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SD7034 (sd7034-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SD7034 (sd7034-il)
Reynolds number: 500,000
Max Cl/Cd: 99.48 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7034-il-500000-n5.txt
Download as CSV file: xf-sd7034-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7034                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6308   0.03579   0.03303  -0.0790   0.9385   0.0081
 -10.000  -0.6361   0.02956   0.02622  -0.0816   0.9169   0.0081
  -9.750  -0.6265   0.02621   0.02241  -0.0819   0.9039   0.0083
  -9.500  -0.6107   0.02393   0.01976  -0.0818   0.8937   0.0084
  -9.250  -0.5923   0.02205   0.01758  -0.0816   0.8843   0.0086
  -9.000  -0.5708   0.02073   0.01608  -0.0814   0.8759   0.0089
  -8.750  -0.5479   0.01974   0.01491  -0.0812   0.8678   0.0091
  -8.500  -0.5236   0.01890   0.01391  -0.0810   0.8601   0.0094
  -8.250  -0.4993   0.01807   0.01291  -0.0807   0.8524   0.0097
  -8.000  -0.4742   0.01723   0.01191  -0.0806   0.8450   0.0101
  -7.750  -0.4492   0.01644   0.01093  -0.0803   0.8376   0.0105
  -7.500  -0.4234   0.01569   0.01000  -0.0801   0.8304   0.0110
  -7.250  -0.3976   0.01500   0.00918  -0.0799   0.8231   0.0115
  -7.000  -0.3710   0.01456   0.00866  -0.0798   0.8162   0.0121
  -6.750  -0.3441   0.01416   0.00817  -0.0797   0.8088   0.0129
  -6.500  -0.3172   0.01370   0.00758  -0.0795   0.8019   0.0137
  -6.250  -0.2903   0.01317   0.00693  -0.0793   0.7945   0.0145
  -6.000  -0.2634   0.01276   0.00644  -0.0792   0.7876   0.0153
  -5.750  -0.2358   0.01239   0.00600  -0.0791   0.7800   0.0164
  -5.500  -0.2085   0.01206   0.00555  -0.0789   0.7728   0.0175
  -5.250  -0.1809   0.01166   0.00510  -0.0789   0.7653   0.0188
  -5.000  -0.1533   0.01141   0.00478  -0.0788   0.7578   0.0204
  -4.750  -0.1253   0.01115   0.00444  -0.0787   0.7502   0.0219
  -4.500  -0.0978   0.01082   0.00406  -0.0786   0.7426   0.0236
  -4.250  -0.0698   0.01059   0.00378  -0.0785   0.7349   0.0256
  -4.000  -0.0419   0.01035   0.00348  -0.0784   0.7273   0.0278
  -3.750  -0.0138   0.01013   0.00323  -0.0784   0.7195   0.0307
  -3.500   0.0142   0.00994   0.00298  -0.0783   0.7117   0.0339
  -3.250   0.0424   0.00975   0.00277  -0.0783   0.7039   0.0385
  -3.000   0.0705   0.00958   0.00259  -0.0782   0.6958   0.0452
  -2.750   0.0987   0.00943   0.00242  -0.0782   0.6876   0.0529
  -2.500   0.1269   0.00933   0.00227  -0.0781   0.6794   0.0603
  -2.250   0.1552   0.00919   0.00214  -0.0781   0.6706   0.0692
  -2.000   0.1833   0.00909   0.00202  -0.0781   0.6621   0.0801
  -1.750   0.2116   0.00898   0.00192  -0.0781   0.6527   0.0928
  -1.500   0.2397   0.00887   0.00183  -0.0781   0.6436   0.1115
  -1.250   0.2677   0.00873   0.00175  -0.0781   0.6340   0.1432
  -1.000   0.2957   0.00858   0.00169  -0.0781   0.6244   0.1809
  -0.750   0.3237   0.00844   0.00163  -0.0781   0.6147   0.2260
  -0.500   0.3515   0.00828   0.00160  -0.0781   0.6045   0.2850
  -0.250   0.3794   0.00814   0.00159  -0.0782   0.5946   0.3440
   0.000   0.4070   0.00800   0.00159  -0.0782   0.5845   0.4125
   0.250   0.4345   0.00783   0.00161  -0.0781   0.5737   0.4911
   0.500   0.4618   0.00769   0.00164  -0.0780   0.5633   0.5679
   0.750   0.4879   0.00747   0.00170  -0.0776   0.5527   0.6748
   1.000   0.5122   0.00724   0.00177  -0.0767   0.5415   0.7858
   1.250   0.5339   0.00701   0.00182  -0.0748   0.5306   0.9069
   1.500   0.5731   0.00703   0.00181  -0.0771   0.5179   1.0000
   1.750   0.6007   0.00716   0.00185  -0.0770   0.5058   1.0000
   2.000   0.6282   0.00731   0.00191  -0.0769   0.4937   1.0000
   2.250   0.6558   0.00744   0.00198  -0.0768   0.4813   1.0000
   2.500   0.6832   0.00758   0.00205  -0.0767   0.4689   1.0000
   2.750   0.7106   0.00774   0.00214  -0.0766   0.4566   1.0000
