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FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 78-K-140 A/20 (fx78k140a20-il)
Reynolds number: 200,000
Max Cl/Cd: 57.45 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx78k140a20-il-200000-n5.txt
Download as CSV file: xf-fx78k140a20-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-140 A/20                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1333   0.09290   0.08813  -0.1014   0.7506   0.0148
 -10.250  -0.1325   0.08920   0.08448  -0.1030   0.7494   0.0145
 -10.000  -0.1455   0.08216   0.07754  -0.1059   0.7482   0.0129
  -9.750  -0.1425   0.07905   0.07443  -0.1071   0.7467   0.0112
  -9.500  -0.1425   0.07631   0.07176  -0.1085   0.7452   0.0139
  -9.250  -0.1538   0.07056   0.06608  -0.1116   0.7438   0.0133
  -9.000  -0.1745   0.06320   0.05882  -0.1167   0.7424   0.0129
  -8.750  -0.1804   0.06039   0.05595  -0.1168   0.7412   0.0102
  -8.500  -0.2075   0.05365   0.04913  -0.1162   0.7399   0.0119
  -8.250  -0.2243   0.04929   0.04460  -0.1139   0.7387   0.0119
  -8.000  -0.2382   0.04472   0.03976  -0.1111   0.7377   0.0120
  -7.750  -0.2434   0.04161   0.03645  -0.1084   0.7359   0.0119
  -7.500  -0.2520   0.03733   0.03175  -0.1048   0.7338   0.0122
  -7.000  -0.2455   0.03131   0.02498  -0.0994   0.7307   0.0129
  -6.750  -0.2324   0.02929   0.02263  -0.0975   0.7294   0.0132
  -6.500  -0.2156   0.02771   0.02071  -0.0961   0.7282   0.0137
  -6.250  -0.1963   0.02642   0.01916  -0.0950   0.7270   0.0146
  -6.000  -0.1744   0.02574   0.01825  -0.0942   0.7260   0.0167
  -5.750  -0.1525   0.02422   0.01640  -0.0932   0.7250   0.0178
  -5.500  -0.1291   0.02294   0.01484  -0.0924   0.7243   0.0185
  -5.250  -0.1075   0.02175   0.01349  -0.0915   0.7229   0.0193
  -5.000  -0.0874   0.02088   0.01258  -0.0904   0.7208   0.0212
  -4.750  -0.0655   0.02036   0.01200  -0.0896   0.7189   0.0231
  -4.500  -0.0428   0.01995   0.01147  -0.0889   0.7172   0.0265
  -4.250  -0.0207   0.01945   0.01094  -0.0881   0.7157   0.0315
  -4.000   0.0022   0.01908   0.01051  -0.0873   0.7145   0.0363
  -3.750   0.0253   0.01873   0.01013  -0.0867   0.7134   0.0440
  -3.500   0.0492   0.01842   0.00973  -0.0861   0.7124   0.0524
  -3.250   0.0730   0.01810   0.00939  -0.0855   0.7115   0.0653
  -3.000   0.0972   0.01779   0.00905  -0.0850   0.7106   0.0808
  -2.750   0.1170   0.01772   0.00909  -0.0840   0.7082   0.1004
  -2.500   0.1362   0.01758   0.00915  -0.0829   0.7057   0.1447
  -2.250   0.1546   0.01718   0.00911  -0.0817   0.7035   0.2374
  -2.000   0.1712   0.01663   0.00902  -0.0801   0.7018   0.3698
  -1.750   0.1823   0.01582   0.00892  -0.0771   0.7003   0.5642
  -1.500   0.1999   0.01582   0.00976  -0.0732   0.6992   0.8063
  -1.250   0.2183   0.01595   0.00975  -0.0713   0.6981   0.8450
  -1.000   0.2384   0.01612   0.00983  -0.0692   0.6972   0.8716
  -0.750   0.2558   0.01659   0.01030  -0.0668   0.6944   0.8923
  -0.500   0.2705   0.01705   0.01076  -0.0639   0.6911   0.9146
  -0.250   0.3145   0.01731   0.01097  -0.0664   0.6896   0.9370
   0.000   0.3658   0.01744   0.01100  -0.0712   0.6884   0.9469
   0.250   0.3969   0.01746   0.01094  -0.0722   0.6871   0.9506
   0.500   0.4183   0.01743   0.01085  -0.0712   0.6857   0.9543
   0.750   0.4482   0.01739   0.01075  -0.0719   0.6847   0.9559
   1.000   0.4805   0.01732   0.01061  -0.0731   0.6838   0.9571
   1.250   0.5123   0.01725   0.01048  -0.0742   0.6830   0.9582
   1.500   0.5272   0.01803   0.01135  -0.0732   0.6765   0.9616
   1.750   0.5531   0.01805   0.01135  -0.0732   0.6743   0.9637
   2.000   0.5788   0.01801   0.01131  -0.0731   0.6728   0.9658
   2.250   0.6035   0.01790   0.01117  -0.0727   0.6715   0.9682
   2.500   0.6357   0.01777   0.01102  -0.0738   0.6705   0.9691
