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

SG6051 (sg6051-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SG6051 (sg6051-il)
Reynolds number: 100,000
Max Cl/Cd: 57.11 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6051-il-100000-n5.txt
Download as CSV file: xf-sg6051-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6051                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4177   0.09411   0.08925  -0.0472   1.0000   0.0243
  -9.500  -0.4234   0.08929   0.08451  -0.0495   1.0000   0.0241
  -9.250  -0.4334   0.08459   0.07991  -0.0513   1.0000   0.0240
  -9.000  -0.4518   0.08085   0.07629  -0.0512   1.0000   0.0238
  -8.750  -0.4799   0.07845   0.07402  -0.0487   1.0000   0.0235
  -8.500  -0.4870   0.06695   0.06244  -0.0620   0.9881   0.0230
  -8.250  -0.4914   0.05710   0.05225  -0.0702   0.9783   0.0227
  -8.000  -0.4862   0.04891   0.04353  -0.0756   0.9717   0.0230
  -7.750  -0.4771   0.04279   0.03680  -0.0777   0.9638   0.0236
  -7.500  -0.4597   0.03664   0.02969  -0.0797   0.9589   0.0257
  -7.250  -0.4363   0.03465   0.02742  -0.0807   0.9532   0.0278
  -7.000  -0.4103   0.03253   0.02492  -0.0816   0.9481   0.0306
  -6.750  -0.3820   0.02961   0.02137  -0.0827   0.9444   0.0345
  -6.500  -0.3555   0.02874   0.02037  -0.0833   0.9389   0.0388
  -6.250  -0.3279   0.02717   0.01842  -0.0838   0.9339   0.0443
  -6.000  -0.2974   0.02620   0.01726  -0.0849   0.9301   0.0499
  -5.750  -0.2692   0.02490   0.01562  -0.0851   0.9253   0.0546
  -5.500  -0.2423   0.02398   0.01468  -0.0855   0.9198   0.0594
  -5.250  -0.2119   0.02299   0.01349  -0.0861   0.9159   0.0639
  -5.000  -0.1832   0.02210   0.01249  -0.0865   0.9117   0.0689
  -4.750  -0.1577   0.02144   0.01180  -0.0863   0.9057   0.0737
  -4.500  -0.1285   0.02081   0.01102  -0.0866   0.9014   0.0793
  -4.250  -0.1002   0.02015   0.01038  -0.0870   0.8973   0.0869
  -4.000  -0.0751   0.01971   0.00984  -0.0867   0.8910   0.0946
  -3.750  -0.0466   0.01919   0.00928  -0.0870   0.8865   0.1074
  -3.500  -0.0182   0.01861   0.00880  -0.0874   0.8824   0.1300
  -3.250   0.0066   0.01807   0.00843  -0.0872   0.8760   0.1754
  -3.000   0.0324   0.01711   0.00823  -0.0874   0.8716   0.3367
  -2.750   0.0601   0.01676   0.00808  -0.0875   0.8676   0.4414
  -2.500   0.0841   0.01655   0.00807  -0.0868   0.8611   0.5066
  -2.250   0.1099   0.01623   0.00799  -0.0863   0.8566   0.5822
  -2.000   0.1344   0.01588   0.00796  -0.0850   0.8527   0.6768
  -1.750   0.1533   0.01568   0.00816  -0.0822   0.8461   0.7994
  -1.500   0.1932   0.01556   0.00815  -0.0835   0.8425   0.9319
  -1.250   0.2431   0.01552   0.00794  -0.0880   0.8396   0.9859
  -1.000   0.2765   0.01559   0.00786  -0.0897   0.8338   1.0000
  -0.750   0.3006   0.01566   0.00779  -0.0892   0.8280   1.0000
  -0.500   0.3272   0.01566   0.00764  -0.0890   0.8239   1.0000
  -0.250   0.3501   0.01586   0.00775  -0.0885   0.8166   1.0000
   0.000   0.3764   0.01592   0.00770  -0.0883   0.8115   1.0000
   0.250   0.4026   0.01601   0.00769  -0.0881   0.8064   1.0000
   0.500   0.4273   0.01618   0.00780  -0.0877   0.7995   1.0000
   0.750   0.4550   0.01620   0.00775  -0.0876   0.7950   1.0000
   1.000   0.4797   0.01641   0.00792  -0.0873   0.7880   1.0000
   1.250   0.5065   0.01650   0.00796  -0.0871   0.7824   1.0000
   1.500   0.5340   0.01656   0.00799  -0.0871   0.7775   1.0000
   1.750   0.5587   0.01679   0.00822  -0.0867   0.7701   1.0000
   2.000   0.5870   0.01681   0.00821  -0.0867   0.7654   1.0000
   2.250   0.6117   0.01704   0.00848  -0.0864   0.7577   1.0000
   2.500   0.6394   0.01708   0.00852  -0.0863   0.7519   1.0000
   2.750   0.6651   0.01724   0.00871  -0.0860   0.7445   1.0000
