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FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 61-147 AIRFOIL (fx61147-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.9 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61147-il-1000000.txt
Download as CSV file: xf-fx61147-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-147 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2650   0.09807   0.09661  -0.0485   0.9974   0.0102
 -11.000  -0.4558   0.04537   0.04371  -0.0669   0.9981   0.0063
 -10.750  -0.4688   0.03816   0.03640  -0.0731   0.9966   0.0061
 -10.500  -0.4973   0.02954   0.02754  -0.0796   0.9940   0.0060
 -10.250  -0.5433   0.04800   0.04605  -0.0760   0.9956   0.0061
 -10.000  -0.6042   0.03211   0.02928  -0.0876   0.9832   0.0058
  -9.750  -0.5959   0.02598   0.02253  -0.0911   0.9773   0.0061
  -9.500  -0.5680   0.02356   0.01982  -0.0938   0.9755   0.0063
  -9.250  -0.5466   0.02256   0.01867  -0.0937   0.9691   0.0064
  -9.000  -0.5256   0.01875   0.01442  -0.0952   0.9654   0.0067
  -8.750  -0.4937   0.01761   0.01320  -0.0972   0.9634   0.0070
  -8.500  -0.4707   0.01672   0.01223  -0.0969   0.9566   0.0072
  -8.250  -0.4405   0.01603   0.01147  -0.0980   0.9526   0.0075
  -8.000  -0.4070   0.01511   0.01047  -0.0998   0.9499   0.0077
  -7.750  -0.3791   0.01431   0.00959  -0.1003   0.9425   0.0080
  -7.500  -0.3420   0.01350   0.00870  -0.1028   0.9382   0.0084
  -7.250  -0.3032   0.01281   0.00793  -0.1055   0.9322   0.0089
  -7.000  -0.2627   0.01177   0.00678  -0.1091   0.9243   0.0097
  -6.750  -0.2171   0.01131   0.00630  -0.1133   0.9161   0.0107
  -6.500  -0.1687   0.01085   0.00575  -0.1182   0.9058   0.0119
  -6.250  -0.1301   0.01025   0.00503  -0.1210   0.8901   0.0131
  -6.000  -0.0980   0.00988   0.00457  -0.1224   0.8708   0.0145
  -5.750  -0.0685   0.00968   0.00428  -0.1229   0.8498   0.0161
  -5.500  -0.0419   0.00939   0.00385  -0.1229   0.8263   0.0178
  -5.250  -0.0166   0.00922   0.00358  -0.1226   0.8023   0.0202
  -5.000   0.0088   0.00913   0.00337  -0.1222   0.7791   0.0220
  -4.750   0.0341   0.00891   0.00304  -0.1219   0.7579   0.0258
  -4.500   0.0602   0.00880   0.00285  -0.1216   0.7375   0.0299
  -4.250   0.0865   0.00856   0.00260  -0.1216   0.7174   0.0481
  -3.750   0.1432   0.00750   0.00205  -0.1233   0.6813   0.2369
  -3.500   0.1753   0.00672   0.00176  -0.1253   0.6656   0.4046
  -3.250   0.2059   0.00640   0.00164  -0.1263   0.6510   0.4973
  -3.000   0.2350   0.00632   0.00161  -0.1268   0.6370   0.5446
  -2.750   0.2636   0.00633   0.00162  -0.1270   0.6239   0.5744
  -2.500   0.2921   0.00638   0.00165  -0.1271   0.6116   0.6008
  -2.250   0.3204   0.00647   0.00170  -0.1272   0.6002   0.6184
  -2.000   0.3484   0.00658   0.00176  -0.1272   0.5891   0.6313
  -1.500   0.4047   0.00678   0.00185  -0.1273   0.5690   0.6463
  -1.250   0.4328   0.00689   0.00188  -0.1273   0.5603   0.6514
  -1.000   0.4612   0.00699   0.00190  -0.1274   0.5512   0.6558
  -0.750   0.4893   0.00705   0.00194  -0.1275   0.5431   0.6594
  -0.500   0.5171   0.00715   0.00200  -0.1275   0.5351   0.6629
  -0.250   0.5456   0.00723   0.00204  -0.1276   0.5281   0.6666
   0.000   0.5737   0.00734   0.00208  -0.1278   0.5205   0.6699
   0.250   0.6019   0.00740   0.00212  -0.1279   0.5136   0.6729
   0.500   0.6297   0.00749   0.00219  -0.1279   0.5066   0.6757
   0.750   0.6576   0.00758   0.00226  -0.1279   0.5001   0.6787
   1.000   0.6857   0.00768   0.00232  -0.1280   0.4931   0.6816
   1.250   0.7136   0.00778   0.00238  -0.1281   0.4864   0.6843
   1.500   0.7418   0.00785   0.00243  -0.1283   0.4800   0.6868
   1.750   0.7690   0.00796   0.00252  -0.1282   0.4736   0.6891
   2.000   0.7972   0.00803   0.00260  -0.1283   0.4683   0.6914
