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

SG6042 (sg6042-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.88 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6042-il-1000000-n5.txt
Download as CSV file: xf-sg6042-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6042                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3787   0.13640   0.13460  -0.0327   0.9996   0.0045
 -11.000  -0.6315   0.02749   0.02476  -0.1171   0.9741   0.0049
 -10.750  -0.6157   0.02473   0.02173  -0.1183   0.9697   0.0050
 -10.500  -0.5951   0.02307   0.01991  -0.1189   0.9650   0.0051
 -10.250  -0.5702   0.02125   0.01788  -0.1203   0.9620   0.0052
 -10.000  -0.5414   0.02018   0.01669  -0.1217   0.9600   0.0053
  -9.750  -0.5208   0.01923   0.01562  -0.1212   0.9533   0.0054
  -9.500  -0.4942   0.01796   0.01416  -0.1221   0.9492   0.0056
  -9.250  -0.4651   0.01701   0.01307  -0.1232   0.9460   0.0058
  -9.000  -0.4402   0.01607   0.01198  -0.1233   0.9399   0.0059
  -8.750  -0.4116   0.01529   0.01106  -0.1240   0.9350   0.0062
  -8.500  -0.3837   0.01458   0.01020  -0.1245   0.9298   0.0064
  -8.250  -0.3566   0.01399   0.00947  -0.1247   0.9234   0.0066
  -8.000  -0.3290   0.01330   0.00864  -0.1251   0.9178   0.0068
  -7.750  -0.3035   0.01270   0.00796  -0.1250   0.9111   0.0071
  -7.500  -0.2764   0.01228   0.00745  -0.1250   0.9050   0.0073
  -7.250  -0.2497   0.01192   0.00702  -0.1250   0.8992   0.0076
  -7.000  -0.2231   0.01156   0.00659  -0.1249   0.8930   0.0079
  -6.750  -0.1963   0.01118   0.00611  -0.1248   0.8873   0.0082
  -6.500  -0.1700   0.01079   0.00564  -0.1246   0.8812   0.0085
  -6.250  -0.1433   0.01047   0.00522  -0.1244   0.8754   0.0088
  -6.000  -0.1164   0.01020   0.00488  -0.1243   0.8701   0.0091
  -5.750  -0.0902   0.00977   0.00438  -0.1240   0.8645   0.0095
  -5.500  -0.0634   0.00948   0.00405  -0.1239   0.8593   0.0099
  -5.250  -0.0363   0.00927   0.00381  -0.1238   0.8545   0.0105
  -5.000  -0.0093   0.00903   0.00352  -0.1236   0.8492   0.0110
  -4.750   0.0178   0.00880   0.00323  -0.1235   0.8442   0.0114
  -4.500   0.0451   0.00859   0.00298  -0.1234   0.8394   0.0118
  -4.250   0.0722   0.00835   0.00270  -0.1232   0.8339   0.0122
  -4.000   0.0992   0.00812   0.00242  -0.1230   0.8284   0.0130
  -3.750   0.1266   0.00795   0.00223  -0.1229   0.8232   0.0139
  -3.500   0.1541   0.00780   0.00205  -0.1228   0.8176   0.0146
  -3.000   0.2091   0.00753   0.00171  -0.1226   0.8072   0.0166
  -2.750   0.2365   0.00741   0.00158  -0.1224   0.8008   0.0186
  -2.500   0.2637   0.00727   0.00146  -0.1223   0.7942   0.0266
  -2.250   0.2911   0.00713   0.00137  -0.1222   0.7872   0.0410
  -2.000   0.3184   0.00705   0.00129  -0.1220   0.7808   0.0521
  -1.750   0.3459   0.00695   0.00122  -0.1219   0.7736   0.0660
  -1.500   0.3729   0.00688   0.00116  -0.1217   0.7650   0.0810
  -1.250   0.3998   0.00678   0.00111  -0.1215   0.7543   0.1076
  -1.000   0.4266   0.00665   0.00106  -0.1213   0.7433   0.1495
  -0.750   0.4530   0.00647   0.00103  -0.1211   0.7324   0.2171
  -0.500   0.4792   0.00624   0.00101  -0.1209   0.7205   0.3120
  -0.250   0.5051   0.00608   0.00101  -0.1206   0.7061   0.3931
   0.000   0.5303   0.00584   0.00103  -0.1202   0.6894   0.5167
   0.250   0.5558   0.00575   0.00108  -0.1198   0.6719   0.5936
   0.500   0.5813   0.00579   0.00114  -0.1192   0.6520   0.6353
   0.750   0.6058   0.00585   0.00121  -0.1185   0.6283   0.6801
   1.000   0.6300   0.00595   0.00130  -0.1177   0.6020   0.7196
   1.250   0.6546   0.00604   0.00139  -0.1169   0.5792   0.7529
   1.500   0.6786   0.00617   0.00149  -0.1161   0.5543   0.7831
   1.750   0.7020   0.00634   0.00160  -0.1151   0.5245   0.8118
   2.000   0.7245   0.00655   0.00174  -0.1140   0.4895   0.8391
   2.250   0.7465   0.00679   0.00188  -0.1128   0.4531   0.8626
   2.500   0.7688   0.00700   0.00201  -0.1116   0.4233   0.8861
   2.750   0.7901   0.00715   0.00214  -0.1101   0.3998   0.9176
   3.000   0.8161   0.00736   0.00227  -0.1098   0.3684   0.9736
   3.250   0.8423   0.00765   0.00242  -0.1096   0.3394   1.0000
   3.500   0.8665   0.00793   0.00258  -0.1090   0.3145   1.0000
