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S3014-095-85 (s3014-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S3014-095-85 (s3014-il)
Reynolds number: 200,000
Max Cl/Cd: 65.19 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3014-il-200000-n5.txt
Download as CSV file: xf-s3014-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3014-095-85                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4468   0.10364   0.10012  -0.0157   1.0000   0.0200
  -9.750  -0.4443   0.09960   0.09611  -0.0173   1.0000   0.0193
  -9.500  -0.4431   0.09536   0.09190  -0.0194   1.0000   0.0190
  -9.250  -0.4430   0.09093   0.08751  -0.0220   1.0000   0.0198
  -9.000  -0.4448   0.08602   0.08265  -0.0250   1.0000   0.0204
  -8.750  -0.4451   0.08193   0.07860  -0.0270   1.0000   0.0198
  -8.500  -0.4482   0.07727   0.07400  -0.0300   1.0000   0.0199
  -8.250  -0.4543   0.07243   0.06923  -0.0334   1.0000   0.0196
  -8.000  -0.4623   0.06706   0.06391  -0.0381   1.0000   0.0192
  -7.750  -0.4677   0.06047   0.05730  -0.0435   1.0000   0.0187
  -7.500  -0.4734   0.05331   0.05001  -0.0474   0.9953   0.0182
  -7.250  -0.4624   0.04323   0.03944  -0.0546   0.9763   0.0176
  -7.000  -0.4479   0.03582   0.03140  -0.0578   0.9636   0.0173
  -6.750  -0.4284   0.03117   0.02616  -0.0591   0.9541   0.0175
  -6.500  -0.4074   0.02788   0.02236  -0.0593   0.9449   0.0178
  -6.250  -0.3853   0.02556   0.01960  -0.0590   0.9363   0.0183
  -6.000  -0.3612   0.02392   0.01759  -0.0587   0.9290   0.0195
  -5.750  -0.3384   0.02229   0.01561  -0.0579   0.9207   0.0202
  -5.500  -0.3143   0.02072   0.01371  -0.0571   0.9141   0.0203
  -5.250  -0.2905   0.01940   0.01215  -0.0563   0.9061   0.0206
  -5.000  -0.2660   0.01829   0.01082  -0.0555   0.8999   0.0209
  -4.750  -0.2416   0.01734   0.00970  -0.0547   0.8921   0.0212
  -4.250  -0.1934   0.01553   0.00768  -0.0530   0.8783   0.0223
  -4.000  -0.1695   0.01480   0.00687  -0.0521   0.8721   0.0232
  -3.750  -0.1445   0.01430   0.00634  -0.0516   0.8644   0.0253
  -3.500  -0.1194   0.01388   0.00582  -0.0509   0.8582   0.0271
  -3.250  -0.0937   0.01347   0.00530  -0.0503   0.8506   0.0282
  -3.000  -0.0681   0.01312   0.00482  -0.0496   0.8442   0.0296
  -2.750  -0.0421   0.01275   0.00442  -0.0491   0.8364   0.0333
  -2.500  -0.0164   0.01238   0.00405  -0.0484   0.8299   0.0461
  -2.250   0.0087   0.01188   0.00377  -0.0480   0.8217   0.1048
  -2.000   0.0335   0.01141   0.00355  -0.0474   0.8151   0.1791
  -1.750   0.0574   0.01081   0.00343  -0.0469   0.8063   0.3012
  -1.500   0.0808   0.01029   0.00331  -0.0461   0.7990   0.4201
  -1.250   0.1019   0.00966   0.00326  -0.0447   0.7903   0.5781
  -1.000   0.1215   0.00904   0.00326  -0.0423   0.7821   0.7521
  -0.750   0.1567   0.00877   0.00322  -0.0429   0.7740   0.8697
  -0.500   0.2111   0.00869   0.00310  -0.0480   0.7644   0.9435
  -0.250   0.2547   0.00867   0.00297  -0.0511   0.7538   0.9774
   0.000   0.2971   0.00865   0.00282  -0.0540   0.7420   0.9984
   0.250   0.3234   0.00867   0.00272  -0.0537   0.7295   1.0000
   0.500   0.3479   0.00870   0.00265  -0.0529   0.7161   1.0000
   0.750   0.3726   0.00875   0.00259  -0.0521   0.7022   1.0000
   1.000   0.3974   0.00880   0.00255  -0.0514   0.6877   1.0000
   1.250   0.4223   0.00887   0.00253  -0.0507   0.6728   1.0000
   1.500   0.4473   0.00895   0.00252  -0.0500   0.6571   1.0000
   1.750   0.4723   0.00905   0.00254  -0.0493   0.6407   1.0000
   2.000   0.4972   0.00916   0.00256  -0.0486   0.6234   1.0000
   2.250   0.5220   0.00929   0.00260  -0.0479   0.6053   1.0000
