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SG6051 (sg6051-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SG6051 (sg6051-il)
Reynolds number: 50,000
Max Cl/Cd: 35.79 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6051-il-50000.txt
Download as CSV file: xf-sg6051-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3681   0.10583   0.09926  -0.0296   1.0000   0.2798
  -8.500  -0.3677   0.10319   0.09671  -0.0283   1.0000   0.2952
  -8.250  -0.3698   0.10088   0.09448  -0.0265   1.0000   0.3114
  -8.000  -0.3743   0.09877   0.09247  -0.0240   1.0000   0.3267
  -7.750  -0.3798   0.09671   0.09050  -0.0212   1.0000   0.3409
  -7.500  -0.4247   0.09804   0.09206  -0.0162   1.0000   0.3463
  -7.250  -0.3984   0.09313   0.08712  -0.0143   1.0000   0.3676
  -7.000  -0.4069   0.09141   0.08548  -0.0103   1.0000   0.3842
  -6.750  -0.4180   0.08987   0.08401  -0.0061   1.0000   0.4015
  -6.500  -0.4321   0.08846   0.08270  -0.0016   1.0000   0.4181
  -6.250  -0.4486   0.08712   0.08146   0.0032   1.0000   0.4345
  -5.500  -0.5078   0.05773   0.05092  -0.0388   1.0000   0.1659
  -5.250  -0.4878   0.05140   0.04392  -0.0412   1.0000   0.1503
  -5.000  -0.4675   0.04723   0.03921  -0.0420   1.0000   0.1501
  -4.750  -0.4437   0.04342   0.03481  -0.0428   1.0000   0.1495
  -4.500  -0.4184   0.04037   0.03114  -0.0435   1.0000   0.1541
  -4.250  -0.3933   0.03797   0.02841  -0.0436   1.0000   0.1580
  -4.000  -0.3670   0.03618   0.02601  -0.0437   1.0000   0.1660
  -3.750  -0.3416   0.03438   0.02400  -0.0437   1.0000   0.1724
  -3.500  -0.3155   0.03320   0.02236  -0.0436   1.0000   0.1822
  -3.250  -0.2908   0.03200   0.02114  -0.0434   1.0000   0.1945
  -3.000  -0.2654   0.03096   0.02003  -0.0431   1.0000   0.2074
  -2.750  -0.2403   0.03011   0.01918  -0.0429   1.0000   0.2309
  -2.500  -0.2124   0.02922   0.01846  -0.0430   1.0000   0.2685
  -2.250  -0.1815   0.02699   0.01827  -0.0428   1.0000   0.5598
  -2.000  -0.1811   0.02557   0.01816  -0.0342   1.0000   1.0000
  -1.750  -0.1569   0.02596   0.01787  -0.0350   1.0000   1.0000
  -1.500  -0.1341   0.02641   0.01785  -0.0353   1.0000   1.0000
  -1.250  -0.1119   0.02691   0.01796  -0.0356   1.0000   1.0000
  -1.000  -0.0901   0.02745   0.01817  -0.0358   1.0000   1.0000
  -0.750  -0.0685   0.02804   0.01844  -0.0360   1.0000   1.0000
  -0.500  -0.0472   0.02865   0.01880  -0.0361   1.0000   1.0000
  -0.250  -0.0261   0.02931   0.01922  -0.0363   1.0000   1.0000
   0.000  -0.0052   0.03001   0.01970  -0.0364   1.0000   1.0000
   0.250   0.0154   0.03075   0.02025  -0.0366   1.0000   1.0000
   0.500   0.0358   0.03152   0.02086  -0.0367   1.0000   1.0000
   0.750   0.0560   0.03233   0.02152  -0.0368   1.0000   1.0000
   1.000   0.0759   0.03319   0.02224  -0.0370   1.0000   1.0000
   1.250   0.0956   0.03409   0.02302  -0.0372   1.0000   1.0000
   1.500   0.1150   0.03503   0.02386  -0.0373   1.0000   1.0000
   1.750   0.1573   0.03647   0.02519  -0.0419   0.9899   1.0000
   2.000   0.1974   0.03791   0.02654  -0.0461   0.9790   1.0000
