Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S9026 (9.5%) (s9026-il)
Reynolds number: 500,000
Max Cl/Cd: 61.46 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9026-il-500000-n5.txt
Download as CSV file: xf-s9026-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9026 (9.5%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.9701   0.13321   0.13057   0.0236   1.0000   0.0087
 -16.750  -1.0062   0.12026   0.11750   0.0162   1.0000   0.0086
 -16.500  -1.0384   0.10885   0.10594   0.0096   1.0000   0.0085
 -16.250  -1.0728   0.09763   0.09458   0.0031   1.0000   0.0084
 -16.000  -1.1078   0.08684   0.08363  -0.0032   1.0000   0.0082
 -15.750  -1.1409   0.07659   0.07321  -0.0093   1.0000   0.0081
 -15.500  -1.1693   0.06734   0.06379  -0.0150   1.0000   0.0080
 -15.250  -1.1916   0.05937   0.05565  -0.0201   1.0000   0.0080
 -15.000  -1.2104   0.05233   0.04843  -0.0247   1.0000   0.0080
 -14.750  -1.2260   0.04634   0.04229  -0.0285   1.0000   0.0081
 -14.500  -1.2363   0.04182   0.03761  -0.0309   1.0000   0.0082
 -14.250  -1.2430   0.03830   0.03396  -0.0321   1.0000   0.0084
 -14.000  -1.2466   0.03558   0.03112  -0.0323   1.0000   0.0085
 -13.750  -1.2476   0.03343   0.02885  -0.0317   1.0000   0.0088
 -13.500  -1.2457   0.03175   0.02706  -0.0305   1.0000   0.0090
 -13.250  -1.2434   0.03027   0.02547  -0.0288   1.0000   0.0093
 -13.000  -1.2399   0.02899   0.02407  -0.0266   1.0000   0.0096
 -12.750  -1.2334   0.02792   0.02288  -0.0243   1.0000   0.0100
 -12.500  -1.2232   0.02685   0.02167  -0.0226   1.0000   0.0104
 -12.250  -1.2082   0.02601   0.02070  -0.0213   1.0000   0.0108
 -12.000  -1.1962   0.02483   0.01942  -0.0197   1.0000   0.0112
 -11.750  -1.1815   0.02381   0.01832  -0.0185   1.0000   0.0118
 -11.500  -1.1633   0.02306   0.01751  -0.0175   1.0000   0.0124
 -11.250  -1.1444   0.02233   0.01670  -0.0165   1.0000   0.0130
 -11.000  -1.1254   0.02157   0.01584  -0.0156   1.0000   0.0136
 -10.750  -1.1055   0.02086   0.01503  -0.0146   1.0000   0.0142
 -10.500  -1.0845   0.02025   0.01430  -0.0138   1.0000   0.0147
 -10.250  -1.0652   0.01940   0.01336  -0.0128   1.0000   0.0154
 -10.000  -1.0452   0.01860   0.01249  -0.0119   1.0000   0.0162
  -9.750  -1.0237   0.01797   0.01181  -0.0111   1.0000   0.0170
  -9.500  -1.0014   0.01741   0.01119  -0.0104   1.0000   0.0179
  -9.250  -0.9788   0.01687   0.01058  -0.0096   1.0000   0.0188
  -9.000  -0.9560   0.01636   0.00998  -0.0089   1.0000   0.0195
  -8.750  -0.9331   0.01583   0.00938  -0.0082   1.0000   0.0202
  -8.500  -0.9112   0.01516   0.00867  -0.0073   1.0000   0.0218
  -8.250  -0.8881   0.01466   0.00814  -0.0066   1.0000   0.0232
  -8.000  -0.8646   0.01420   0.00764  -0.0058   1.0000   0.0246
  -7.750  -0.8409   0.01379   0.00717  -0.0051   1.0000   0.0260
  -7.500  -0.8175   0.01334   0.00667  -0.0044   1.0000   0.0282
  -7.250  -0.7940   0.01292   0.00626  -0.0036   1.0000   0.0313
  -7.000  -0.7701   0.01258   0.00589  -0.0029   1.0000   0.0346