   2.250   0.8248   0.00813   0.00269  -0.1283   0.4624   0.6939
   2.500   0.8524   0.00824   0.00278  -0.1284   0.4568   0.6965
   2.750   0.8805   0.00833   0.00286  -0.1285   0.4509   0.6988
   3.000   0.9078   0.00846   0.00296  -0.1285   0.4452   0.7010
   3.250   0.9356   0.00852   0.00305  -0.1286   0.4402   0.7031
   3.500   0.9630   0.00861   0.00316  -0.1286   0.4347   0.7051
   3.750   0.9896   0.00876   0.00329  -0.1284   0.4289   0.7072
   4.000   1.0174   0.00884   0.00340  -0.1285   0.4235   0.7094
   4.250   1.0444   0.00897   0.00352  -0.1285   0.4177   0.7116
   4.500   1.0715   0.00910   0.00365  -0.1284   0.4125   0.7136
   4.750   1.0989   0.00921   0.00378  -0.1285   0.4063   0.7154
   5.000   1.1250   0.00935   0.00391  -0.1283   0.3988   0.7175
   5.250   1.1520   0.00945   0.00404  -0.1282   0.3905   0.7194
   5.500   1.1781   0.00961   0.00420  -0.1280   0.3813   0.7212
   5.750   1.2039   0.00978   0.00436  -0.1278   0.3718   0.7232
   6.000   1.2303   0.00993   0.00453  -0.1276   0.3634   0.7253
   6.250   1.2556   0.01014   0.00471  -0.1273   0.3521   0.7273
   6.500   1.2804   0.01039   0.00492  -0.1270   0.3367   0.7290
   6.750   1.3045   0.01068   0.00514  -0.1265   0.3177   0.7309
   7.000   1.3276   0.01100   0.00540  -0.1258   0.2989   0.7328
   7.250   1.3502   0.01136   0.00569  -0.1251   0.2793   0.7347
   7.500   1.3722   0.01176   0.00603  -0.1242   0.2583   0.7366
   7.750   1.3923   0.01229   0.00644  -0.1230   0.2325   0.7387
   8.000   1.4108   0.01290   0.00691  -0.1216   0.2041   0.7406
   8.250   1.4252   0.01376   0.00754  -0.1196   0.1655   0.7426
   8.500   1.4367   0.01474   0.00829  -0.1171   0.1285   0.7444
   8.750   1.4470   0.01559   0.00899  -0.1142   0.0994   0.7464
   9.000   1.4557   0.01643   0.00971  -0.1111   0.0756   0.7483
   9.250   1.4639   0.01731   0.01048  -0.1080   0.0558   0.7502
   9.500   1.4731   0.01814   0.01124  -0.1051   0.0407   0.7523
   9.750   1.4816   0.01900   0.01205  -0.1022   0.0294   0.7545
  10.000   1.4907   0.01985   0.01288  -0.0995   0.0220   0.7566
  10.250   1.4984   0.02078   0.01379  -0.0968   0.0155   0.7584
  10.500   1.5035   0.02188   0.01487  -0.0937   0.0087   0.7602
  10.750   1.5073   0.02310   0.01611  -0.0907   0.0048   0.7623
  11.000   1.5152   0.02414   0.01723  -0.0884   0.0042   0.7645
  11.250   1.5218   0.02531   0.01847  -0.0862   0.0038   0.7667
  11.500   1.5273   0.02662   0.01987  -0.0839   0.0035   0.7690
  11.750   1.5322   0.02806   0.02139  -0.0819   0.0033   0.7712
  12.000   1.5378   0.02954   0.02295  -0.0801   0.0032   0.7732
  12.250   1.5424   0.03119   0.02469  -0.0785   0.0031   0.7753
  12.500   1.5459   0.03302   0.02662  -0.0770   0.0030   0.7775
  12.750   1.5483   0.03506   0.02877  -0.0757   0.0030   0.7799
  13.000   1.5500   0.03731   0.03111  -0.0747   0.0029   0.7824
  13.250   1.5506   0.03979   0.03369  -0.0738   0.0028   0.7849
  13.500   1.5505   0.04249   0.03649  -0.0732   0.0027   0.7872
  13.750   1.5494   0.04543   0.03955  -0.0728   0.0027   0.7894
  14.000   1.5474   0.04862   0.04285  -0.0726   0.0026   0.7918
  14.250   1.5444   0.05207   0.04643  -0.0727   0.0026   0.7942
  14.500   1.5404   0.05578   0.05024  -0.0730   0.0025   0.7966
  14.750   1.5350   0.05980   0.05438  -0.0735   0.0025   0.7990
  15.000   1.5286   0.06411   0.05881  -0.0742   0.0024   0.8014
  15.250   1.5217   0.06864   0.06345  -0.0752   0.0024   0.8037
  15.500   1.5134   0.07352   0.06846  -0.0764   0.0023   0.8061
  15.750   1.5048   0.07860   0.07367  -0.0778   0.0023   0.8086
  16.000   1.4939   0.08419   0.07939  -0.0796   0.0022   0.8110
  16.250   1.4825   0.09000   0.08534  -0.0815   0.0022   0.8134
  16.500   1.4724   0.09577   0.09123  -0.0836   0.0022   0.8157
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