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=1,000,000 Ncrit=5


Details Polar file
Airfoil: SG6051 (sg6051-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.79 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6051-il-1000000-n5.txt
Download as CSV file: xf-sg6051-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6691   0.10229   0.10049  -0.0290   1.0000   0.0037
 -13.250  -0.8288   0.06678   0.06478  -0.0502   1.0000   0.0033
 -13.000  -0.8892   0.04371   0.04136  -0.0706   0.9896   0.0031
 -12.250  -0.9275   0.03155   0.02833  -0.0711   0.9117   0.0032
 -12.000  -0.9230   0.02869   0.02516  -0.0703   0.9019   0.0032
 -11.750  -0.9121   0.02642   0.02263  -0.0696   0.8943   0.0033
 -11.500  -0.8966   0.02465   0.02063  -0.0691   0.8872   0.0033
 -11.250  -0.8784   0.02316   0.01894  -0.0686   0.8813   0.0034
 -11.000  -0.8581   0.02189   0.01750  -0.0684   0.8755   0.0035
 -10.750  -0.8366   0.02077   0.01620  -0.0681   0.8699   0.0036
 -10.500  -0.8138   0.01976   0.01504  -0.0679   0.8650   0.0036
 -10.250  -0.7902   0.01884   0.01399  -0.0678   0.8598   0.0037
 -10.000  -0.7660   0.01802   0.01302  -0.0677   0.8550   0.0038
  -9.750  -0.7411   0.01725   0.01213  -0.0677   0.8508   0.0038
  -9.500  -0.7156   0.01653   0.01130  -0.0677   0.8462   0.0039
  -9.250  -0.6898   0.01588   0.01053  -0.0678   0.8419   0.0041
  -9.000  -0.6636   0.01528   0.00981  -0.0678   0.8381   0.0042
  -8.750  -0.6368   0.01472   0.00916  -0.0680   0.8341   0.0043
  -8.500  -0.6099   0.01420   0.00855  -0.0681   0.8298   0.0044
  -8.250  -0.5827   0.01373   0.00798  -0.0683   0.8257   0.0046
  -8.000  -0.5553   0.01330   0.00747  -0.0685   0.8222   0.0047
  -7.750  -0.5274   0.01290   0.00699  -0.0687   0.8184   0.0049
  -7.500  -0.4998   0.01243   0.00645  -0.0689   0.8142   0.0051
  -7.250  -0.4720   0.01204   0.00597  -0.0691   0.8103   0.0055
  -7.000  -0.4439   0.01168   0.00556  -0.0694   0.8066   0.0059
  -6.750  -0.4155   0.01135   0.00519  -0.0697   0.8025   0.0063
  -6.500  -0.3870   0.01106   0.00484  -0.0700   0.7982   0.0069
  -6.250  -0.3587   0.01074   0.00447  -0.0703   0.7941   0.0086
  -6.000  -0.3302   0.01042   0.00415  -0.0707   0.7901   0.0123
  -5.750  -0.3015   0.01015   0.00390  -0.0710   0.7856   0.0176
  -5.500  -0.2727   0.00996   0.00369  -0.0714   0.7814   0.0212
  -5.250  -0.2437   0.00978   0.00351  -0.0718   0.7776   0.0245
  -5.000  -0.2146   0.00963   0.00334  -0.0722   0.7734   0.0263
  -4.750  -0.1855   0.00945   0.00316  -0.0726   0.7689   0.0295
  -4.500  -0.1564   0.00932   0.00300  -0.0730   0.7648   0.0318
  -4.250  -0.1271   0.00920   0.00286  -0.0734   0.7608   0.0336
  -4.000  -0.0979   0.00902   0.00268  -0.0738   0.7562   0.0378
  -3.750  -0.0687   0.00890   0.00254  -0.0742   0.7519   0.0408
  -3.500  -0.0393   0.00880   0.00241  -0.0746   0.7479   0.0427
  -3.250  -0.0099   0.00865   0.00227  -0.0751   0.7434   0.0480