   3.750   0.8900   0.00825   0.00276  -0.1082   0.2862   1.0000
   4.000   0.9133   0.00858   0.00296  -0.1074   0.2592   1.0000
   4.250   0.9366   0.00891   0.00316  -0.1067   0.2340   1.0000
   4.500   0.9599   0.00924   0.00337  -0.1059   0.2104   1.0000
   5.000   1.0070   0.00985   0.00379  -0.1044   0.1748   1.0000
   5.250   1.0302   0.01016   0.00403  -0.1036   0.1577   1.0000
   5.500   1.0538   0.01044   0.00425  -0.1029   0.1454   1.0000
   5.750   1.0771   0.01074   0.00448  -0.1022   0.1337   1.0000
   6.000   1.1002   0.01104   0.00473  -0.1014   0.1223   1.0000
   6.250   1.1231   0.01134   0.00499  -0.1005   0.1116   1.0000
   6.500   1.1460   0.01163   0.00524  -0.0997   0.1033   1.0000
   6.750   1.1684   0.01195   0.00552  -0.0988   0.0953   1.0000
   7.000   1.1910   0.01224   0.00580  -0.0979   0.0886   1.0000
   7.250   1.2126   0.01258   0.00610  -0.0969   0.0809   1.0000
   7.500   1.2341   0.01291   0.00640  -0.0959   0.0740   1.0000
   7.750   1.2545   0.01324   0.00672  -0.0946   0.0678   1.0000
   8.000   1.2746   0.01357   0.00704  -0.0933   0.0631   1.0000
   8.250   1.2938   0.01394   0.00738  -0.0918   0.0577   1.0000
   8.500   1.3132   0.01429   0.00773  -0.0904   0.0536   1.0000
   8.750   1.3317   0.01470   0.00813  -0.0889   0.0491   1.0000
   9.000   1.3511   0.01504   0.00849  -0.0875   0.0466   1.0000
   9.250   1.3697   0.01544   0.00889  -0.0860   0.0436   1.0000
   9.500   1.3874   0.01590   0.00934  -0.0844   0.0401   1.0000
   9.750   1.4059   0.01629   0.00977  -0.0830   0.0379   1.0000
  10.000   1.4235   0.01674   0.01023  -0.0814   0.0354   1.0000
  10.250   1.4401   0.01726   0.01075  -0.0797   0.0327   1.0000
  10.500   1.4573   0.01772   0.01125  -0.0782   0.0310   1.0000
  10.750   1.4740   0.01822   0.01178  -0.0766   0.0290   1.0000
  11.000   1.4891   0.01883   0.01239  -0.0749   0.0266   1.0000
  11.250   1.5048   0.01940   0.01300  -0.0732   0.0250   1.0000
  11.500   1.5199   0.02002   0.01364  -0.0715   0.0232   1.0000
  11.750   1.5338   0.02072   0.01436  -0.0697   0.0213   1.0000
  12.000   1.5473   0.02144   0.01512  -0.0680   0.0195   1.0000
  12.250   1.5608   0.02218   0.01590  -0.0662   0.0182   1.0000
  12.500   1.5727   0.02304   0.01679  -0.0644   0.0167   1.0000
  12.750   1.5851   0.02388   0.01767  -0.0627   0.0158   1.0000
  13.000   1.5976   0.02473   0.01859  -0.0610   0.0152   1.0000
  13.250   1.6090   0.02567   0.01958  -0.0593   0.0144   1.0000
  13.500   1.6194   0.02670   0.02066  -0.0576   0.0138   1.0000
  13.750   1.6285   0.02787   0.02187  -0.0558   0.0128   1.0000
  14.000   1.6386   0.02897   0.02305  -0.0543   0.0123   1.0000
  14.250   1.6481   0.03013   0.02429  -0.0528   0.0119   1.0000
  14.500   1.6568   0.03140   0.02563  -0.0513   0.0114   1.0000
  14.750   1.6644   0.03280   0.02709  -0.0498   0.0109   1.0000
  15.000   1.6710   0.03432   0.02867  -0.0483   0.0104   1.0000
  15.250   1.6762   0.03600   0.03042  -0.0469   0.0099   1.0000
  15.500   1.6818   0.03770   0.03220  -0.0457   0.0096   1.0000
  15.750   1.6874   0.03945   0.03404  -0.0446   0.0093   1.0000
  16.000   1.6917   0.04137   0.03606  -0.0436   0.0091   1.0000
  16.250   1.6955   0.04343   0.03820  -0.0427   0.0088   1.0000
  16.500   1.6981   0.04569   0.04055  -0.0420   0.0084   1.0000
  16.750   1.6995   0.04817   0.04311  -0.0414   0.0081   1.0000
  17.000   1.6995   0.05089   0.04592  -0.0409   0.0079   1.0000
  17.250   1.6982   0.05389   0.04902  -0.0407   0.0076   1.0000
  17.500   1.6960   0.05714   0.05236  -0.0407   0.0072   1.0000
  17.750   1.6943   0.06045   0.05578  -0.0410   0.0071   1.0000
  18.000   1.6912   0.06405   0.05950  -0.0415   0.0070   1.0000
  18.250   1.6871   0.06794   0.06351  -0.0423   0.0068   1.0000
  18.500   1.6811   0.07228   0.06797  -0.0434   0.0066   1.0000
  18.750   1.6735   0.07702   0.07282  -0.0449   0.0064   1.0000
  19.000   1.6642   0.08216   0.07809  -0.0467   0.0062   1.0000
  19.250   1.6526   0.08789   0.08395  -0.0490   0.0061   1.0000
<< Back to SG6042 (sg6042-il)

Polar data table (+)

Polar graphs


<< Back to SG6042 (sg6042-il)