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S3010-103-84 (s3010-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S3010-103-84 (s3010-il)
Reynolds number: 200,000
Max Cl/Cd: 70.04 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3010-il-200000.txt
Download as CSV file: xf-s3010-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3010-103-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4013   0.08842   0.08504  -0.0215   1.0000   0.0559
  -8.250  -0.4014   0.08462   0.08129  -0.0242   1.0000   0.0580
  -8.000  -0.4157   0.07953   0.07631  -0.0316   1.0000   0.0603
  -7.750  -0.4361   0.07152   0.06819  -0.0460   1.0000   0.0610
  -7.500  -0.4347   0.06562   0.06236  -0.0469   1.0000   0.0620
  -7.250  -0.4211   0.06404   0.06090  -0.0439   1.0000   0.0631
  -7.000  -0.4140   0.06187   0.05877  -0.0430   1.0000   0.0644
  -6.750  -0.4159   0.05934   0.05625  -0.0423   1.0000   0.0657
  -6.500  -0.4280   0.05721   0.05412  -0.0400   1.0000   0.0666
  -6.250  -0.4153   0.04874   0.04502  -0.0504   0.9923   0.0747
  -6.000  -0.3827   0.04550   0.04188  -0.0532   0.9868   0.0769
  -5.750  -0.3519   0.02903   0.02354  -0.0595   0.9773   0.0395
  -5.500  -0.3128   0.02556   0.01956  -0.0627   0.9725   0.0393
  -5.250  -0.2769   0.02249   0.01606  -0.0647   0.9655   0.0380
  -5.000  -0.2378   0.02010   0.01326  -0.0669   0.9598   0.0374
  -4.750  -0.2026   0.01847   0.01137  -0.0680   0.9515   0.0379
  -4.500  -0.1661   0.01715   0.00989  -0.0693   0.9442   0.0391
  -4.250  -0.1363   0.01625   0.00887  -0.0692   0.9332   0.0404
  -4.000  -0.1091   0.01516   0.00782  -0.0690   0.9223   0.0443
  -3.750  -0.0821   0.01455   0.00715  -0.0683   0.9118   0.0488
  -3.500  -0.0581   0.01373   0.00634  -0.0672   0.8997   0.0553
  -3.250  -0.0343   0.01284   0.00555  -0.0660   0.8874   0.0867
  -3.000  -0.0111   0.01195   0.00513  -0.0652   0.8757   0.1843
  -2.750   0.0130   0.01148   0.00490  -0.0643   0.8647   0.2608
  -2.500   0.0365   0.01096   0.00476  -0.0633   0.8530   0.3662
  -2.250   0.0599   0.01051   0.00467  -0.0623   0.8407   0.4741
  -2.000   0.0834   0.01016   0.00459  -0.0610   0.8289   0.5658
  -1.750   0.1062   0.00985   0.00452  -0.0593   0.8178   0.6534
  -1.500   0.1281   0.00959   0.00446  -0.0572   0.8061   0.7381
  -1.250   0.1489   0.00939   0.00443  -0.0548   0.7937   0.8159
  -1.000   0.1721   0.00925   0.00434  -0.0526   0.7817   0.8877
  -0.750   0.2117   0.00913   0.00414  -0.0541   0.7700   0.9532
  -0.500   0.2656   0.00902   0.00384  -0.0590   0.7576   0.9994
  -0.250   0.2892   0.00907   0.00373  -0.0582   0.7438   1.0000
   0.000   0.3137   0.00913   0.00365  -0.0574   0.7300   1.0000
   0.250   0.3389   0.00920   0.00358  -0.0568   0.7163   1.0000
   0.500   0.3646   0.00928   0.00353  -0.0562   0.7026   1.0000
   0.750   0.3907   0.00937   0.00349  -0.0557   0.6890   1.0000
   1.000   0.4170   0.00947   0.00347  -0.0552   0.6753   1.0000
   1.250   0.4434   0.00958   0.00346  -0.0547   0.6615   1.0000
   1.500   0.4700   0.00970   0.00346  -0.0543   0.6475   1.0000
   1.750   0.4967   0.00982   0.00347  -0.0539   0.6333   1.0000
   2.000   0.5234   0.00996   0.00350  -0.0535   0.6189   1.0000
   2.250   0.5502   0.01010   0.00356  -0.0531   0.6041   1.0000
   2.500   0.5770   0.01025   0.00363  -0.0528   0.5894   1.0000
   2.750   0.6037   0.01040   0.00372  -0.0525   0.5746   1.0000
   3.000   0.6305   0.01057   0.00382  -0.0522   0.5597   1.0000
