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S3014-095-85 (s3014-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S3014-095-85 (s3014-il)
Reynolds number: 500,000
Max Cl/Cd: 92.36 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3014-il-500000.txt
Download as CSV file: xf-s3014-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4465   0.10192   0.09969  -0.0177   1.0000   0.0180
  -9.750  -0.4433   0.09789   0.09568  -0.0197   1.0000   0.0180
  -9.500  -0.4522   0.09193   0.08976  -0.0213   1.0000   0.0188
  -9.250  -0.4470   0.08915   0.08699  -0.0221   1.0000   0.0192
  -9.000  -0.4444   0.08566   0.08353  -0.0238   1.0000   0.0195
  -8.750  -0.4421   0.08221   0.08010  -0.0256   1.0000   0.0198
  -8.500  -0.4415   0.07853   0.07646  -0.0276   1.0000   0.0202
  -8.250  -0.4435   0.07452   0.07249  -0.0303   1.0000   0.0204
  -8.000  -0.4500   0.07029   0.06832  -0.0336   1.0000   0.0209
  -7.750  -0.4535   0.06467   0.06272  -0.0395   1.0000   0.0214
  -7.500  -0.4496   0.05788   0.05586  -0.0466   0.9924   0.0218
  -7.000  -0.4236   0.03760   0.03451  -0.0620   0.9603   0.0258
  -6.750  -0.4079   0.03531   0.03219  -0.0619   0.9494   0.0267
  -6.500  -0.3918   0.03377   0.03055  -0.0610   0.9394   0.0277
  -6.250  -0.3763   0.03194   0.02852  -0.0599   0.9298   0.0294
  -6.000  -0.3500   0.03310   0.02931  -0.0583   0.9210   0.0337
  -5.750  -0.3451   0.02669   0.02253  -0.0573   0.9125   0.0362
  -5.500  -0.3235   0.02558   0.02139  -0.0567   0.9049   0.0384
  -5.250  -0.3057   0.01805   0.01270  -0.0530   0.8982   0.0227
  -5.000  -0.2820   0.01618   0.01054  -0.0520   0.8913   0.0221
  -4.750  -0.2578   0.01490   0.00905  -0.0509   0.8856   0.0220
  -4.500  -0.2322   0.01392   0.00795  -0.0503   0.8787   0.0224
  -4.250  -0.2070   0.01321   0.00711  -0.0495   0.8729   0.0232
  -4.000  -0.1815   0.01241   0.00621  -0.0489   0.8663   0.0235
  -3.750  -0.1562   0.01172   0.00542  -0.0481   0.8600   0.0239
  -3.500  -0.1305   0.01117   0.00480  -0.0475   0.8538   0.0244
  -3.250  -0.1045   0.01074   0.00429  -0.0470   0.8470   0.0249
  -3.000  -0.0791   0.01015   0.00359  -0.0463   0.8409   0.0262
  -2.750  -0.0525   0.00978   0.00317  -0.0458   0.8337   0.0284
  -2.500  -0.0258   0.00953   0.00287  -0.0454   0.8276   0.0319
  -2.250   0.0012   0.00922   0.00257  -0.0450   0.8200   0.0430
  -2.000   0.0257   0.00853   0.00230  -0.0445   0.8136   0.1595
  -1.750   0.0513   0.00803   0.00217  -0.0442   0.8055   0.2633
  -1.500   0.0766   0.00763   0.00205  -0.0437   0.7982   0.3622
  -1.250   0.1010   0.00712   0.00196  -0.0431   0.7893   0.4934
  -1.000   0.1237   0.00659   0.00192  -0.0420   0.7807   0.6401
  -0.750   0.1445   0.00610   0.00189  -0.0402   0.7719   0.7834
  -0.500   0.1936   0.00576   0.00193  -0.0438   0.7622   0.9531
  -0.250   0.2404   0.00580   0.00188  -0.0476   0.7521   0.9818
   0.000   0.2862   0.00582   0.00179  -0.0513   0.7418   0.9947
   0.250   0.3248   0.00582   0.00170  -0.0536   0.7299   1.0000
   0.500   0.3499   0.00584   0.00165  -0.0530   0.7178   1.0000
   0.750   0.3751   0.00587   0.00161  -0.0524   0.7054   1.0000
   1.000   0.4004   0.00591   0.00158  -0.0518   0.6921   1.0000
   1.250   0.4258   0.00597   0.00157  -0.0512   0.6781   1.0000
   1.500   0.4513   0.00604   0.00156  -0.0507   0.6633   1.0000
   1.750   0.4768   0.00613   0.00157  -0.0501   0.6473   1.0000
   2.000   0.5022   0.00623   0.00160  -0.0495   0.6306   1.0000
   2.250   0.5276   0.00635   0.00163  -0.0490   0.6132   1.0000
   2.500   0.5531   0.00647   0.00168  -0.0484   0.5942   1.0000
   2.750   0.5784   0.00662   0.00175  -0.0479   0.5739   1.0000
   3.000   0.6037   0.00677   0.00183  -0.0474   0.5531   1.0000
   3.250   0.6289   0.00695   0.00192  -0.0468   0.5307   1.0000
