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Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf)
Reynolds number: 500,000
Max Cl/Cd: 58.22 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk0009-jf-500000.txt
Download as CSV file: xf-joukowsk0009-jf-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=9%                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.9955   0.07812   0.07551   0.0078   1.0000   0.0151
 -13.000  -1.0333   0.06592   0.06310  -0.0017   1.0000   0.0148
 -12.750  -1.0612   0.05705   0.05400  -0.0087   1.0000   0.0147
 -12.500  -1.0895   0.04945   0.04613  -0.0141   1.0000   0.0145
 -12.250  -1.1028   0.04517   0.04167  -0.0162   1.0000   0.0146
 -12.000  -1.1171   0.04158   0.03789  -0.0166   1.0000   0.0146
 -11.750  -1.1277   0.03895   0.03506  -0.0149   1.0000   0.0148
 -11.500  -1.1280   0.03641   0.03230  -0.0138   1.0000   0.0150
 -11.250  -1.1217   0.03415   0.02981  -0.0128   1.0000   0.0153
 -11.000  -1.1111   0.03219   0.02763  -0.0120   1.0000   0.0157
 -10.750  -1.0968   0.03054   0.02576  -0.0112   1.0000   0.0162
 -10.500  -1.0802   0.02907   0.02407  -0.0105   1.0000   0.0165
 -10.250  -1.0672   0.02640   0.02111  -0.0097   1.0000   0.0169
 -10.000  -1.0515   0.02416   0.01872  -0.0089   1.0000   0.0175
  -9.750  -1.0310   0.02297   0.01746  -0.0084   1.0000   0.0181
  -9.500  -1.0091   0.02198   0.01637  -0.0079   1.0000   0.0188
  -9.250  -0.9867   0.02099   0.01527  -0.0074   1.0000   0.0196
  -9.000  -0.9638   0.02003   0.01420  -0.0069   1.0000   0.0205
  -8.750  -0.9397   0.01927   0.01332  -0.0065   1.0000   0.0213
  -8.500  -0.9188   0.01772   0.01166  -0.0059   1.0000   0.0226
  -8.250  -0.8945   0.01700   0.01092  -0.0056   1.0000   0.0240
  -8.000  -0.8694   0.01637   0.01024  -0.0053   1.0000   0.0255
  -7.750  -0.8439   0.01578   0.00956  -0.0050   1.0000   0.0269
  -7.500  -0.8201   0.01476   0.00846  -0.0045   1.0000   0.0287
  -7.250  -0.7949   0.01407   0.00776  -0.0043   1.0000   0.0311
  -7.000  -0.7685   0.01364   0.00729  -0.0041   1.0000   0.0337
  -6.750  -0.7428   0.01296   0.00655  -0.0038   1.0000   0.0367
  -6.500  -0.7167   0.01241   0.00601  -0.0036   1.0000   0.0407
  -6.250  -0.6899   0.01201   0.00556  -0.0034   1.0000   0.0448
  -6.000  -0.6636   0.01143   0.00500  -0.0032   1.0000   0.0518
  -5.750  -0.6369   0.01094   0.00453  -0.0030   1.0000   0.0598
  -5.500  -0.6100   0.01051   0.00413  -0.0029   1.0000   0.0708
  -5.250  -0.5832   0.01007   0.00376  -0.0028   1.0000   0.0863
  -5.000  -0.5562   0.00967   0.00344  -0.0027   1.0000   0.1060
  -4.750  -0.5293   0.00925   0.00315  -0.0026   1.0000   0.1322
  -4.500  -0.5023   0.00886   0.00289  -0.0025   1.0000   0.1626
  -4.250  -0.4753   0.00847   0.00265  -0.0025   1.0000   0.1965
  -4.000  -0.4482   0.00813   0.00246  -0.0024   1.0000   0.2310
  -3.750  -0.4211   0.00781   0.00228  -0.0023   1.0000   0.2664
  -3.500  -0.3940   0.00751   0.00212  -0.0022   1.0000   0.3029
  -3.250  -0.3669   0.00726   0.00200  -0.0021   1.0000   0.3380
  -3.000  -0.3399   0.00701   0.00189  -0.0019   1.0000   0.3720
  -2.750  -0.3133   0.00679   0.00181  -0.0017   1.0000   0.4059
  -2.500  -0.2795   0.00660   0.00174  -0.0030   0.9882   0.4417
  -2.250  -0.2411   0.00644   0.00170  -0.0052   0.9660   0.4771
  -2.000  -0.2083   0.00632   0.00166  -0.0059   0.9383   0.5092
  -1.750  -0.1825   0.00625   0.00162  -0.0051   0.9078   0.5378
  -1.500  -0.1579   0.00621   0.00158  -0.0040   0.8789   0.5655
  -1.250  -0.1327   0.00617   0.00155  -0.0030   0.8515   0.5926
  -1.000  -0.1067   0.00613   0.00151  -0.0023   0.8247   0.6191
  -0.750  -0.0803   0.00611   0.00148  -0.0016   0.7987   0.6453
