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=100,000 Ncrit=5


Details Polar file
Airfoil: S9026 (9.5%) (s9026-il)
Reynolds number: 100,000
Max Cl/Cd: 34.65 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9026-il-100000-n5.txt
Download as CSV file: xf-s9026-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7856   0.09862   0.09342   0.0009   1.0000   0.0346
 -12.250  -0.8226   0.08518   0.07998  -0.0080   1.0000   0.0340
 -12.000  -0.8550   0.07425   0.06897  -0.0162   1.0000   0.0332
 -11.750  -0.8856   0.06547   0.06001  -0.0231   1.0000   0.0327
 -11.500  -0.9112   0.05913   0.05346  -0.0271   1.0000   0.0323
 -11.250  -0.9326   0.05445   0.04854  -0.0283   1.0000   0.0324
 -11.000  -0.9502   0.05084   0.04467  -0.0273   1.0000   0.0327
 -10.750  -0.9623   0.04761   0.04109  -0.0255   1.0000   0.0335
 -10.500  -0.9668   0.04445   0.03750  -0.0239   1.0000   0.0344
 -10.250  -0.9642   0.04145   0.03417  -0.0224   1.0000   0.0353
 -10.000  -0.9544   0.03912   0.03171  -0.0213   1.0000   0.0363
  -9.750  -0.9422   0.03715   0.02956  -0.0201   1.0000   0.0374
  -9.500  -0.9284   0.03523   0.02740  -0.0190   1.0000   0.0389
  -9.250  -0.9131   0.03349   0.02541  -0.0179   1.0000   0.0410
  -9.000  -0.8964   0.03176   0.02335  -0.0167   1.0000   0.0435
  -8.750  -0.8788   0.02994   0.02131  -0.0156   1.0000   0.0457
  -8.500  -0.8603   0.02849   0.01981  -0.0147   1.0000   0.0479
  -8.250  -0.8409   0.02718   0.01839  -0.0137   1.0000   0.0508
  -8.000  -0.8205   0.02595   0.01692  -0.0126   1.0000   0.0547
  -7.750  -0.8010   0.02476   0.01569  -0.0117   1.0000   0.0591
  -7.500  -0.7803   0.02377   0.01462  -0.0107   1.0000   0.0644
  -7.250  -0.7597   0.02270   0.01345  -0.0097   1.0000   0.0699
  -7.000  -0.7385   0.02187   0.01258  -0.0088   1.0000   0.0774
  -6.750  -0.7174   0.02101   0.01170  -0.0078   1.0000   0.0857
  -6.500  -0.6955   0.02025   0.01085  -0.0069   1.0000   0.0957
  -6.250  -0.6736   0.01955   0.01011  -0.0060   1.0000   0.1073
  -6.000  -0.6519   0.01885   0.00943  -0.0051   1.0000   0.1206
  -5.750  -0.6299   0.01819   0.00879  -0.0041   1.0000   0.1355
  -5.500  -0.6080   0.01755   0.00819  -0.0032   1.0000   0.1515
  -5.250  -0.5861   0.01696   0.00766  -0.0023   1.0000   0.1709
  -5.000  -0.5638   0.01643   0.00717  -0.0013   1.0000   0.1926
  -4.750  -0.5418   0.01590   0.00673  -0.0003   1.0000   0.2164
  -4.500  -0.5198   0.01541   0.00634   0.0007   1.0000   0.2440
  -4.250  -0.4979   0.01495   0.00597   0.0017   1.0000   0.2748
  -4.000  -0.4760   0.01453   0.00567   0.0028   1.0000   0.3084
  -3.750  -0.4544   0.01411   0.00540   0.0039   1.0000   0.3440
  -3.500  -0.4326   0.01374   0.00516   0.0050   1.0000   0.3809
  -3.250  -0.4111   0.01339   0.00494   0.0062   1.0000   0.4185
  -3.000  -0.3897   0.01307   0.00478   0.0075   1.0000   0.4575
  -2.750  -0.3684   0.01278   0.00465   0.0088   1.0000   0.4978
  -2.500  -0.3474   0.01252   0.00456   0.0102   1.0000   0.5391
  -2.250  -0.3267   0.01230   0.00450   0.0117   1.0000   0.5817
  -2.000  -0.3060   0.01212   0.00448   0.0132   1.0000   0.6238
  -1.750  -0.2853   0.01198   0.00450   0.0148   1.0000   0.6651
  -1.500  -0.2546   0.01191   0.00456   0.0143   0.9942   0.7086
  -1.250  -0.2142   0.01188   0.00466   0.0121   0.9824   0.7525
  -1.000  -0.1744   0.01186   0.00474   0.0102   0.9697   0.7932
  -0.750  -0.1336   0.01185   0.00481   0.0082   0.9567   0.8287