  -3.000   0.0194   0.00854   0.00215  -0.0755   0.7388   0.0528
  -2.750   0.0487   0.00843   0.00204  -0.0759   0.7346   0.0603
  -2.500   0.0782   0.00831   0.00194  -0.0764   0.7302   0.0706
  -2.250   0.1075   0.00816   0.00184  -0.0769   0.7252   0.0906
  -2.000   0.1367   0.00801   0.00176  -0.0774   0.7203   0.1173
  -1.500   0.1954   0.00761   0.00160  -0.0784   0.7097   0.2036
  -1.250   0.2243   0.00724   0.00152  -0.0790   0.7050   0.3017
  -1.000   0.2537   0.00706   0.00151  -0.0796   0.7001   0.3616
  -0.750   0.2832   0.00700   0.00150  -0.0801   0.6949   0.3874
  -0.500   0.3125   0.00695   0.00149  -0.0805   0.6900   0.4125
  -0.250   0.3420   0.00684   0.00148  -0.0810   0.6846   0.4490
   0.000   0.3712   0.00671   0.00148  -0.0815   0.6788   0.4926
   0.250   0.4002   0.00645   0.00151  -0.0821   0.6728   0.5871
   0.500   0.4292   0.00625   0.00153  -0.0825   0.6653   0.6662
   0.750   0.4581   0.00616   0.00156  -0.0829   0.6580   0.7150
   1.000   0.4867   0.00605   0.00160  -0.0831   0.6501   0.7708
   1.250   0.5143   0.00594   0.00165  -0.0831   0.6420   0.8323
   1.750   0.5669   0.00587   0.00174  -0.0824   0.6221   0.9134
   2.000   0.5918   0.00586   0.00176  -0.0816   0.6123   0.9468
   2.250   0.6207   0.00590   0.00177  -0.0819   0.6009   0.9791
   2.500   0.6524   0.00598   0.00180  -0.0829   0.5867   0.9957
   2.750   0.6822   0.00608   0.00185  -0.0835   0.5714   1.0000
   3.000   0.7106   0.00622   0.00194  -0.0838   0.5555   1.0000
   3.250   0.7387   0.00640   0.00204  -0.0841   0.5347   1.0000
   3.500   0.7665   0.00662   0.00216  -0.0843   0.5109   1.0000
   4.000   0.8209   0.00719   0.00248  -0.0846   0.4503   1.0000
   4.250   0.8467   0.00763   0.00272  -0.0845   0.4051   1.0000
   4.500   0.8717   0.00815   0.00300  -0.0844   0.3544   1.0000
   4.750   0.8959   0.00875   0.00333  -0.0841   0.2994   1.0000
   5.000   0.9202   0.00930   0.00365  -0.0839   0.2532   1.0000
   5.250   0.9445   0.00981   0.00398  -0.0836   0.2130   1.0000
   5.500   0.9692   0.01026   0.00429  -0.0834   0.1829   1.0000
   5.750   0.9932   0.01076   0.00462  -0.0830   0.1523   1.0000
   6.000   1.0175   0.01119   0.00495  -0.0827   0.1278   1.0000
   6.250   1.0417   0.01162   0.00529  -0.0824   0.1077   1.0000
   6.500   1.0657   0.01204   0.00563  -0.0820   0.0900   1.0000
   6.750   1.0886   0.01254   0.00602  -0.0815   0.0715   1.0000
   7.000   1.1117   0.01299   0.00640  -0.0809   0.0569   1.0000
   7.250   1.1346   0.01344   0.00679  -0.0803   0.0459   1.0000
   7.500   1.1573   0.01388   0.00719  -0.0797   0.0376   1.0000
   7.750   1.1796   0.01432   0.00760  -0.0791   0.0312   1.0000
   8.000   1.2021   0.01471   0.00799  -0.0784   0.0276   1.0000
   8.250   1.2236   0.01516   0.00843  -0.0776   0.0240   1.0000
   8.500   1.2454   0.01555   0.00884  -0.0768   0.0223   1.0000
