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GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 595 AIRFOIL (goe595-il)
Reynolds number: 500,000
Max Cl/Cd: 86.83 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe595-il-500000-n5.txt
Download as CSV file: xf-goe595-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 595 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4093   0.09245   0.09022  -0.0355   1.0000   0.0063
  -9.250  -0.4167   0.08862   0.08644  -0.0357   1.0000   0.0062
  -9.000  -0.4226   0.08456   0.08241  -0.0369   0.9996   0.0062
  -8.750  -0.4163   0.07848   0.07635  -0.0432   0.9964   0.0063
  -8.500  -0.4114   0.07230   0.07018  -0.0503   0.9910   0.0064
  -8.250  -0.4072   0.06379   0.06167  -0.0623   0.9821   0.0064
  -8.000  -0.4009   0.05272   0.05045  -0.0750   0.9740   0.0065
  -7.750  -0.4167   0.03225   0.02918  -0.0842   0.9628   0.0064
  -7.500  -0.4144   0.02244   0.01825  -0.0842   0.9555   0.0068
  -7.250  -0.3927   0.01918   0.01443  -0.0842   0.9520   0.0072
  -7.000  -0.3715   0.01739   0.01227  -0.0834   0.9466   0.0075
  -6.750  -0.3451   0.01599   0.01059  -0.0835   0.9431   0.0078
  -6.500  -0.3168   0.01474   0.00915  -0.0841   0.9404   0.0084
  -6.250  -0.2899   0.01413   0.00844  -0.0841   0.9358   0.0088
  -6.000  -0.2627   0.01355   0.00776  -0.0841   0.9305   0.0094
  -5.750  -0.2318   0.01314   0.00726  -0.0849   0.9263   0.0105
  -5.500  -0.2056   0.01255   0.00652  -0.0846   0.9204   0.0112
  -5.250  -0.1798   0.01174   0.00561  -0.0843   0.9146   0.0123
  -5.000  -0.1507   0.01140   0.00522  -0.0847   0.9101   0.0135
  -4.750  -0.1253   0.01112   0.00490  -0.0842   0.9034   0.0150
  -4.500  -0.0970   0.01085   0.00453  -0.0842   0.8977   0.0165
  -4.250  -0.0723   0.01039   0.00403  -0.0836   0.8909   0.0185
  -4.000  -0.0455   0.01011   0.00370  -0.0834   0.8843   0.0208
  -3.750  -0.0191   0.00992   0.00346  -0.0831   0.8771   0.0237
  -3.500   0.0079   0.00976   0.00321  -0.0828   0.8688   0.0252
  -3.250   0.0326   0.00939   0.00278  -0.0821   0.8599   0.0283
  -3.000   0.0591   0.00916   0.00249  -0.0818   0.8527   0.0315
  -2.750   0.0850   0.00900   0.00226  -0.0814   0.8452   0.0337
  -2.500   0.1118   0.00886   0.00206  -0.0811   0.8382   0.0361
  -2.250   0.1379   0.00872   0.00189  -0.0807   0.8294   0.0398
  -2.000   0.1638   0.00855   0.00174  -0.0803   0.8199   0.0510
  -1.750   0.1895   0.00840   0.00162  -0.0798   0.8077   0.0819
  -1.500   0.2150   0.00824   0.00150  -0.0793   0.7946   0.1079
  -1.250   0.2401   0.00807   0.00141  -0.0787   0.7802   0.1518
  -1.000   0.2647   0.00790   0.00133  -0.0781   0.7645   0.2059
  -0.750   0.2889   0.00772   0.00128  -0.0774   0.7480   0.2721
  -0.500   0.3130   0.00754   0.00123  -0.0767   0.7327   0.3351
  -0.250   0.3348   0.00720   0.00122  -0.0756   0.7164   0.4726
   0.250   0.3784   0.00687   0.00124  -0.0731   0.6777   0.6370
   0.500   0.3966   0.00660   0.00129  -0.0709   0.6561   0.7584
   0.750   0.4354   0.00642   0.00147  -0.0729   0.6271   0.9321
   1.000   0.4899   0.00669   0.00157  -0.0788   0.5883   0.9720
   1.250   0.5235   0.00697   0.00166  -0.0802   0.5504   0.9847
   1.500   0.5618   0.00724   0.00176  -0.0827   0.5157   0.9946
   1.750   0.5983   0.00747   0.00184  -0.0849   0.4905   1.0000
   2.000   0.6194   0.00764   0.00192  -0.0835   0.4727   1.0000
   2.250   0.6409   0.00780   0.00201  -0.0823   0.4579   1.0000
   2.500   0.6619   0.00800   0.00213  -0.0809   0.4391   1.0000
   2.750   0.6834   0.00818   0.00224  -0.0797   0.4234   1.0000
   3.000   0.7052   0.00836   0.00236  -0.0785   0.4085   1.0000
   3.250   0.7275   0.00852   0.00249  -0.0774   0.3964   1.0000
   3.500   0.7497   0.00869   0.00262  -0.0763   0.3830   1.0000
   3.750   0.7712   0.00891   0.00276  -0.0751   0.3618   1.0000
