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

S3025 9.38% (s3025-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 500,000
Max Cl/Cd: 109.72 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3025-il-500000.txt
Download as CSV file: xf-s3025-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3025 9.38%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3450   0.08359   0.08147  -0.0336   1.0000   0.0157
  -7.750  -0.3508   0.08105   0.07897  -0.0331   1.0000   0.0157
  -7.500  -0.3622   0.07900   0.07699  -0.0313   1.0000   0.0160
  -7.250  -0.3727   0.07667   0.07472  -0.0307   0.9990   0.0162
  -7.000  -0.3445   0.06997   0.06800  -0.0425   0.9937   0.0169
  -6.750  -0.3012   0.05789   0.05577  -0.0638   0.9862   0.0186
  -6.500  -0.2813   0.04724   0.04490  -0.0747   0.9784   0.0191
  -6.250  -0.2542   0.04522   0.04286  -0.0782   0.9746   0.0199
  -6.000  -0.2246   0.04151   0.03902  -0.0827   0.9694   0.0212
  -5.750  -0.1952   0.03633   0.03354  -0.0869   0.9611   0.0233
  -5.500  -0.1728   0.02996   0.02660  -0.0894   0.9490   0.0261
  -5.250  -0.1471   0.02844   0.02505  -0.0904   0.9385   0.0274
  -5.000  -0.1213   0.02639   0.02279  -0.0909   0.9259   0.0295
  -4.750  -0.0904   0.02669   0.02264  -0.0902   0.9116   0.0330
  -4.500  -0.0738   0.02133   0.01696  -0.0904   0.8954   0.0355
  -4.250  -0.0485   0.01534   0.00997  -0.0877   0.8805   0.0176
  -4.000  -0.0235   0.01332   0.00759  -0.0867   0.8656   0.0162
  -3.750   0.0021   0.01212   0.00615  -0.0859   0.8511   0.0159
  -3.500   0.0278   0.01135   0.00522  -0.0852   0.8372   0.0164
  -3.250   0.0536   0.01076   0.00450  -0.0845   0.8239   0.0171
  -3.000   0.0797   0.01030   0.00392  -0.0840   0.8115   0.0180
  -2.750   0.1056   0.00983   0.00333  -0.0834   0.7995   0.0196
  -2.500   0.1320   0.00946   0.00289  -0.0830   0.7876   0.0218
  -2.250   0.1588   0.00921   0.00254  -0.0826   0.7764   0.0244
  -2.000   0.1849   0.00866   0.00212  -0.0821   0.7660   0.0726
  -1.750   0.2104   0.00818   0.00197  -0.0819   0.7558   0.1848
  -1.500   0.2361   0.00777   0.00190  -0.0816   0.7452   0.3009
  -1.250   0.2610   0.00730   0.00186  -0.0813   0.7353   0.4503
  -0.750   0.3018   0.00616   0.00191  -0.0778   0.7159   0.8495
  -0.500   0.3492   0.00605   0.00188  -0.0813   0.7064   0.9772
   0.000   0.4252   0.00614   0.00173  -0.0857   0.6863   1.0000
   0.250   0.4501   0.00622   0.00171  -0.0850   0.6766   1.0000
   0.750   0.5003   0.00637   0.00170  -0.0837   0.6571   1.0000
   1.000   0.5256   0.00646   0.00171  -0.0832   0.6478   1.0000
   1.250   0.5510   0.00656   0.00173  -0.0826   0.6384   1.0000
   1.500   0.5767   0.00663   0.00176  -0.0821   0.6283   1.0000
   1.750   0.6024   0.00672   0.00180  -0.0816   0.6186   1.0000
   2.250   0.6540   0.00692   0.00189  -0.0807   0.5981   1.0000
   2.500   0.6800   0.00702   0.00196  -0.0803   0.5875   1.0000
   2.750   0.7059   0.00713   0.00203  -0.0798   0.5765   1.0000
   3.000   0.7316   0.00726   0.00210  -0.0794   0.5648   1.0000
   3.250   0.7575   0.00737   0.00218  -0.0790   0.5523   1.0000
   3.500   0.7834   0.00750   0.00229  -0.0786   0.5391   1.0000
   3.750   0.8092   0.00763   0.00239  -0.0782   0.5257   1.0000
   4.000   0.8349   0.00778   0.00251  -0.0777   0.5115   1.0000
   4.250   0.8604   0.00794   0.00263  -0.0773   0.4965   1.0000
   4.500   0.8857   0.00812   0.00278  -0.0768   0.4805   1.0000
   4.750   0.9108   0.00833   0.00294  -0.0763   0.4630   1.0000
   5.000   0.9359   0.00853   0.00311  -0.0759   0.4438   1.0000
   5.250   0.9604   0.00878   0.00330  -0.0753   0.4234   1.0000
