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SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD8040 (10%) (sd8040-il)
Reynolds number: 200,000
Max Cl/Cd: 65.94 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd8040-il-200000-n5.txt
Download as CSV file: xf-sd8040-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8040 (10%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4516   0.07178   0.06820  -0.0410   1.0000   0.0170
  -8.500  -0.4635   0.06714   0.06364  -0.0433   1.0000   0.0168
  -8.250  -0.4821   0.06148   0.05803  -0.0471   1.0000   0.0167
  -8.000  -0.5010   0.05541   0.05189  -0.0491   1.0000   0.0165
  -7.750  -0.5196   0.05019   0.04653  -0.0486   1.0000   0.0163
  -7.500  -0.5147   0.04004   0.03575  -0.0555   0.9921   0.0160
  -7.250  -0.4966   0.03297   0.02792  -0.0596   0.9855   0.0160
  -7.000  -0.4737   0.02853   0.02283  -0.0615   0.9798   0.0161
  -6.750  -0.4459   0.02529   0.01898  -0.0630   0.9753   0.0165
  -6.500  -0.4138   0.02293   0.01613  -0.0647   0.9725   0.0168
  -6.250  -0.3864   0.02131   0.01423  -0.0651   0.9668   0.0172
  -6.000  -0.3543   0.02037   0.01322  -0.0664   0.9629   0.0181
  -5.750  -0.3206   0.01939   0.01209  -0.0679   0.9597   0.0193
  -5.500  -0.2927   0.01838   0.01087  -0.0680   0.9535   0.0203
  -5.250  -0.2620   0.01734   0.00972  -0.0686   0.9486   0.0210
  -5.000  -0.2292   0.01650   0.00886  -0.0698   0.9448   0.0221
  -4.750  -0.2034   0.01584   0.00814  -0.0694   0.9371   0.0231
  -4.500  -0.1727   0.01517   0.00737  -0.0699   0.9317   0.0248
  -4.250  -0.1452   0.01461   0.00681  -0.0698   0.9247   0.0271
  -4.000  -0.1169   0.01411   0.00626  -0.0698   0.9176   0.0309
  -3.750  -0.0885   0.01363   0.00574  -0.0698   0.9108   0.0356
  -3.500  -0.0618   0.01316   0.00527  -0.0694   0.9023   0.0433
  -3.250  -0.0341   0.01271   0.00487  -0.0692   0.8947   0.0579
  -3.000  -0.0078   0.01229   0.00455  -0.0689   0.8855   0.0830
  -2.750   0.0187   0.01185   0.00427  -0.0685   0.8764   0.1228
  -2.500   0.0454   0.01144   0.00401  -0.0682   0.8672   0.1731
  -2.250   0.0711   0.01102   0.00382  -0.0678   0.8565   0.2365
  -2.000   0.0971   0.01058   0.00363  -0.0674   0.8465   0.3170
  -1.750   0.1225   0.01015   0.00349  -0.0668   0.8352   0.4090
  -1.500   0.1471   0.00975   0.00340  -0.0660   0.8230   0.5055
  -1.250   0.1716   0.00941   0.00333  -0.0649   0.8105   0.5958
  -1.000   0.1957   0.00915   0.00327  -0.0636   0.7975   0.6750
  -0.750   0.2197   0.00896   0.00322  -0.0622   0.7839   0.7418
  -0.500   0.2435   0.00884   0.00317  -0.0606   0.7692   0.7992
  -0.250   0.2681   0.00875   0.00311  -0.0592   0.7539   0.8514
   0.000   0.2970   0.00870   0.00304  -0.0587   0.7377   0.9007
   0.250   0.3332   0.00869   0.00295  -0.0599   0.7201   0.9446
   0.500   0.3748   0.00870   0.00284  -0.0625   0.7008   0.9798
   0.750   0.4113   0.00875   0.00275  -0.0642   0.6808   1.0000
   1.000   0.4354   0.00887   0.00272  -0.0633   0.6611   1.0000
   1.250   0.4599   0.00901   0.00272  -0.0625   0.6411   1.0000
   1.500   0.4846   0.00915   0.00273  -0.0618   0.6201   1.0000
   1.750   0.5095   0.00932   0.00277  -0.0611   0.5989   1.0000
   2.000   0.5344   0.00951   0.00282  -0.0604   0.5780   1.0000
   2.250   0.5595   0.00969   0.00289  -0.0598   0.5568   1.0000
   2.500   0.5846   0.00990   0.00298  -0.0592   0.5351   1.0000
   2.750   0.6096   0.01012   0.00308  -0.0585   0.5138   1.0000
   3.000   0.6347   0.01034   0.00321  -0.0580   0.4920   1.0000
   3.250   0.6597   0.01059   0.00334  -0.0574   0.4702   1.0000
   3.500   0.6845   0.01085   0.00351  -0.0568   0.4489   1.0000
   3.750   0.7095   0.01112   0.00368  -0.0562   0.4272   1.0000
   4.000   0.7342   0.01140   0.00387  -0.0556   0.4062   1.0000