   3.250   0.6572   0.01075   0.00395  -0.0518   0.5449   1.0000
   3.500   0.6839   0.01094   0.00407  -0.0515   0.5298   1.0000
   3.750   0.7105   0.01114   0.00421  -0.0512   0.5147   1.0000
   4.000   0.7369   0.01135   0.00438  -0.0509   0.4993   1.0000
   4.250   0.7633   0.01158   0.00455  -0.0505   0.4838   1.0000
   4.500   0.7896   0.01181   0.00473  -0.0502   0.4682   1.0000
   4.750   0.8157   0.01206   0.00493  -0.0499   0.4524   1.0000
   5.000   0.8416   0.01232   0.00516  -0.0495   0.4365   1.0000
   5.250   0.8674   0.01260   0.00539  -0.0491   0.4203   1.0000
   5.500   0.8930   0.01289   0.00565  -0.0488   0.4037   1.0000
   5.750   0.9185   0.01318   0.00595  -0.0484   0.3866   1.0000
   6.000   0.9437   0.01349   0.00625  -0.0480   0.3692   1.0000
   6.250   0.9687   0.01383   0.00657  -0.0475   0.3519   1.0000
   6.500   0.9933   0.01420   0.00692  -0.0471   0.3345   1.0000
   6.750   1.0176   0.01460   0.00728  -0.0466   0.3173   1.0000
   7.000   1.0414   0.01505   0.00767  -0.0461   0.3001   1.0000
   7.250   1.0651   0.01550   0.00811  -0.0455   0.2829   1.0000
   7.500   1.0884   0.01597   0.00860  -0.0450   0.2656   1.0000
   7.750   1.1113   0.01649   0.00910  -0.0443   0.2488   1.0000
   8.000   1.1336   0.01704   0.00964  -0.0437   0.2325   1.0000
   8.250   1.1554   0.01763   0.01023  -0.0430   0.2168   1.0000
   8.500   1.1766   0.01826   0.01084  -0.0422   0.2017   1.0000
   8.750   1.1973   0.01893   0.01151  -0.0414   0.1874   1.0000
   9.000   1.2173   0.01964   0.01222  -0.0405   0.1738   1.0000
   9.250   1.2365   0.02040   0.01300  -0.0395   0.1612   1.0000
   9.500   1.2547   0.02123   0.01382  -0.0385   0.1494   1.0000
   9.750   1.2716   0.02213   0.01471  -0.0373   0.1387   1.0000
  10.000   1.2878   0.02304   0.01562  -0.0360   0.1287   1.0000
  10.250   1.3039   0.02392   0.01660  -0.0347   0.1193   1.0000
  10.500   1.3170   0.02504   0.01772  -0.0331   0.1112   1.0000
  10.750   1.3292   0.02602   0.01875  -0.0315   0.1038   1.0000
  11.000   1.3386   0.02714   0.01994  -0.0294   0.0970   1.0000
  11.250   1.3458   0.02823   0.02104  -0.0274   0.0907   1.0000
  11.500   1.3534   0.02942   0.02234  -0.0256   0.0845   1.0000
  11.750   1.3592   0.03070   0.02365  -0.0239   0.0790   1.0000
  12.000   1.3649   0.03222   0.02528  -0.0225   0.0739   1.0000
  12.250   1.3709   0.03373   0.02690  -0.0213   0.0694   1.0000
  12.500   1.3723   0.03585   0.02897  -0.0201   0.0655   1.0000
  12.750   1.3779   0.03758   0.03093  -0.0193   0.0614   1.0000
  13.000   1.3800   0.03968   0.03310  -0.0188   0.0577   1.0000
  13.250   1.3793   0.04230   0.03576  -0.0182   0.0543   1.0000
  13.500   1.3805   0.04477   0.03843  -0.0181   0.0505   1.0000
  13.750   1.3779   0.04774   0.04144  -0.0183   0.0473   1.0000
  14.000   1.3740   0.05108   0.04489  -0.0184   0.0443   1.0000
  14.250   1.3705   0.05453   0.04849  -0.0191   0.0410   1.0000
  14.500   1.3647   0.05831   0.05232  -0.0200   0.0386   1.0000
  14.750   1.3576   0.06244   0.05657  -0.0207   0.0362   1.0000
  15.000   1.3519   0.06657   0.06087  -0.0220   0.0341   1.0000
  15.250   1.3460   0.07085   0.06523  -0.0236   0.0324   1.0000
  15.500   1.3407   0.07499   0.06937  -0.0248   0.0309   1.0000
  15.750   1.3348   0.07950   0.07403  -0.0261   0.0297   1.0000
  16.000   1.3262   0.08477   0.07951  -0.0285   0.0286   1.0000
  16.250   1.3190   0.08989   0.08479  -0.0309   0.0275   1.0000
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