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SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD7084 (9.6%) (sd7084-il)
Reynolds number: 200,000
Max Cl/Cd: 63.8 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7084-il-200000-n5.txt
Download as CSV file: xf-sd7084-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7084 (9.6%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4426   0.11641   0.11269  -0.0188   1.0000   0.0205
 -10.750  -0.4408   0.11213   0.10844  -0.0203   1.0000   0.0194
 -10.500  -0.4415   0.10729   0.10362  -0.0223   1.0000   0.0181
  -9.750  -0.4529   0.08998   0.08642  -0.0304   1.0000   0.0159
  -9.500  -0.4586   0.08432   0.08083  -0.0333   1.0000   0.0161
  -9.250  -0.4642   0.07924   0.07580  -0.0359   1.0000   0.0161
  -8.750  -0.4805   0.06860   0.06526  -0.0422   1.0000   0.0159
  -8.500  -0.4990   0.06282   0.05953  -0.0461   1.0000   0.0157
  -8.250  -0.5202   0.05611   0.05272  -0.0476   1.0000   0.0158
  -8.000  -0.5388   0.05131   0.04776  -0.0463   1.0000   0.0159
  -7.750  -0.5543   0.04702   0.04323  -0.0439   1.0000   0.0160
  -7.500  -0.5618   0.04185   0.03773  -0.0430   0.9983   0.0163
  -7.250  -0.5419   0.03807   0.03365  -0.0456   0.9936   0.0170
  -7.000  -0.5222   0.03387   0.02899  -0.0472   0.9882   0.0174
  -6.750  -0.4976   0.03029   0.02493  -0.0487   0.9842   0.0178
  -6.500  -0.4725   0.02760   0.02182  -0.0495   0.9799   0.0184
  -6.250  -0.4461   0.02523   0.01904  -0.0500   0.9755   0.0190
  -6.000  -0.4154   0.02348   0.01692  -0.0512   0.9722   0.0202
  -5.750  -0.3828   0.02198   0.01509  -0.0525   0.9696   0.0216
  -5.500  -0.3560   0.02050   0.01331  -0.0524   0.9643   0.0220
  -5.250  -0.3240   0.01918   0.01176  -0.0533   0.9607   0.0225
  -5.000  -0.2910   0.01783   0.01025  -0.0545   0.9578   0.0231
  -4.750  -0.2634   0.01665   0.00899  -0.0546   0.9528   0.0242
  -4.500  -0.2343   0.01586   0.00813  -0.0550   0.9477   0.0254
  -4.250  -0.2017   0.01528   0.00749  -0.0560   0.9439   0.0276
  -4.000  -0.1746   0.01477   0.00692  -0.0558   0.9374   0.0299
  -3.750  -0.1450   0.01422   0.00627  -0.0561   0.9317   0.0315
  -3.500  -0.1171   0.01361   0.00561  -0.0560   0.9256   0.0347
  -3.250  -0.0898   0.01318   0.00512  -0.0558   0.9184   0.0408
  -3.000  -0.0619   0.01271   0.00468  -0.0557   0.9120   0.0572
  -2.750  -0.0362   0.01224   0.00435  -0.0552   0.9039   0.0937
  -2.500  -0.0110   0.01168   0.00408  -0.0548   0.8959   0.1648
  -2.250   0.0127   0.01090   0.00385  -0.0542   0.8877   0.3007
  -2.000   0.0343   0.01027   0.00371  -0.0530   0.8775   0.4349
  -1.750   0.0577   0.00981   0.00357  -0.0519   0.8678   0.5345
  -1.500   0.0809   0.00937   0.00346  -0.0505   0.8582   0.6352
  -1.250   0.1028   0.00901   0.00340  -0.0487   0.8462   0.7330
  -1.000   0.1282   0.00876   0.00335  -0.0473   0.8339   0.8147
  -0.750   0.1631   0.00862   0.00327  -0.0480   0.8211   0.8802
  -0.500   0.2064   0.00856   0.00313  -0.0507   0.8066   0.9243
  -0.250   0.2493   0.00852   0.00298  -0.0534   0.7897   0.9537
   0.000   0.2905   0.00851   0.00284  -0.0559   0.7703   0.9737
   0.250   0.3302   0.00851   0.00269  -0.0582   0.7483   0.9892
   0.500   0.3685   0.00854   0.00256  -0.0604   0.7245   1.0000
   0.750   0.3913   0.00862   0.00248  -0.0592   0.7013   1.0000
   1.000   0.4142   0.00872   0.00244  -0.0581   0.6772   1.0000
   1.250   0.4372   0.00886   0.00243  -0.0571   0.6529   1.0000
   1.500   0.4602   0.00901   0.00244  -0.0560   0.6290   1.0000
   1.750   0.4832   0.00919   0.00247  -0.0550   0.6046   1.0000
   2.000   0.5064   0.00937   0.00253  -0.0540   0.5806   1.0000
   2.250   0.5295   0.00957   0.00260  -0.0531   0.5569   1.0000
   2.500   0.5526   0.00978   0.00270  -0.0521   0.5338   1.0000
   2.750   0.5758   0.01000   0.00282  -0.0512   0.5105   1.0000
   3.000   0.5989   0.01024   0.00295  -0.0502   0.4881   1.0000