   3.000   0.6924   0.01729   0.00879  -0.0858   0.7377   1.0000
   3.250   0.7183   0.01742   0.00896  -0.0855   0.7298   1.0000
   3.500   0.7458   0.01744   0.00901  -0.0853   0.7225   1.0000
   3.750   0.7712   0.01757   0.00921  -0.0848   0.7132   1.0000
   4.000   0.8000   0.01747   0.00915  -0.0847   0.7057   1.0000
   4.250   0.8245   0.01762   0.00939  -0.0841   0.6943   1.0000
   4.500   0.8501   0.01769   0.00954  -0.0835   0.6832   1.0000
   4.750   0.8764   0.01769   0.00963  -0.0831   0.6717   1.0000
   5.000   0.9026   0.01769   0.00969  -0.0825   0.6590   1.0000
   5.250   0.9280   0.01772   0.00980  -0.0818   0.6443   1.0000
   5.500   0.9525   0.01779   0.00997  -0.0810   0.6273   1.0000
   5.750   0.9770   0.01785   0.01011  -0.0802   0.6079   1.0000
   6.000   1.0011   0.01792   0.01022  -0.0792   0.5858   1.0000
   6.250   1.0240   0.01805   0.01037  -0.0781   0.5585   1.0000
   6.500   1.0451   0.01830   0.01062  -0.0767   0.5242   1.0000
   6.750   1.0648   0.01866   0.01087  -0.0750   0.4819   1.0000
   7.000   1.0815   0.01924   0.01125  -0.0730   0.4308   1.0000
   7.250   1.0942   0.02011   0.01183  -0.0705   0.3727   1.0000
   7.500   1.1033   0.02123   0.01264  -0.0676   0.3144   1.0000
   7.750   1.1105   0.02248   0.01360  -0.0647   0.2609   1.0000
   8.000   1.1172   0.02377   0.01464  -0.0618   0.2146   1.0000
   8.250   1.1230   0.02506   0.01573  -0.0588   0.1767   1.0000
   8.500   1.1282   0.02634   0.01687  -0.0558   0.1461   1.0000
   8.750   1.1343   0.02771   0.01813  -0.0530   0.1220   1.0000
   9.000   1.1414   0.02910   0.01949  -0.0506   0.1032   1.0000
   9.250   1.1482   0.03057   0.02092  -0.0483   0.0888   1.0000
   9.500   1.1552   0.03208   0.02245  -0.0461   0.0780   1.0000
   9.750   1.1608   0.03375   0.02410  -0.0439   0.0706   1.0000
  10.000   1.1686   0.03530   0.02575  -0.0420   0.0636   1.0000
  10.250   1.1738   0.03708   0.02756  -0.0400   0.0583   1.0000
  10.500   1.1818   0.03871   0.02933  -0.0383   0.0533   1.0000
  10.750   1.1861   0.04067   0.03131  -0.0365   0.0494   1.0000
  11.000   1.1945   0.04237   0.03318  -0.0350   0.0454   1.0000
  11.250   1.2016   0.04419   0.03510  -0.0335   0.0419   1.0000
  11.500   1.2052   0.04636   0.03728  -0.0320   0.0392   1.0000
  11.750   1.2140   0.04823   0.03935  -0.0306   0.0365   1.0000
  12.000   1.2210   0.05024   0.04151  -0.0293   0.0340   1.0000
  12.250   1.2258   0.05239   0.04374  -0.0282   0.0319   1.0000
  12.500   1.2302   0.05478   0.04618  -0.0269   0.0302   1.0000
  12.750   1.2376   0.05710   0.04880  -0.0257   0.0287   1.0000
  13.000   1.2435   0.05962   0.05154  -0.0245   0.0273   1.0000
  13.250   1.2469   0.06228   0.05439  -0.0235   0.0262   1.0000
  13.500   1.2484   0.06503   0.05729  -0.0227   0.0251   1.0000
  13.750   1.2487   0.06791   0.06026  -0.0221   0.0242   1.0000
  14.000   1.2473   0.07126   0.06374  -0.0215   0.0234   1.0000
  14.250   1.2413   0.07518   0.06800  -0.0212   0.0227   1.0000
  14.500   1.2333   0.07946   0.07259  -0.0212   0.0221   1.0000
  14.750   1.2235   0.08414   0.07756  -0.0216   0.0217   1.0000
  15.000   1.2114   0.08931   0.08301  -0.0225   0.0214   1.0000
  15.250   1.1973   0.09502   0.08899  -0.0240   0.0211   1.0000
  15.500   1.1810   0.10140   0.09562  -0.0263   0.0210   1.0000
  15.750   1.1626   0.10855   0.10303  -0.0295   0.0209   1.0000
  16.000   1.1418   0.11670   0.11143  -0.0338   0.0210   1.0000
  16.250   1.1183   0.12618   0.12115  -0.0395   0.0211   1.0000
  16.500   1.0909   0.13773   0.13291  -0.0469   0.0215   1.0000
  16.750   1.0588   0.15221   0.14755  -0.0565   0.0220   1.0000
<< Back to SG6051 (sg6051-il)

Polar data table (+)

Polar graphs


<< Back to SG6051 (sg6051-il)