  -0.500  -0.0537   0.00610   0.00146  -0.0010   0.7732   0.6713
  -0.250  -0.0269   0.00609   0.00145  -0.0005   0.7477   0.6970
   0.000   0.0000   0.00608   0.00145   0.0000   0.7223   0.7222
   0.250   0.0269   0.00609   0.00145   0.0005   0.6970   0.7478
   0.500   0.0537   0.00610   0.00146   0.0010   0.6713   0.7733
   0.750   0.0803   0.00611   0.00148   0.0016   0.6453   0.7987
   1.000   0.1067   0.00613   0.00151   0.0023   0.6192   0.8247
   1.250   0.1327   0.00617   0.00155   0.0030   0.5926   0.8515
   1.500   0.1579   0.00621   0.00158   0.0040   0.5655   0.8789
   1.750   0.1825   0.00625   0.00162   0.0051   0.5378   0.9078
   2.000   0.2083   0.00632   0.00166   0.0059   0.5092   0.9383
   2.250   0.2411   0.00644   0.00170   0.0052   0.4770   0.9660
   2.500   0.2796   0.00660   0.00174   0.0030   0.4416   0.9881
   2.750   0.3134   0.00679   0.00181   0.0017   0.4059   1.0000
   3.000   0.3400   0.00701   0.00189   0.0019   0.3721   1.0000
   3.250   0.3669   0.00726   0.00200   0.0021   0.3380   1.0000
   3.500   0.3940   0.00751   0.00213   0.0022   0.3028   1.0000
   3.750   0.4211   0.00781   0.00228   0.0023   0.2665   1.0000
   4.000   0.4483   0.00813   0.00246   0.0024   0.2309   1.0000
   4.250   0.4754   0.00847   0.00265   0.0024   0.1965   1.0000
   4.500   0.5023   0.00886   0.00289   0.0025   0.1625   1.0000
   4.750   0.5293   0.00925   0.00315   0.0026   0.1322   1.0000
   5.000   0.5562   0.00967   0.00344   0.0027   0.1060   1.0000
   5.250   0.5832   0.01007   0.00376   0.0028   0.0863   1.0000
   5.500   0.6100   0.01051   0.00413   0.0029   0.0709   1.0000
   5.750   0.6369   0.01094   0.00453   0.0031   0.0598   1.0000
   6.000   0.6635   0.01143   0.00500   0.0032   0.0518   1.0000
   6.250   0.6897   0.01202   0.00557   0.0034   0.0447   1.0000
   6.500   0.7165   0.01241   0.00601   0.0036   0.0407   1.0000
   6.750   0.7425   0.01296   0.00655   0.0039   0.0367   1.0000
   7.000   0.7681   0.01364   0.00729   0.0042   0.0337   1.0000
   7.250   0.7944   0.01407   0.00776   0.0044   0.0311   1.0000
   7.500   0.8197   0.01474   0.00844   0.0046   0.0288   1.0000
   7.750   0.8434   0.01576   0.00954   0.0051   0.0269   1.0000
   8.000   0.8687   0.01636   0.01022   0.0054   0.0255   1.0000
   8.250   0.8936   0.01698   0.01090   0.0058   0.0241   1.0000
   8.500   0.9178   0.01770   0.01165   0.0061   0.0227   1.0000
   8.750   0.9385   0.01927   0.01332   0.0067   0.0213   1.0000
   9.000   0.9627   0.02002   0.01419   0.0071   0.0205   1.0000
   9.250   0.9858   0.02097   0.01526   0.0076   0.0196   1.0000
   9.500   1.0084   0.02198   0.01637   0.0080   0.0189   1.0000
   9.750   1.0304   0.02298   0.01747   0.0085   0.0182   1.0000
  10.000   1.0512   0.02415   0.01872   0.0089   0.0176   1.0000
  10.250   1.0671   0.02641   0.02113   0.0097   0.0169   1.0000
  10.500   1.0797   0.02918   0.02418   0.0105   0.0165   1.0000
  10.750   1.0971   0.03045   0.02566   0.0112   0.0162   1.0000
  11.000   1.1114   0.03210   0.02753   0.0120   0.0157   1.0000
  11.250   1.1219   0.03409   0.02975   0.0128   0.0153   1.0000
  11.500   1.1280   0.03638   0.03227   0.0138   0.0149   1.0000
  11.750   1.1283   0.03885   0.03496   0.0149   0.0147   1.0000
  12.000   1.1167   0.04165   0.03796   0.0166   0.0146   1.0000
  12.250   1.1010   0.04541   0.04193   0.0161   0.0146   1.0000
  12.500   1.0846   0.05018   0.04690   0.0136   0.0146   1.0000
  12.750   1.0679   0.05596   0.05287   0.0095   0.0145   1.0000
  13.000   1.0337   0.06596   0.06313   0.0016   0.0148   1.0000
  13.250   0.9943   0.07856   0.07595  -0.0082   0.0151   1.0000
  13.500   0.8425   0.12265   0.12039  -0.0360   0.0171   1.0000
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