   2.500   0.5469   0.00944   0.00266  -0.0472   0.5865   1.0000
   2.750   0.5717   0.00960   0.00275  -0.0466   0.5659   1.0000
   3.000   0.5963   0.00979   0.00284  -0.0459   0.5449   1.0000
   3.250   0.6209   0.00999   0.00296  -0.0452   0.5218   1.0000
   3.500   0.6453   0.01022   0.00309  -0.0445   0.4982   1.0000
   3.750   0.6695   0.01048   0.00327  -0.0438   0.4733   1.0000
   4.000   0.6935   0.01076   0.00345  -0.0431   0.4474   1.0000
   4.250   0.7174   0.01106   0.00365  -0.0424   0.4212   1.0000
   4.500   0.7411   0.01139   0.00388  -0.0417   0.3948   1.0000
   4.750   0.7647   0.01173   0.00416  -0.0410   0.3692   1.0000
   5.000   0.7881   0.01211   0.00444  -0.0403   0.3445   1.0000
   5.250   0.8113   0.01249   0.00475  -0.0396   0.3212   1.0000
   5.500   0.8346   0.01288   0.00508  -0.0390   0.2994   1.0000
   5.750   0.8576   0.01330   0.00543  -0.0383   0.2794   1.0000
   6.000   0.8807   0.01371   0.00583  -0.0376   0.2609   1.0000
   6.250   0.9037   0.01412   0.00622  -0.0369   0.2435   1.0000
   6.500   0.9265   0.01456   0.00663  -0.0362   0.2269   1.0000
   6.750   0.9490   0.01500   0.00707  -0.0355   0.2117   1.0000
   7.000   0.9713   0.01546   0.00752  -0.0347   0.1966   1.0000
   7.250   0.9935   0.01594   0.00803  -0.0340   0.1823   1.0000
   7.500   1.0152   0.01643   0.00853  -0.0332   0.1683   1.0000
   7.750   1.0362   0.01699   0.00907  -0.0323   0.1528   1.0000
   8.000   1.0570   0.01755   0.00961  -0.0314   0.1353   1.0000
   8.250   1.0767   0.01819   0.01020  -0.0305   0.1164   1.0000
   8.500   1.0959   0.01887   0.01083  -0.0294   0.1007   1.0000
   8.750   1.1154   0.01951   0.01152  -0.0284   0.0890   1.0000
   9.000   1.1332   0.02027   0.01225  -0.0272   0.0746   1.0000
   9.250   1.1498   0.02112   0.01304  -0.0260   0.0569   1.0000
   9.500   1.1640   0.02216   0.01397  -0.0244   0.0398   1.0000
   9.750   1.1768   0.02326   0.01503  -0.0227   0.0257   1.0000
  10.000   1.1865   0.02455   0.01629  -0.0206   0.0164   1.0000
  10.250   1.1955   0.02567   0.01749  -0.0183   0.0132   1.0000
  10.500   1.2016   0.02697   0.01887  -0.0157   0.0114   1.0000
  10.750   1.2088   0.02822   0.02028  -0.0136   0.0107   1.0000
  11.000   1.2154   0.02955   0.02177  -0.0115   0.0101   1.0000
  11.250   1.2206   0.03104   0.02341  -0.0097   0.0097   1.0000
  11.500   1.2244   0.03270   0.02522  -0.0079   0.0092   1.0000
  11.750   1.2273   0.03450   0.02717  -0.0064   0.0087   1.0000
  12.000   1.2294   0.03646   0.02927  -0.0052   0.0085   1.0000
  12.250   1.2257   0.03906   0.03201  -0.0041   0.0079   1.0000
  12.500   1.2206   0.04196   0.03506  -0.0033   0.0077   1.0000
  12.750   1.2184   0.04476   0.03801  -0.0029   0.0075   1.0000
  13.000   1.2164   0.04768   0.04110  -0.0029   0.0073   1.0000
  13.250   1.2126   0.05099   0.04457  -0.0032   0.0071   1.0000
  13.500   1.2067   0.05475   0.04849  -0.0039   0.0071   1.0000
  13.750   1.1997   0.05885   0.05276  -0.0050   0.0069   1.0000
  14.000   1.1919   0.06329   0.05736  -0.0064   0.0069   1.0000
  14.250   1.1836   0.06802   0.06225  -0.0082   0.0068   1.0000
  14.500   1.1752   0.07298   0.06737  -0.0102   0.0068   1.0000
  14.750   1.1655   0.07841   0.07295  -0.0126   0.0068   1.0000
  15.000   1.1558   0.08405   0.07878  -0.0153   0.0067   1.0000
  15.250   1.1446   0.09015   0.08503  -0.0182   0.0067   1.0000
  15.500   1.1351   0.09610   0.09113  -0.0212   0.0067   1.0000
  15.750   1.1234   0.10269   0.09787  -0.0245   0.0066   1.0000
  16.000   1.1131   0.10913   0.10445  -0.0278   0.0067   1.0000
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