  -6.750  -0.7468   0.01218   0.00551  -0.0020   1.0000   0.0398
  -6.500  -0.7230   0.01188   0.00519  -0.0013   1.0000   0.0442
  -6.250  -0.6996   0.01154   0.00485  -0.0004   1.0000   0.0493
  -6.000  -0.6759   0.01125   0.00456   0.0004   1.0000   0.0545
  -5.750  -0.6524   0.01095   0.00428   0.0013   1.0000   0.0604
  -5.500  -0.6288   0.01068   0.00402   0.0021   1.0000   0.0672
  -5.250  -0.6055   0.01039   0.00376   0.0030   1.0000   0.0762
  -5.000  -0.5823   0.01012   0.00353   0.0039   1.0000   0.0860
  -4.750  -0.5537   0.00985   0.00331   0.0036   0.9982   0.0990
  -4.500  -0.5187   0.00954   0.00310   0.0020   0.9940   0.1185
  -4.250  -0.4852   0.00926   0.00289   0.0007   0.9887   0.1374
  -4.000  -0.4499   0.00900   0.00270  -0.0010   0.9834   0.1551
  -3.750  -0.4176   0.00876   0.00253  -0.0020   0.9751   0.1743
  -3.500  -0.3842   0.00849   0.00236  -0.0032   0.9659   0.1981
  -3.250  -0.3507   0.00826   0.00220  -0.0043   0.9535   0.2216
  -3.000  -0.3179   0.00804   0.00205  -0.0053   0.9384   0.2448
  -2.750  -0.2870   0.00782   0.00191  -0.0059   0.9207   0.2731
  -2.500  -0.2588   0.00759   0.00178  -0.0058   0.8994   0.3090
  -2.250  -0.2325   0.00742   0.00167  -0.0053   0.8749   0.3409
  -2.000  -0.2066   0.00732   0.00156  -0.0046   0.8492   0.3669
  -1.750  -0.1810   0.00722   0.00148  -0.0040   0.8231   0.3958
  -1.250  -0.1293   0.00704   0.00134  -0.0028   0.7729   0.4563
  -1.000  -0.1034   0.00695   0.00128  -0.0023   0.7478   0.4913
  -0.500  -0.0519   0.00683   0.00121  -0.0011   0.6877   0.5621
  -0.250  -0.0260   0.00682   0.00118  -0.0005   0.6543   0.5920
   0.000   0.0000   0.00683   0.00118   0.0000   0.6217   0.6215
   0.250   0.0260   0.00682   0.00118   0.0005   0.5919   0.6541
   0.500   0.0519   0.00683   0.00121   0.0011   0.5623   0.6878
   1.000   0.1034   0.00695   0.00128   0.0023   0.4918   0.7478
   1.250   0.1292   0.00704   0.00134   0.0028   0.4560   0.7727
   1.750   0.1810   0.00722   0.00148   0.0040   0.3957   0.8233
   2.250   0.2324   0.00742   0.00167   0.0053   0.3409   0.8749
   2.500   0.2588   0.00759   0.00178   0.0058   0.3089   0.8994
   2.750   0.2870   0.00781   0.00191   0.0059   0.2738   0.9207
   3.000   0.3179   0.00804   0.00205   0.0053   0.2447   0.9383
   3.250   0.3507   0.00826   0.00220   0.0043   0.2216   0.9533
   3.500   0.3842   0.00850   0.00236   0.0032   0.1978   0.9659
   3.750   0.4176   0.00876   0.00253   0.0020   0.1746   0.9750
   4.000   0.4498   0.00900   0.00270   0.0010   0.1553   0.9833
   4.250   0.4851   0.00926   0.00289  -0.0006   0.1372   0.9886
   4.500   0.5186   0.00954   0.00310  -0.0019   0.1185   0.9940
   4.750   0.5535   0.00985   0.00331  -0.0036   0.0987   0.9981
   5.000   0.5825   0.01012   0.00353  -0.0040   0.0860   1.0000
   5.250   0.6058   0.01039   0.00376  -0.0030   0.0762   1.0000
   5.500   0.6290   0.01068   0.00402  -0.0022   0.0672   1.0000
   5.750   0.6526   0.01095   0.00428  -0.0013   0.0603   1.0000