   4.250   0.7589   0.01170   0.00407  -0.0551   0.3859   1.0000
   4.500   0.7836   0.01200   0.00431  -0.0545   0.3651   1.0000
   4.750   0.8081   0.01232   0.00455  -0.0540   0.3454   1.0000
   5.000   0.8323   0.01267   0.00482  -0.0534   0.3259   1.0000
   5.250   0.8567   0.01301   0.00511  -0.0528   0.3074   1.0000
   5.500   0.8809   0.01336   0.00541  -0.0522   0.2887   1.0000
   5.750   0.9049   0.01373   0.00572  -0.0517   0.2709   1.0000
   6.000   0.9286   0.01413   0.00608  -0.0510   0.2533   1.0000
   6.250   0.9522   0.01453   0.00644  -0.0504   0.2369   1.0000
   6.500   0.9755   0.01496   0.00682  -0.0498   0.2206   1.0000
   6.750   0.9986   0.01541   0.00722  -0.0491   0.2051   1.0000
   7.000   1.0213   0.01587   0.00766  -0.0484   0.1900   1.0000
   7.250   1.0439   0.01635   0.00812  -0.0477   0.1759   1.0000
   7.500   1.0661   0.01685   0.00859  -0.0469   0.1620   1.0000
   7.750   1.0880   0.01737   0.00911  -0.0461   0.1490   1.0000
   8.000   1.1095   0.01791   0.00964  -0.0453   0.1369   1.0000
   8.250   1.1306   0.01848   0.01020  -0.0444   0.1258   1.0000
   8.500   1.1509   0.01908   0.01080  -0.0434   0.1158   1.0000
   8.750   1.1709   0.01970   0.01142  -0.0425   0.1062   1.0000
   9.000   1.1909   0.02031   0.01207  -0.0414   0.0975   1.0000
   9.250   1.2096   0.02099   0.01277  -0.0403   0.0898   1.0000
   9.500   1.2275   0.02170   0.01351  -0.0391   0.0823   1.0000
   9.750   1.2451   0.02241   0.01427  -0.0378   0.0758   1.0000
  10.250   1.2760   0.02397   0.01592  -0.0347   0.0645   1.0000
  10.500   1.2872   0.02489   0.01686  -0.0326   0.0600   1.0000
  10.750   1.3001   0.02572   0.01779  -0.0308   0.0559   1.0000
  11.000   1.3105   0.02670   0.01882  -0.0288   0.0523   1.0000
  11.250   1.3196   0.02781   0.01999  -0.0268   0.0495   1.0000
  11.500   1.3295   0.02888   0.02118  -0.0251   0.0465   1.0000
  11.750   1.3370   0.03015   0.02252  -0.0232   0.0441   1.0000
  12.000   1.3423   0.03163   0.02406  -0.0214   0.0422   1.0000
  12.250   1.3495   0.03303   0.02561  -0.0199   0.0402   1.0000
  12.500   1.3552   0.03461   0.02730  -0.0185   0.0385   1.0000
  12.750   1.3586   0.03644   0.02921  -0.0173   0.0370   1.0000
  13.000   1.3589   0.03865   0.03147  -0.0162   0.0358   1.0000
  13.250   1.3629   0.04066   0.03366  -0.0154   0.0345   1.0000
  13.500   1.3651   0.04293   0.03607  -0.0148   0.0332   1.0000
  13.750   1.3658   0.04546   0.03873  -0.0144   0.0322   1.0000
  14.000   1.3652   0.04826   0.04164  -0.0144   0.0313   1.0000
  14.250   1.3623   0.05145   0.04493  -0.0147   0.0305   1.0000
  14.500   1.3573   0.05503   0.04858  -0.0152   0.0299   1.0000
  14.750   1.3556   0.05840   0.05214  -0.0159   0.0291   1.0000
  15.000   1.3521   0.06213   0.05604  -0.0169   0.0283   1.0000
  15.250   1.3473   0.06616   0.06023  -0.0182   0.0277   1.0000
  15.500   1.3419   0.07047   0.06468  -0.0198   0.0270   1.0000
  15.750   1.3354   0.07508   0.06942  -0.0217   0.0264   1.0000
  16.000   1.3283   0.07992   0.07440  -0.0238   0.0260   1.0000
  16.250   1.3205   0.08505   0.07965  -0.0261   0.0256   1.0000
  16.500   1.3125   0.09028   0.08499  -0.0286   0.0252   1.0000
  16.750   1.3043   0.09558   0.09036  -0.0311   0.0248   1.0000
  17.000   1.2950   0.10145   0.09641  -0.0341   0.0244   1.0000
  17.250   1.2847   0.10765   0.10279  -0.0374   0.0241   1.0000
  17.500   1.2736   0.11413   0.10945  -0.0409   0.0237   1.0000
  17.750   1.2620   0.12089   0.11638  -0.0448   0.0234   1.0000
  18.000   1.2495   0.12804   0.12369  -0.0490   0.0230   1.0000
  18.250   1.2367   0.13537   0.13118  -0.0534   0.0227   1.0000
  18.500   1.2227   0.14319   0.13915  -0.0582   0.0225   1.0000
  18.750   1.2070   0.15172   0.14783  -0.0636   0.0222   1.0000
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