   4.000   0.7928   0.00913   0.00293  -0.0739   0.3402   1.0000
   4.250   0.8136   0.00940   0.00310  -0.0726   0.3123   1.0000
   4.500   0.8335   0.00974   0.00330  -0.0711   0.2809   1.0000
   4.750   0.8525   0.01016   0.00357  -0.0695   0.2501   1.0000
   5.000   0.8722   0.01054   0.00385  -0.0680   0.2280   1.0000
   5.250   0.8931   0.01086   0.00412  -0.0668   0.2123   1.0000
   5.500   0.9144   0.01116   0.00438  -0.0656   0.1989   1.0000
   5.750   0.9358   0.01146   0.00465  -0.0645   0.1813   1.0000
   6.000   0.9533   0.01205   0.00502  -0.0627   0.1337   1.0000
   6.250   0.9621   0.01332   0.00582  -0.0596   0.0515   1.0000
   6.500   0.9822   0.01374   0.00623  -0.0583   0.0436   1.0000
   6.750   1.0031   0.01409   0.00662  -0.0571   0.0390   1.0000
   7.000   1.0236   0.01447   0.00702  -0.0559   0.0350   1.0000
   7.250   1.0430   0.01492   0.00748  -0.0545   0.0304   1.0000
   7.500   1.0640   0.01523   0.00786  -0.0534   0.0267   1.0000
   7.750   1.0829   0.01570   0.00832  -0.0519   0.0208   1.0000
   8.000   1.1017   0.01615   0.00879  -0.0505   0.0167   1.0000
   8.250   1.1189   0.01670   0.00934  -0.0488   0.0129   1.0000
   8.500   1.1355   0.01721   0.00991  -0.0469   0.0113   1.0000
   8.750   1.1498   0.01781   0.01053  -0.0447   0.0099   1.0000
   9.000   1.1621   0.01853   0.01132  -0.0421   0.0090   1.0000
   9.250   1.1759   0.01914   0.01205  -0.0398   0.0085   1.0000
   9.500   1.1894   0.01977   0.01276  -0.0376   0.0078   1.0000
   9.750   1.2026   0.02043   0.01347  -0.0355   0.0071   1.0000
  10.000   1.2134   0.02125   0.01436  -0.0331   0.0067   1.0000
  10.250   1.2206   0.02232   0.01551  -0.0302   0.0062   1.0000
  10.500   1.2308   0.02320   0.01650  -0.0279   0.0060   1.0000
  10.750   1.2397   0.02418   0.01759  -0.0256   0.0057   1.0000
  11.000   1.2466   0.02533   0.01885  -0.0231   0.0055   1.0000
  11.250   1.2540   0.02648   0.02010  -0.0208   0.0052   1.0000
  11.500   1.2604   0.02774   0.02146  -0.0187   0.0051   1.0000
  11.750   1.2654   0.02916   0.02298  -0.0165   0.0049   1.0000
  12.000   1.2708   0.03059   0.02453  -0.0146   0.0047   1.0000
  12.250   1.2736   0.03230   0.02636  -0.0127   0.0047   1.0000
  12.500   1.2773   0.03400   0.02816  -0.0111   0.0045   1.0000
  12.750   1.2779   0.03606   0.03033  -0.0095   0.0044   1.0000
  13.000   1.2707   0.03899   0.03338  -0.0078   0.0042   1.0000
  13.250   1.2723   0.04121   0.03574  -0.0068   0.0041   1.0000
  13.500   1.2735   0.04357   0.03823  -0.0061   0.0041   1.0000
  13.750   1.2696   0.04660   0.04142  -0.0054   0.0040   1.0000
  14.000   1.2691   0.04938   0.04437  -0.0052   0.0038   1.0000
  14.250   1.2689   0.05226   0.04739  -0.0053   0.0036   1.0000
  14.500   1.2622   0.05609   0.05138  -0.0056   0.0036   1.0000
  14.750   1.2584   0.05974   0.05517  -0.0063   0.0035   1.0000
  15.000   1.2511   0.06407   0.05965  -0.0073   0.0034   1.0000
  15.250   1.2459   0.06827   0.06400  -0.0087   0.0034   1.0000
  15.500   1.2325   0.07387   0.06978  -0.0104   0.0034   1.0000
  15.750   1.2240   0.07895   0.07502  -0.0125   0.0033   1.0000
  16.000   1.2138   0.08450   0.08072  -0.0148   0.0033   1.0000
  16.250   1.2072   0.08956   0.08588  -0.0172   0.0032   1.0000
  16.500   1.1892   0.09675   0.09327  -0.0204   0.0033   1.0000
  16.750   1.1807   0.10250   0.09913  -0.0233   0.0032   1.0000
  17.000   1.1572   0.11122   0.10806  -0.0274   0.0033   1.0000
  17.250   1.1484   0.11745   0.11439  -0.0308   0.0032   1.0000
  17.500   1.1326   0.12530   0.12239  -0.0350   0.0032   1.0000
  17.750   1.1172   0.13338   0.13062  -0.0394   0.0032   1.0000
  18.000   1.0967   0.14293   0.14031  -0.0447   0.0033   1.0000
  18.250   1.0788   0.15223   0.14974  -0.0500   0.0033   1.0000
  18.500   1.0522   0.16458   0.16225  -0.0569   0.0034   1.0000
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