   3.000   0.7379   0.00791   0.00224  -0.0765   0.4441   1.0000
   3.250   0.7650   0.00809   0.00235  -0.0764   0.4311   1.0000
   3.500   0.7920   0.00827   0.00247  -0.0763   0.4181   1.0000
   3.750   0.8191   0.00846   0.00260  -0.0761   0.4048   1.0000
   4.000   0.8459   0.00865   0.00274  -0.0760   0.3914   1.0000
   4.250   0.8727   0.00886   0.00290  -0.0758   0.3780   1.0000
   4.500   0.8992   0.00909   0.00307  -0.0756   0.3645   1.0000
   4.750   0.9256   0.00932   0.00325  -0.0754   0.3508   1.0000
   5.000   0.9519   0.00957   0.00344  -0.0752   0.3372   1.0000
   5.250   0.9779   0.00983   0.00365  -0.0750   0.3235   1.0000
   5.500   1.0038   0.01010   0.00387  -0.0748   0.3099   1.0000
   6.000   1.0550   0.01067   0.00436  -0.0742   0.2832   1.0000
   6.250   1.0803   0.01097   0.00462  -0.0739   0.2697   1.0000
   6.500   1.1053   0.01129   0.00489  -0.0736   0.2561   1.0000
   6.750   1.1299   0.01164   0.00520  -0.0732   0.2416   1.0000
   7.000   1.1543   0.01200   0.00551  -0.0727   0.2273   1.0000
   7.250   1.1783   0.01238   0.00584  -0.0723   0.2135   1.0000
   7.500   1.2020   0.01277   0.00619  -0.0718   0.1999   1.0000
   7.750   1.2253   0.01318   0.00657  -0.0713   0.1867   1.0000
   8.000   1.2483   0.01361   0.00696  -0.0707   0.1742   1.0000
   8.250   1.2708   0.01406   0.00737  -0.0700   0.1621   1.0000
   8.500   1.2926   0.01454   0.00782  -0.0693   0.1491   1.0000
   8.750   1.3137   0.01506   0.00829  -0.0685   0.1360   1.0000
   9.000   1.3340   0.01561   0.00880  -0.0676   0.1233   1.0000
   9.250   1.3535   0.01620   0.00935  -0.0666   0.1108   1.0000
   9.500   1.3720   0.01683   0.00994  -0.0654   0.0991   1.0000
   9.750   1.3897   0.01746   0.01054  -0.0642   0.0883   1.0000
  10.000   1.4064   0.01811   0.01117  -0.0628   0.0785   1.0000
  10.250   1.4209   0.01879   0.01184  -0.0611   0.0700   1.0000
  10.500   1.4325   0.01952   0.01256  -0.0589   0.0628   1.0000
  10.750   1.4433   0.02030   0.01334  -0.0567   0.0562   1.0000
  11.000   1.4545   0.02109   0.01416  -0.0548   0.0514   1.0000
  11.250   1.4645   0.02201   0.01509  -0.0529   0.0468   1.0000
  11.500   1.4751   0.02293   0.01605  -0.0511   0.0434   1.0000
  11.750   1.4851   0.02394   0.01710  -0.0495   0.0401   1.0000
  12.000   1.4932   0.02514   0.01833  -0.0478   0.0369   1.0000
  12.250   1.5032   0.02624   0.01951  -0.0465   0.0347   1.0000
  12.500   1.5107   0.02758   0.02090  -0.0451   0.0320   1.0000
  12.750   1.5173   0.02906   0.02242  -0.0437   0.0300   1.0000
  13.000   1.5254   0.03047   0.02392  -0.0426   0.0284   1.0000
  13.250   1.5317   0.03210   0.02562  -0.0416   0.0266   1.0000
  13.500   1.5358   0.03399   0.02756  -0.0406   0.0250   1.0000
  13.750   1.5405   0.03590   0.02956  -0.0398   0.0236   1.0000
  14.000   1.5453   0.03787   0.03163  -0.0391   0.0225   1.0000
  14.250   1.5483   0.04009   0.03392  -0.0386   0.0214   1.0000
  14.500   1.5489   0.04264   0.03654  -0.0382   0.0202   1.0000
  14.750   1.5490   0.04534   0.03933  -0.0379   0.0193   1.0000
  15.000   1.5501   0.04802   0.04212  -0.0379   0.0186   1.0000
  15.250   1.5502   0.05092   0.04513  -0.0380   0.0178   1.0000
  15.500   1.5483   0.05417   0.04847  -0.0383   0.0169   1.0000
  15.750   1.5453   0.05771   0.05211  -0.0389   0.0163   1.0000
  16.000   1.5400   0.06170   0.05619  -0.0397   0.0157   1.0000
  16.250   1.5359   0.06563   0.06024  -0.0407   0.0152   1.0000
  16.500   1.5324   0.06961   0.06435  -0.0418   0.0147   1.0000
  16.750   1.5270   0.07399   0.06885  -0.0431   0.0142   1.0000
  17.000   1.5204   0.07864   0.07361  -0.0447   0.0138   1.0000
  17.250   1.5131   0.08354   0.07862  -0.0465   0.0132   1.0000
  17.500   1.5039   0.08889   0.08409  -0.0486   0.0129   1.0000
  17.750   1.4937   0.09455   0.08985  -0.0509   0.0126   1.0000
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