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

S3010-103-84 (s3010-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S3010-103-84 (s3010-il)
Reynolds number: 500,000
Max Cl/Cd: 95.79 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3010-il-500000.txt
Download as CSV file: xf-s3010-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3010-103-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4381   0.07353   0.07142  -0.0328   1.0000   0.0265
  -8.250  -0.4567   0.06271   0.06058  -0.0449   1.0000   0.0265
  -8.000  -0.4808   0.05319   0.05086  -0.0518   1.0000   0.0269
  -7.750  -0.4695   0.05138   0.04914  -0.0514   1.0000   0.0273
  -7.500  -0.4618   0.04942   0.04717  -0.0514   1.0000   0.0277
  -7.250  -0.4409   0.04640   0.04407  -0.0548   0.9908   0.0284
  -7.000  -0.4140   0.04176   0.03921  -0.0603   0.9787   0.0297
  -6.750  -0.3866   0.03761   0.03419  -0.0647   0.9618   0.0329
  -6.500  -0.3870   0.02206   0.01748  -0.0649   0.9434   0.0201
  -6.250  -0.3682   0.01892   0.01384  -0.0635   0.9294   0.0190
  -6.000  -0.3461   0.01719   0.01179  -0.0623   0.9166   0.0188
  -5.750  -0.3226   0.01592   0.01029  -0.0613   0.9047   0.0188
  -5.500  -0.2985   0.01496   0.00916  -0.0604   0.8936   0.0191
  -5.250  -0.2739   0.01410   0.00815  -0.0595   0.8829   0.0193
  -5.000  -0.2482   0.01344   0.00740  -0.0589   0.8714   0.0199
  -4.750  -0.2223   0.01289   0.00674  -0.0583   0.8607   0.0207
  -4.500  -0.1964   0.01232   0.00606  -0.0577   0.8505   0.0211
  -4.250  -0.1702   0.01169   0.00534  -0.0572   0.8394   0.0215
  -4.000  -0.1442   0.01093   0.00452  -0.0568   0.8287   0.0226
  -3.750  -0.1174   0.01053   0.00405  -0.0564   0.8185   0.0239
  -3.500  -0.0901   0.01021   0.00365  -0.0560   0.8074   0.0256
  -3.250  -0.0627   0.00983   0.00322  -0.0558   0.7965   0.0284
  -3.000  -0.0352   0.00951   0.00287  -0.0555   0.7858   0.0361
  -2.750  -0.0085   0.00889   0.00251  -0.0553   0.7749   0.1014
  -2.500   0.0189   0.00855   0.00233  -0.0552   0.7633   0.1536
  -2.250   0.0463   0.00829   0.00219  -0.0551   0.7521   0.2055
  -2.000   0.0735   0.00798   0.00207  -0.0550   0.7408   0.2755
  -1.750   0.1007   0.00767   0.00198  -0.0549   0.7288   0.3544
  -1.500   0.1277   0.00733   0.00192  -0.0547   0.7165   0.4475
  -1.250   0.1547   0.00707   0.00187  -0.0545   0.7044   0.5316
  -1.000   0.1815   0.00687   0.00184  -0.0541   0.6922   0.6057
  -0.750   0.2076   0.00667   0.00183  -0.0536   0.6799   0.6851
  -0.500   0.2335   0.00651   0.00183  -0.0528   0.6670   0.7539
  -0.250   0.2585   0.00638   0.00184  -0.0518   0.6542   0.8159
   0.000   0.2820   0.00627   0.00184  -0.0504   0.6415   0.8768
   0.250   0.3081   0.00621   0.00182  -0.0494   0.6286   0.9387
   0.500   0.3505   0.00622   0.00175  -0.0523   0.6137   0.9862
   0.750   0.3836   0.00630   0.00172  -0.0533   0.5993   1.0000
   1.000   0.4107   0.00640   0.00172  -0.0531   0.5853   1.0000
   1.250   0.4379   0.00651   0.00173  -0.0529   0.5713   1.0000
   1.500   0.4652   0.00663   0.00176  -0.0527   0.5574   1.0000
   1.750   0.4927   0.00675   0.00179  -0.0526   0.5434   1.0000
   2.000   0.5203   0.00687   0.00184  -0.0524   0.5293   1.0000
   2.250   0.5478   0.00699   0.00190  -0.0523   0.5155   1.0000
   2.500   0.5753   0.00713   0.00196  -0.0522   0.5014   1.0000
   2.750   0.6028   0.00727   0.00204  -0.0520   0.4876   1.0000
   3.000   0.6303   0.00743   0.00213  -0.0519   0.4734   1.0000
   3.250   0.6577   0.00759   0.00223  -0.0518   0.4593   1.0000