   8.750   1.2662   0.01598   0.00928  -0.0759   0.0204   1.0000
   9.000   1.2856   0.01647   0.00977  -0.0747   0.0183   1.0000
   9.250   1.3054   0.01690   0.01024  -0.0736   0.0171   1.0000
   9.500   1.3231   0.01738   0.01075  -0.0722   0.0154   1.0000
   9.750   1.3372   0.01797   0.01135  -0.0701   0.0136   1.0000
  10.000   1.3527   0.01853   0.01194  -0.0683   0.0122   1.0000
  10.250   1.3670   0.01921   0.01263  -0.0665   0.0105   1.0000
  10.500   1.3819   0.01989   0.01334  -0.0649   0.0094   1.0000
  10.750   1.3964   0.02063   0.01412  -0.0633   0.0085   1.0000
  11.000   1.4100   0.02146   0.01499  -0.0616   0.0077   1.0000
  11.250   1.4242   0.02228   0.01586  -0.0601   0.0073   1.0000
  11.500   1.4380   0.02314   0.01678  -0.0587   0.0069   1.0000
  11.750   1.4512   0.02407   0.01777  -0.0572   0.0066   1.0000
  12.000   1.4636   0.02508   0.01882  -0.0557   0.0062   1.0000
  12.250   1.4751   0.02617   0.01997  -0.0542   0.0059   1.0000
  12.500   1.4852   0.02742   0.02127  -0.0527   0.0055   1.0000
  12.750   1.4960   0.02860   0.02254  -0.0512   0.0053   1.0000
  13.000   1.5070   0.02980   0.02381  -0.0499   0.0052   1.0000
  13.250   1.5170   0.03110   0.02518  -0.0486   0.0051   1.0000
  13.500   1.5263   0.03249   0.02665  -0.0473   0.0049   1.0000
  13.750   1.5347   0.03396   0.02819  -0.0460   0.0048   1.0000
  14.000   1.5425   0.03551   0.02982  -0.0447   0.0047   1.0000
  14.250   1.5496   0.03717   0.03156  -0.0435   0.0045   1.0000
  14.500   1.5557   0.03894   0.03341  -0.0424   0.0044   1.0000
  14.750   1.5608   0.04082   0.03537  -0.0412   0.0043   1.0000
  15.000   1.5648   0.04286   0.03750  -0.0401   0.0041   1.0000
  15.250   1.5673   0.04512   0.03984  -0.0391   0.0040   1.0000
  15.500   1.5678   0.04766   0.04248  -0.0382   0.0039   1.0000
  15.750   1.5663   0.05049   0.04542  -0.0373   0.0037   1.0000
  16.000   1.5688   0.05298   0.04801  -0.0368   0.0037   1.0000
  16.250   1.5711   0.05558   0.05070  -0.0364   0.0036   1.0000
  16.500   1.5717   0.05844   0.05366  -0.0361   0.0036   1.0000
  16.750   1.5708   0.06154   0.05687  -0.0360   0.0035   1.0000
  17.000   1.5685   0.06490   0.06034  -0.0360   0.0034   1.0000
  17.250   1.5656   0.06847   0.06402  -0.0362   0.0034   1.0000
  17.500   1.5616   0.07226   0.06792  -0.0366   0.0033   1.0000
  17.750   1.5560   0.07638   0.07216  -0.0372   0.0033   1.0000
  18.000   1.5489   0.08079   0.07669  -0.0380   0.0032   1.0000
  18.250   1.5411   0.08542   0.08145  -0.0391   0.0032   1.0000
  18.500   1.5312   0.09050   0.08666  -0.0404   0.0031   1.0000
  18.750   1.5207   0.09583   0.09211  -0.0420   0.0031   1.0000
  19.000   1.5077   0.10165   0.09806  -0.0440   0.0031   1.0000
  19.250   1.4941   0.10770   0.10424  -0.0463   0.0030   1.0000
<< Back to SG6051 (sg6051-il)

Polar data table (+)

Polar graphs


<< Back to SG6051 (sg6051-il)