   2.750   0.6679   0.01764   0.01088  -0.0750   0.6696   0.9698
   3.250   0.7100   0.01851   0.01191  -0.0744   0.6600   0.9741
   3.500   0.7389   0.01839   0.01181  -0.0749   0.6585   0.9752
   3.750   0.7678   0.01821   0.01165  -0.0753   0.6573   0.9762
   4.000   0.7978   0.01799   0.01148  -0.0758   0.6562   0.9771
   4.500   0.8372   0.01884   0.01251  -0.0747   0.6459   0.9821
   4.750   0.8682   0.01864   0.01237  -0.0755   0.6444   0.9830
   5.000   0.8999   0.01838   0.01219  -0.0763   0.6432   0.9837
   5.500   0.9399   0.01920   0.01325  -0.0754   0.6324   0.9895
   5.750   0.9717   0.01892   0.01306  -0.0763   0.6307   0.9904
   6.000   0.9981   0.01903   0.01329  -0.0767   0.6266   0.9925
   6.250   1.0001   0.01965   0.01402  -0.0730   0.6191   1.0000
   6.500   1.0226   0.01937   0.01386  -0.0719   0.6169   1.0000
   6.750   1.0512   0.01895   0.01355  -0.0719   0.6152   1.0000
   7.000   1.0212   0.02032   0.01496  -0.0632   0.6035   1.0000
   7.500   1.0303   0.02200   0.01681  -0.0583   0.5809   1.0000
   7.750   1.0807   0.01881   0.01344  -0.0587   0.5299   1.0000
   8.000   1.0841   0.01896   0.01276  -0.0543   0.4231   1.0000
   8.250   1.0642   0.02154   0.01484  -0.0497   0.3531   1.0000
   8.500   1.0547   0.02378   0.01683  -0.0465   0.3005   1.0000
   8.750   1.0324   0.02698   0.01944  -0.0424   0.2198   1.0000
   9.000   1.0177   0.02985   0.02187  -0.0392   0.1471   1.0000
   9.250   1.0036   0.03280   0.02431  -0.0362   0.0718   1.0000
   9.500   0.9945   0.03553   0.02668  -0.0337   0.0235   1.0000
   9.750   1.0038   0.03699   0.02820  -0.0327   0.0190   1.0000
  10.000   1.0087   0.03889   0.03015  -0.0313   0.0137   1.0000
  10.250   1.0188   0.04039   0.03175  -0.0305   0.0122   1.0000
  10.500   1.0277   0.04202   0.03350  -0.0296   0.0114   1.0000
  10.750   1.0356   0.04378   0.03539  -0.0287   0.0106   1.0000
  11.000   1.0418   0.04572   0.03743  -0.0277   0.0097   1.0000
  11.250   1.0476   0.04771   0.03953  -0.0268   0.0093   1.0000
  11.500   1.0507   0.04997   0.04188  -0.0258   0.0088   1.0000
  11.750   1.0528   0.05235   0.04435  -0.0246   0.0084   1.0000
  12.250   1.0618   0.05659   0.04879  -0.0221   0.0079   1.0000
  12.500   1.0724   0.05819   0.05050  -0.0214   0.0076   1.0000
  12.750   1.0823   0.05978   0.05218  -0.0202   0.0075   1.0000
  13.000   1.0918   0.06171   0.05423  -0.0204   0.0058   1.0000
  13.250   1.1023   0.06330   0.05593  -0.0193   0.0060   1.0000
  13.500   1.1108   0.06518   0.05792  -0.0184   0.0056   1.0000
  13.750   1.1196   0.06707   0.05991  -0.0177   0.0054   1.0000
  14.000   1.1273   0.06912   0.06207  -0.0170   0.0052   1.0000
  14.250   1.1362   0.07118   0.06431  -0.0161   0.0052   1.0000
  14.500   1.1406   0.07387   0.06713  -0.0149   0.0049   1.0000
  14.750   1.1461   0.07635   0.06983  -0.0147   0.0051   1.0000
  15.000   1.1410   0.08056   0.07430  -0.0135   0.0047   1.0000
  15.250   1.1442   0.08334   0.07725  -0.0136   0.0049   1.0000
  15.500   1.1353   0.08811   0.08231  -0.0133   0.0048   1.0000
  15.750   1.1249   0.09302   0.08752  -0.0140   0.0047   1.0000
  16.000   1.1173   0.09759   0.09228  -0.0146   0.0048   1.0000
  16.500   1.0967   0.10805   0.10316  -0.0174   0.0048   1.0000
  16.750   1.0811   0.11462   0.10998  -0.0199   0.0048   1.0000
  17.250   1.0679   0.12508   0.12080  -0.0247   0.0050   1.0000
  17.500   1.0483   0.13316   0.12907  -0.0286   0.0049   1.0000
  17.750   1.0313   0.14136   0.13746  -0.0331   0.0049   1.0000
  18.000   1.0180   0.14940   0.14568  -0.0380   0.0049   1.0000
  18.250   1.0066   0.15818   0.15471  -0.0436   0.0052   1.0000
  18.500   0.9899   0.16815   0.16477  -0.0498   0.0050   1.0000
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