   2.250   0.2357   0.03933   0.02790  -0.0497   0.9682   1.0000
   2.500   0.2761   0.04083   0.02935  -0.0537   0.9567   1.0000
   2.750   0.3064   0.04204   0.03054  -0.0559   0.9454   1.0000
   3.000   0.3348   0.04326   0.03176  -0.0576   0.9335   1.0000
   3.250   0.3656   0.04456   0.03308  -0.0597   0.9208   1.0000
   3.500   0.3970   0.04588   0.03443  -0.0618   0.9076   1.0000
   3.750   0.4287   0.04720   0.03579  -0.0639   0.8939   1.0000
   4.000   0.4597   0.04848   0.03715  -0.0657   0.8794   1.0000
   4.250   0.4898   0.04974   0.03847  -0.0673   0.8645   1.0000
   4.500   0.5187   0.05096   0.03977  -0.0686   0.8490   1.0000
   4.750   0.5468   0.05214   0.04104  -0.0697   0.8328   1.0000
   5.000   0.5755   0.05327   0.04230  -0.0707   0.8159   1.0000
   5.250   0.6063   0.05432   0.04348  -0.0718   0.7987   1.0000
   5.500   0.6414   0.05522   0.04456  -0.0733   0.7813   1.0000
   5.750   0.6802   0.05591   0.04543  -0.0749   0.7638   1.0000
   6.000   0.6949   0.05698   0.04663  -0.0736   0.7439   1.0000
   6.250   0.7277   0.05749   0.04733  -0.0741   0.7245   1.0000
   6.500   0.7756   0.05716   0.04729  -0.0755   0.7059   1.0000
   6.750   0.7899   0.05802   0.04832  -0.0738   0.6834   1.0000
   7.000   0.8395   0.05677   0.04741  -0.0743   0.6632   1.0000
   7.250   0.8651   0.05655   0.04742  -0.0727   0.6395   1.0000
   7.500   0.9412   0.05157   0.04294  -0.0726   0.6186   1.0000
   7.750   0.9930   0.04717   0.03898  -0.0699   0.5928   1.0000
   8.000   1.0959   0.03664   0.02908  -0.0681   0.5538   1.0000
   8.250   1.1351   0.03256   0.02504  -0.0636   0.4907   1.0000
   8.500   1.1449   0.03199   0.02392  -0.0577   0.4065   1.0000
   8.750   1.1411   0.03365   0.02479  -0.0520   0.3291   1.0000
   9.000   1.1405   0.03602   0.02646  -0.0475   0.2684   1.0000
   9.250   1.1532   0.03859   0.02853  -0.0451   0.2193   1.0000
   9.500   1.1795   0.04122   0.03087  -0.0446   0.1827   1.0000
   9.750   1.2115   0.04409   0.03366  -0.0448   0.1576   1.0000
  10.000   1.2448   0.04724   0.03683  -0.0454   0.1406   1.0000
  10.250   1.2651   0.05037   0.04020  -0.0444   0.1291   1.0000
  10.500   1.2854   0.05407   0.04416  -0.0435   0.1209   1.0000
  10.750   1.2965   0.05720   0.04759  -0.0416   0.1138   1.0000
  11.000   1.3088   0.06147   0.05208  -0.0402   0.1091   1.0000
  11.250   1.3000   0.06505   0.05622  -0.0363   0.1072   1.0000
  11.500   1.2879   0.06870   0.06031  -0.0325   0.1056   1.0000
  11.750   1.2714   0.07225   0.06421  -0.0285   0.1045   1.0000
  12.000   1.2511   0.07605   0.06830  -0.0249   0.1041   1.0000
  12.250   1.2271   0.08033   0.07288  -0.0220   0.1043   1.0000
  12.500   1.2000   0.08519   0.07800  -0.0202   0.1051   1.0000
  12.750   1.1714   0.09070   0.08374  -0.0194   0.1062   1.0000
  13.000   1.1424   0.09689   0.09011  -0.0198   0.1076   1.0000
  13.250   1.1162   0.10364   0.09699  -0.0212   0.1088   1.0000
  13.500   1.0940   0.11081   0.10425  -0.0233   0.1098   1.0000
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