   6.000   0.6761   0.01125   0.00456  -0.0005   0.0545   1.0000
   6.250   0.6998   0.01154   0.00485   0.0004   0.0493   1.0000
   6.500   0.7232   0.01188   0.00519   0.0012   0.0441   1.0000
   6.750   0.7470   0.01218   0.00551   0.0020   0.0397   1.0000
   7.000   0.7702   0.01258   0.00589   0.0028   0.0345   1.0000
   7.250   0.7941   0.01292   0.00626   0.0036   0.0313   1.0000
   7.500   0.8175   0.01334   0.00668   0.0044   0.0282   1.0000
   7.750   0.8409   0.01379   0.00717   0.0051   0.0260   1.0000
   8.000   0.8646   0.01420   0.00764   0.0059   0.0246   1.0000
   8.250   0.8880   0.01466   0.00814   0.0066   0.0232   1.0000
   8.500   0.9110   0.01516   0.00867   0.0073   0.0218   1.0000
   8.750   0.9329   0.01583   0.00938   0.0082   0.0202   1.0000
   9.000   0.9558   0.01635   0.00997   0.0089   0.0195   1.0000
   9.250   0.9787   0.01686   0.01058   0.0097   0.0188   1.0000
   9.500   1.0012   0.01740   0.01119   0.0104   0.0179   1.0000
   9.750   1.0235   0.01796   0.01181   0.0111   0.0170   1.0000
  10.000   1.0450   0.01859   0.01250   0.0119   0.0163   1.0000
  10.250   1.0649   0.01941   0.01337   0.0129   0.0154   1.0000
  10.500   1.0847   0.02019   0.01424   0.0138   0.0146   1.0000
  10.750   1.1052   0.02086   0.01502   0.0147   0.0142   1.0000
  11.000   1.1249   0.02159   0.01586   0.0156   0.0136   1.0000
  11.250   1.1441   0.02232   0.01669   0.0166   0.0130   1.0000
  11.500   1.1630   0.02305   0.01750   0.0175   0.0124   1.0000
  11.750   1.1807   0.02384   0.01836   0.0186   0.0119   1.0000
  12.000   1.1959   0.02481   0.01940   0.0198   0.0113   1.0000
  12.250   1.2087   0.02592   0.02061   0.0213   0.0107   1.0000
  12.500   1.2216   0.02693   0.02175   0.0228   0.0105   1.0000
  12.750   1.2328   0.02792   0.02288   0.0244   0.0100   1.0000
  13.000   1.2386   0.02903   0.02411   0.0268   0.0097   1.0000
  13.250   1.2429   0.03027   0.02546   0.0289   0.0093   1.0000
  13.500   1.2453   0.03175   0.02706   0.0306   0.0091   1.0000
  13.750   1.2463   0.03351   0.02893   0.0318   0.0088   1.0000
  14.000   1.2454   0.03566   0.03120   0.0323   0.0086   1.0000
  14.250   1.2428   0.03831   0.03397   0.0321   0.0084   1.0000
  14.500   1.2354   0.04190   0.03771   0.0309   0.0083   1.0000
  14.750   1.2247   0.04653   0.04248   0.0284   0.0082   1.0000
  15.000   1.2113   0.05216   0.04827   0.0248   0.0081   1.0000
  15.250   1.1924   0.05924   0.05552   0.0201   0.0080   1.0000
  15.500   1.1690   0.06744   0.06389   0.0148   0.0080   1.0000
  15.750   1.1396   0.07686   0.07349   0.0090   0.0081   1.0000
  16.000   1.1083   0.08679   0.08359   0.0031   0.0083   1.0000
  16.250   1.0749   0.09736   0.09430  -0.0031   0.0083   1.0000
  16.500   1.0394   0.10873   0.10583  -0.0097   0.0085   1.0000
  16.750   1.0052   0.12056   0.11780  -0.0165   0.0087   1.0000
  17.000   0.9719   0.13294   0.13030  -0.0236   0.0087   1.0000
<< Back to S9026 (9.5%) (s9026-il)

Polar data table (+)

Polar graphs


<< Back to S9026 (9.5%) (s9026-il)