  -0.500  -0.0913   0.01185   0.00486   0.0059   0.9427   0.8595
  -0.250  -0.0462   0.01185   0.00490   0.0031   0.9270   0.8858
   0.000   0.0000   0.01186   0.00491   0.0000   0.9081   0.9081
   0.250   0.0462   0.01185   0.00490  -0.0030   0.8858   0.9270
   0.500   0.0913   0.01185   0.00486  -0.0059   0.8595   0.9427
   0.750   0.1336   0.01185   0.00481  -0.0082   0.8287   0.9566
   1.000   0.1743   0.01186   0.00474  -0.0102   0.7930   0.9696
   1.250   0.2142   0.01188   0.00466  -0.0121   0.7524   0.9824
   1.500   0.2545   0.01191   0.00456  -0.0143   0.7084   0.9941
   1.750   0.2854   0.01198   0.00450  -0.0148   0.6650   1.0000
   2.000   0.3061   0.01211   0.00448  -0.0132   0.6241   1.0000
   2.250   0.3268   0.01230   0.00450  -0.0117   0.5817   1.0000
   2.500   0.3476   0.01252   0.00456  -0.0102   0.5394   1.0000
   2.750   0.3686   0.01278   0.00465  -0.0088   0.4980   1.0000
   3.000   0.3898   0.01307   0.00478  -0.0075   0.4574   1.0000
   3.250   0.4113   0.01339   0.00495  -0.0062   0.4186   1.0000
   3.500   0.4328   0.01374   0.00516  -0.0050   0.3808   1.0000
   3.750   0.4545   0.01411   0.00540  -0.0039   0.3440   1.0000
   4.250   0.4980   0.01495   0.00597  -0.0017   0.2747   1.0000
   4.500   0.5199   0.01541   0.00634  -0.0007   0.2439   1.0000
   4.750   0.5419   0.01590   0.00673   0.0003   0.2163   1.0000
   5.000   0.5638   0.01643   0.00717   0.0013   0.1926   1.0000
   5.250   0.5862   0.01696   0.00766   0.0022   0.1709   1.0000
   5.500   0.6081   0.01755   0.00819   0.0032   0.1515   1.0000
   5.750   0.6299   0.01819   0.00879   0.0041   0.1355   1.0000
   6.000   0.6519   0.01885   0.00943   0.0051   0.1206   1.0000
   6.250   0.6736   0.01955   0.01011   0.0060   0.1074   1.0000
   6.500   0.6955   0.02026   0.01085   0.0069   0.0958   1.0000
   6.750   0.7174   0.02101   0.01169   0.0078   0.0856   1.0000
   7.000   0.7385   0.02186   0.01257   0.0088   0.0774   1.0000
   7.250   0.7596   0.02270   0.01345   0.0097   0.0698   1.0000
   7.500   0.7802   0.02377   0.01462   0.0107   0.0644   1.0000
   7.750   0.8009   0.02476   0.01569   0.0117   0.0591   1.0000
   8.000   0.8204   0.02594   0.01691   0.0127   0.0546   1.0000
   8.250   0.8408   0.02718   0.01838   0.0137   0.0507   1.0000
   8.500   0.8602   0.02849   0.01981   0.0147   0.0479   1.0000
   8.750   0.8786   0.02994   0.02132   0.0157   0.0457   1.0000
   9.000   0.8962   0.03175   0.02333   0.0167   0.0436   1.0000
   9.250   0.9129   0.03348   0.02540   0.0179   0.0410   1.0000
   9.500   0.9282   0.03522   0.02739   0.0190   0.0388   1.0000
   9.750   0.9420   0.03713   0.02952   0.0202   0.0374   1.0000
  10.000   0.9542   0.03913   0.03172   0.0213   0.0363   1.0000
  10.250   0.9640   0.04146   0.03418   0.0224   0.0353   1.0000
  10.500   0.9668   0.04444   0.03748   0.0239   0.0344   1.0000
  10.750   0.9624   0.04759   0.04107   0.0255   0.0335   1.0000
  11.000   0.9504   0.05087   0.04469   0.0273   0.0329   1.0000
  11.250   0.9326   0.05452   0.04861   0.0283   0.0325   1.0000
  11.500   0.9110   0.05916   0.05349   0.0271   0.0323   1.0000
  11.750   0.8855   0.06548   0.06002   0.0230   0.0325   1.0000
  12.000   0.8554   0.07423   0.06895   0.0162   0.0332   1.0000
  12.250   0.8202   0.08589   0.08070   0.0073   0.0340   1.0000
<< Back to S9026 (9.5%) (s9026-il)

Polar data table (+)

Polar graphs


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