   3.500   0.6850   0.00775   0.00233  -0.0517   0.4450   1.0000
   3.750   0.7123   0.00793   0.00245  -0.0515   0.4308   1.0000
   4.000   0.7395   0.00811   0.00258  -0.0514   0.4165   1.0000
   4.250   0.7667   0.00830   0.00272  -0.0513   0.4019   1.0000
   4.500   0.7937   0.00851   0.00287  -0.0511   0.3872   1.0000
   4.750   0.8207   0.00872   0.00303  -0.0510   0.3719   1.0000
   5.000   0.8475   0.00894   0.00321  -0.0509   0.3566   1.0000
   5.250   0.8743   0.00917   0.00340  -0.0507   0.3408   1.0000
   5.500   0.9008   0.00942   0.00360  -0.0505   0.3249   1.0000
   5.750   0.9272   0.00968   0.00382  -0.0503   0.3085   1.0000
   6.000   0.9535   0.00997   0.00405  -0.0501   0.2924   1.0000
   6.250   0.9794   0.01027   0.00430  -0.0499   0.2760   1.0000
   6.500   1.0052   0.01059   0.00458  -0.0497   0.2600   1.0000
   6.750   1.0307   0.01094   0.00487  -0.0494   0.2441   1.0000
   7.000   1.0560   0.01130   0.00518  -0.0491   0.2283   1.0000
   7.250   1.0811   0.01168   0.00552  -0.0488   0.2130   1.0000
   7.500   1.1059   0.01208   0.00587  -0.0485   0.1980   1.0000
   7.750   1.1305   0.01249   0.00624  -0.0481   0.1840   1.0000
   8.000   1.1549   0.01290   0.00662  -0.0477   0.1708   1.0000
   8.250   1.1790   0.01334   0.00704  -0.0473   0.1577   1.0000
   8.500   1.2028   0.01379   0.00747  -0.0468   0.1457   1.0000
   8.750   1.2262   0.01426   0.00793  -0.0463   0.1345   1.0000
   9.000   1.2489   0.01478   0.00843  -0.0458   0.1231   1.0000
   9.250   1.2710   0.01534   0.00895  -0.0452   0.1121   1.0000
   9.500   1.2923   0.01595   0.00952  -0.0444   0.1011   1.0000
   9.750   1.3141   0.01649   0.01005  -0.0438   0.0917   1.0000
  10.000   1.3351   0.01706   0.01064  -0.0430   0.0831   1.0000
  10.250   1.3548   0.01772   0.01127  -0.0421   0.0748   1.0000
  10.500   1.3740   0.01839   0.01194  -0.0412   0.0679   1.0000
  10.750   1.3930   0.01902   0.01261  -0.0402   0.0624   1.0000
  11.000   1.4097   0.01979   0.01337  -0.0390   0.0569   1.0000
  11.250   1.4268   0.02046   0.01411  -0.0377   0.0525   1.0000
  11.500   1.4411   0.02125   0.01491  -0.0362   0.0480   1.0000
  11.750   1.4524   0.02203   0.01574  -0.0342   0.0444   1.0000
  12.000   1.4631   0.02282   0.01658  -0.0322   0.0409   1.0000
  12.250   1.4688   0.02397   0.01774  -0.0299   0.0374   1.0000
  12.500   1.4797   0.02485   0.01870  -0.0283   0.0342   1.0000
  12.750   1.4830   0.02633   0.02020  -0.0264   0.0304   1.0000
  13.000   1.4907   0.02761   0.02155  -0.0250   0.0266   1.0000
  13.250   1.4922   0.02946   0.02345  -0.0235   0.0231   1.0000
  13.500   1.4919   0.03162   0.02565  -0.0223   0.0201   1.0000
  13.750   1.4913   0.03397   0.02810  -0.0214   0.0176   1.0000
  14.000   1.4904   0.03649   0.03070  -0.0209   0.0166   1.0000
  14.250   1.4824   0.03997   0.03426  -0.0207   0.0152   1.0000
  14.500   1.4810   0.04288   0.03730  -0.0207   0.0147   1.0000
  14.750   1.4769   0.04626   0.04081  -0.0211   0.0140   1.0000
  15.000   1.4725   0.04985   0.04451  -0.0218   0.0135   1.0000
  15.250   1.4645   0.05407   0.04884  -0.0230   0.0130   1.0000
  15.500   1.4550   0.05866   0.05354  -0.0244   0.0127   1.0000
  15.750   1.4449   0.06356   0.05857  -0.0262   0.0125   1.0000
  16.000   1.4290   0.06959   0.06473  -0.0286   0.0123   1.0000
  16.250   1.4127   0.07590   0.07117  -0.0313   0.0120   1.0000
  16.500   1.4017   0.08162   0.07702  -0.0339   0.0118   1.0000
<< Back to S3010-103-84 (s3010-il)

Polar data table (+)

Polar graphs


<< Back to S3010-103-84 (s3010-il)