   3.250   0.6221   0.01048   0.00310  -0.0493   0.4658   1.0000
   3.500   0.6453   0.01073   0.00326  -0.0485   0.4445   1.0000
   3.750   0.6686   0.01100   0.00346  -0.0476   0.4233   1.0000
   4.000   0.6918   0.01127   0.00366  -0.0468   0.4032   1.0000
   4.250   0.7153   0.01155   0.00388  -0.0460   0.3835   1.0000
   4.500   0.7385   0.01185   0.00411  -0.0451   0.3647   1.0000
   4.750   0.7619   0.01215   0.00438  -0.0444   0.3473   1.0000
   5.000   0.7853   0.01245   0.00465  -0.0436   0.3303   1.0000
   5.250   0.8087   0.01276   0.00494  -0.0429   0.3143   1.0000
   5.500   0.8320   0.01309   0.00524  -0.0421   0.2989   1.0000
   5.750   0.8553   0.01342   0.00557  -0.0414   0.2844   1.0000
   6.000   0.8784   0.01377   0.00594  -0.0406   0.2703   1.0000
   6.250   0.9015   0.01413   0.00630  -0.0398   0.2568   1.0000
   6.500   0.9243   0.01450   0.00669  -0.0391   0.2431   1.0000
   6.750   0.9470   0.01489   0.00709  -0.0383   0.2296   1.0000
   7.000   0.9695   0.01529   0.00751  -0.0375   0.2159   1.0000
   7.250   0.9917   0.01570   0.00794  -0.0366   0.2017   1.0000
   7.500   1.0135   0.01615   0.00844  -0.0357   0.1864   1.0000
   7.750   1.0347   0.01664   0.00892  -0.0348   0.1698   1.0000
   8.000   1.0550   0.01720   0.00944  -0.0338   0.1465   1.0000
   8.250   1.0727   0.01800   0.01004  -0.0326   0.1144   1.0000
   8.500   1.0895   0.01889   0.01076  -0.0312   0.0830   1.0000
   8.750   1.1062   0.01978   0.01157  -0.0298   0.0621   1.0000
   9.000   1.1206   0.02087   0.01258  -0.0281   0.0406   1.0000
   9.250   1.1335   0.02205   0.01370  -0.0262   0.0252   1.0000
   9.500   1.1451   0.02328   0.01493  -0.0241   0.0172   1.0000
   9.750   1.1574   0.02436   0.01611  -0.0221   0.0140   1.0000
  10.000   1.1674   0.02545   0.01731  -0.0197   0.0124   1.0000
  10.250   1.1720   0.02679   0.01876  -0.0167   0.0112   1.0000
  10.500   1.1791   0.02795   0.02008  -0.0142   0.0107   1.0000
  10.750   1.1841   0.02929   0.02158  -0.0117   0.0102   1.0000
  11.000   1.1879   0.03076   0.02320  -0.0093   0.0098   1.0000
  11.250   1.1900   0.03242   0.02505  -0.0071   0.0093   1.0000
  11.500   1.1913   0.03424   0.02701  -0.0051   0.0091   1.0000
  11.750   1.1916   0.03624   0.02915  -0.0034   0.0089   1.0000
  12.000   1.1908   0.03849   0.03153  -0.0021   0.0086   1.0000
  12.250   1.1887   0.04100   0.03418  -0.0011   0.0084   1.0000
  12.500   1.1863   0.04374   0.03706  -0.0005   0.0083   1.0000
  12.750   1.1814   0.04692   0.04036  -0.0004   0.0080   1.0000
  13.000   1.1765   0.05033   0.04390  -0.0005   0.0079   1.0000
  13.250   1.1679   0.05441   0.04811  -0.0012   0.0076   1.0000
  13.500   1.1615   0.05840   0.05223  -0.0020   0.0075   1.0000
  13.750   1.1582   0.06221   0.05621  -0.0032   0.0074   1.0000
  14.000   1.1539   0.06634   0.06053  -0.0047   0.0072   1.0000
  14.250   1.1474   0.07095   0.06532  -0.0066   0.0070   1.0000
  14.500   1.1399   0.07582   0.07034  -0.0085   0.0070   1.0000
  14.750   1.1317   0.08107   0.07577  -0.0110   0.0069   1.0000
  15.000   1.1231   0.08654   0.08139  -0.0136   0.0068   1.0000
  15.250   1.1141   0.09225   0.08726  -0.0164   0.0068   1.0000
  15.500   1.1037   0.09843   0.09361  -0.0196   0.0067   1.0000
  15.750   1.0928   0.10490   0.10023  -0.0230   0.0067   1.0000
  16.000   1.0814   0.11172   0.10720  -0.0267   0.0067   1.0000
  16.250   1.0697   0.11880   0.11443  -0.0306   0.0067   1.0000
  16.500   1.0570   0.12635   0.12213  -0.0348   0.0067   1.0000
  16.750   1.0448   0.13407   0.12999  -0.0392   0.0067   1.0000
  17.000   1.0318   0.14225   0.13832  -0.0440   0.0068   1.0000
  17.250   1.0171   0.15127   0.14747  -0.0492   0.0068   1.0000
  17.500   1.0029   0.16056   0.15688  -0.0546   0.0069   1.0000
  17.750   0.9852   0.17155   0.16797  -0.0608   0.0070   1.0000
  18.000   0.9645   0.18455   0.18104  -0.0678   0.0072   1.0000
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