   3.500   0.6539   0.00715   0.00203  -0.0463   0.5068   1.0000
   3.750   0.6787   0.00737   0.00217  -0.0457   0.4822   1.0000
   4.000   0.7033   0.00762   0.00231  -0.0451   0.4558   1.0000
   4.250   0.7278   0.00788   0.00247  -0.0445   0.4284   1.0000
   4.500   0.7520   0.00817   0.00265  -0.0439   0.3999   1.0000
   4.750   0.7762   0.00848   0.00287  -0.0433   0.3719   1.0000
   5.000   0.8002   0.00881   0.00308  -0.0426   0.3444   1.0000
   5.250   0.8242   0.00914   0.00332  -0.0420   0.3189   1.0000
   5.500   0.8482   0.00948   0.00357  -0.0414   0.2967   1.0000
   5.750   0.8722   0.00982   0.00385  -0.0409   0.2750   1.0000
   6.000   0.8960   0.01018   0.00413  -0.0402   0.2563   1.0000
   6.250   0.9200   0.01050   0.00442  -0.0397   0.2385   1.0000
   6.500   0.9439   0.01085   0.00472  -0.0391   0.2209   1.0000
   6.750   0.9674   0.01123   0.00505  -0.0385   0.2033   1.0000
   7.000   0.9906   0.01163   0.00538  -0.0378   0.1851   1.0000
   7.250   1.0137   0.01202   0.00572  -0.0372   0.1657   1.0000
   7.500   1.0363   0.01247   0.00609  -0.0365   0.1477   1.0000
   7.750   1.0587   0.01293   0.00649  -0.0358   0.1314   1.0000
   8.000   1.0811   0.01338   0.00691  -0.0351   0.1160   1.0000
   8.250   1.1029   0.01387   0.00735  -0.0343   0.1005   1.0000
   8.500   1.1243   0.01439   0.00782  -0.0335   0.0865   1.0000
   8.750   1.1449   0.01496   0.00834  -0.0326   0.0718   1.0000
   9.000   1.1640   0.01566   0.00894  -0.0315   0.0546   1.0000
   9.250   1.1775   0.01687   0.00993  -0.0297   0.0249   1.0000
   9.500   1.1906   0.01808   0.01106  -0.0277   0.0134   1.0000
   9.750   1.2075   0.01887   0.01192  -0.0262   0.0114   1.0000
  10.000   1.2215   0.01985   0.01298  -0.0244   0.0101   1.0000
  10.250   1.2347   0.02081   0.01405  -0.0225   0.0095   1.0000
  10.500   1.2460   0.02170   0.01505  -0.0202   0.0091   1.0000
  10.750   1.2545   0.02262   0.01607  -0.0176   0.0088   1.0000
  11.000   1.2606   0.02374   0.01730  -0.0150   0.0086   1.0000
  11.250   1.2668   0.02491   0.01857  -0.0126   0.0083   1.0000
  11.500   1.2714   0.02628   0.02005  -0.0104   0.0079   1.0000
  11.750   1.2752   0.02778   0.02166  -0.0084   0.0078   1.0000
  12.000   1.2774   0.02949   0.02349  -0.0065   0.0077   1.0000
  12.250   1.2761   0.03161   0.02571  -0.0048   0.0074   1.0000
  12.500   1.2755   0.03380   0.02801  -0.0034   0.0073   1.0000
  12.750   1.2675   0.03685   0.03119  -0.0020   0.0070   1.0000
  13.000   1.2708   0.03893   0.03339  -0.0014   0.0071   1.0000
  13.250   1.2627   0.04235   0.03694  -0.0007   0.0070   1.0000
  13.500   1.2605   0.04530   0.04001  -0.0005   0.0070   1.0000
  13.750   1.2522   0.04909   0.04395  -0.0004   0.0069   1.0000
  14.000   1.2428   0.05324   0.04826  -0.0006   0.0068   1.0000
  14.250   1.2330   0.05761   0.05280  -0.0010   0.0068   1.0000
  14.500   1.2313   0.06105   0.05636  -0.0020   0.0068   1.0000
  14.750   1.2251   0.06529   0.06074  -0.0032   0.0068   1.0000
  15.000   1.2116   0.07081   0.06644  -0.0048   0.0068   1.0000
  15.250   1.2132   0.07424   0.06997  -0.0066   0.0068   1.0000
  15.500   1.2009   0.08000   0.07589  -0.0089   0.0068   1.0000
  15.750   1.1903   0.08576   0.08181  -0.0115   0.0068   1.0000
  16.000   1.1837   0.09105   0.08723  -0.0143   0.0069   1.0000
  16.250   1.1739   0.09709   0.09340  -0.0175   0.0069   1.0000
  16.500   1.1621   0.10373   0.10019  -0.0211   0.0069   1.0000
  16.750   1.1544   0.10980   0.10638  -0.0246   0.0070   1.0000
  17.000   1.1414   0.11711   0.11384  -0.0288   0.0070   1.0000
  17.250   1.1309   0.12415   0.12103  -0.0330   0.0070   1.0000
  17.500   1.1201   0.13149   0.12850  -0.0374   0.0071   1.0000
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