   5.500   0.9848   0.00905   0.00352  -0.0747   0.4034   1.0000
   5.750   1.0091   0.00933   0.00375  -0.0741   0.3817   1.0000
   6.000   1.0325   0.00968   0.00401  -0.0735   0.3558   1.0000
   6.250   1.0546   0.01014   0.00433  -0.0726   0.3221   1.0000
   6.500   1.0765   0.01062   0.00467  -0.0717   0.2902   1.0000
   6.750   1.0992   0.01104   0.00501  -0.0710   0.2659   1.0000
   7.000   1.1215   0.01149   0.00537  -0.0702   0.2410   1.0000
   7.250   1.1427   0.01202   0.00579  -0.0692   0.2122   1.0000
   7.500   1.1639   0.01255   0.00622  -0.0683   0.1870   1.0000
   7.750   1.1844   0.01313   0.00669  -0.0673   0.1611   1.0000
   8.000   1.2040   0.01376   0.00720  -0.0662   0.1358   1.0000
   8.250   1.2227   0.01446   0.00778  -0.0649   0.1100   1.0000
   8.500   1.2404   0.01522   0.00841  -0.0635   0.0841   1.0000
   8.750   1.2535   0.01633   0.00927  -0.0615   0.0486   1.0000
   9.000   1.2632   0.01766   0.01040  -0.0589   0.0221   1.0000
   9.250   1.2783   0.01850   0.01126  -0.0570   0.0178   1.0000
   9.500   1.2939   0.01925   0.01209  -0.0552   0.0161   1.0000
   9.750   1.3064   0.02005   0.01297  -0.0530   0.0151   1.0000
  10.000   1.3142   0.02106   0.01407  -0.0500   0.0142   1.0000
  10.250   1.3190   0.02225   0.01538  -0.0468   0.0136   1.0000
  10.500   1.3275   0.02325   0.01647  -0.0442   0.0133   1.0000
  10.750   1.3341   0.02440   0.01773  -0.0417   0.0131   1.0000
  11.000   1.3397   0.02567   0.01911  -0.0393   0.0128   1.0000
  11.250   1.3438   0.02713   0.02068  -0.0369   0.0125   1.0000
  11.500   1.3480   0.02866   0.02231  -0.0349   0.0122   1.0000
  11.750   1.3510   0.03040   0.02416  -0.0331   0.0118   1.0000
  12.000   1.3539   0.03225   0.02612  -0.0315   0.0115   1.0000
  12.250   1.3549   0.03438   0.02835  -0.0300   0.0112   1.0000
  12.500   1.3559   0.03663   0.03069  -0.0289   0.0109   1.0000
  12.750   1.3551   0.03918   0.03335  -0.0279   0.0107   1.0000
  13.000   1.3532   0.04196   0.03623  -0.0270   0.0105   1.0000
  13.250   1.3505   0.04497   0.03936  -0.0262   0.0103   1.0000
  13.500   1.3484   0.04805   0.04256  -0.0255   0.0102   1.0000
  13.750   1.3441   0.05161   0.04626  -0.0246   0.0100   1.0000
  14.000   1.3427   0.05489   0.04969  -0.0242   0.0099   1.0000
  14.250   1.3426   0.05809   0.05303  -0.0239   0.0099   1.0000
  14.500   1.3405   0.06141   0.05651  -0.0245   0.0098   1.0000
  14.750   1.3372   0.06510   0.06037  -0.0251   0.0097   1.0000
  15.000   1.3334   0.06894   0.06437  -0.0261   0.0095   1.0000
  15.250   1.3282   0.07318   0.06877  -0.0273   0.0094   1.0000
  15.500   1.3206   0.07800   0.07378  -0.0286   0.0095   1.0000
  15.750   1.3139   0.08277   0.07871  -0.0306   0.0092   1.0000
  16.000   1.3051   0.08811   0.08422  -0.0329   0.0091   1.0000
  16.250   1.2952   0.09388   0.09016  -0.0356   0.0090   1.0000
  16.500   1.2839   0.10009   0.09654  -0.0386   0.0089   1.0000
  16.750   1.2708   0.10688   0.10350  -0.0420   0.0090   1.0000
  17.000   1.2574   0.11400   0.11079  -0.0459   0.0089   1.0000
  17.250   1.2423   0.12176   0.11872  -0.0503   0.0089   1.0000
  17.500   1.2274   0.12975   0.12688  -0.0552   0.0089   1.0000
  17.750   1.2114   0.13829   0.13558  -0.0604   0.0090   1.0000
  18.000   1.1941   0.14753   0.14497  -0.0662   0.0091   1.0000
  18.250   1.1763   0.15734   0.15494  -0.0725   0.0092   1.0000
  18.500   1.1576   0.16781   0.16553  -0.0793   0.0093   1.0000
  18.750   1.1358   0.17979   0.17763  -0.0869   0.0095   1.0000
<< Back to S3025 9.38% (s3025-il)

Polar data table (+)

Polar graphs


<< Back to S3025 9.38% (s3025-il)