0.13398  -0.0004   0.3518   1.0000
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