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GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 613 AIRFOIL (goe613-il)
Reynolds number: 200,000
Max Cl/Cd: 67.87 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe613-il-200000-n5.txt
Download as CSV file: xf-goe613-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 613 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3298   0.10109   0.09766  -0.0338   1.0000   0.0237
  -9.000  -0.3357   0.09861   0.09523  -0.0331   1.0000   0.0247
  -8.750  -0.3433   0.09619   0.09287  -0.0319   1.0000   0.0245
  -8.500  -0.3363   0.09191   0.08861  -0.0355   0.9973   0.0243
  -8.250  -0.3262   0.08728   0.08398  -0.0403   0.9929   0.0242
  -8.000  -0.3169   0.08250   0.07921  -0.0457   0.9874   0.0244
  -7.750  -0.3102   0.07761   0.07433  -0.0517   0.9795   0.0248
  -7.500  -0.2993   0.06759   0.06422  -0.0670   0.9680   0.0265
  -7.250  -0.2856   0.06031   0.05680  -0.0747   0.9612   0.0270
  -7.000  -0.2692   0.05874   0.05523  -0.0754   0.9560   0.0278
  -6.750  -0.2469   0.05464   0.05101  -0.0797   0.9519   0.0284
  -6.500  -0.2288   0.05161   0.04788  -0.0818   0.9447   0.0296
  -6.250  -0.2044   0.04709   0.04312  -0.0858   0.9395   0.0316
  -6.000  -0.1814   0.04169   0.03739  -0.0891   0.9340   0.0322
  -5.750  -0.1612   0.03672   0.03197  -0.0904   0.9266   0.0333
  -5.500  -0.1331   0.03241   0.02699  -0.0920   0.9225   0.0350
  -5.250  -0.1151   0.02928   0.02354  -0.0915   0.9147   0.0354
  -5.000  -0.0885   0.02697   0.02098  -0.0923   0.9098   0.0360
  -4.750  -0.0565   0.02568   0.01959  -0.0939   0.9065   0.0372
  -4.500  -0.0346   0.02453   0.01827  -0.0930   0.8977   0.0384
  -4.250  -0.0042   0.02269   0.01610  -0.0937   0.8927   0.0389
  -4.000   0.0201   0.02127   0.01440  -0.0931   0.8851   0.0393
  -3.750   0.0487   0.01997   0.01283  -0.0932   0.8794   0.0398
  -3.500   0.0767   0.01890   0.01152  -0.0931   0.8733   0.0403
  -3.250   0.1034   0.01801   0.01044  -0.0928   0.8659   0.0409
  -3.000   0.1329   0.01731   0.00957  -0.0929   0.8594   0.0425
  -2.750   0.1602   0.01661   0.00870  -0.0926   0.8495   0.0433
  -2.500   0.1869   0.01590   0.00786  -0.0921   0.8375   0.0436
  -2.250   0.2143   0.01527   0.00712  -0.0917   0.8252   0.0440
  -2.000   0.2419   0.01472   0.00647  -0.0914   0.8141   0.0445
  -1.750   0.2696   0.01426   0.00593  -0.0912   0.8035   0.0451
  -1.500   0.2948   0.01367   0.00531  -0.0905   0.7915   0.0459
  -1.250   0.3204   0.01318   0.00480  -0.0899   0.7793   0.0472
  -1.000   0.3463   0.01284   0.00443  -0.0894   0.7664   0.0486
  -0.750   0.3725   0.01260   0.00414  -0.0889   0.7529   0.0509
  -0.500   0.3984   0.01242   0.00388  -0.0884   0.7384   0.0538
  -0.250   0.4240   0.01227   0.00364  -0.0878   0.7235   0.0559
   0.000   0.4492   0.01214   0.00342  -0.0871   0.7073   0.0580
   0.250   0.4738   0.01201   0.00322  -0.0862   0.6899   0.0628
   0.500   0.4983   0.01195   0.00309  -0.0854   0.6711   0.0700
   0.750   0.5214   0.01175   0.00302  -0.0844   0.6507   0.1265
   1.000   0.6074   0.00983   0.00322  -0.0970   0.6150   1.0000
   1.250   0.6272   0.01002   0.00319  -0.0952   0.5865   1.0000
   1.500   0.6463   0.01025   0.00320  -0.0933   0.5600   1.0000
   1.750   0.6660   0.01049   0.00325  -0.0916   0.5383   1.0000
   2.000   0.6861   0.01074   0.00333  -0.0900   0.5199   1.0000
   2.250   0.7065   0.01098   0.00344  -0.0885   0.5029   1.0000
   2.500   0.7272   0.01122   0.00356  -0.0870   0.4862   1.0000
   2.750   0.7480   0.01146   0.00369  -0.0856   0.4694   1.0000
   3.000   0.7690   0.01169   0.00384  -0.0842   0.4532   1.0000
   3.250   0.7900   0.01193   0.00399  -0.0829   0.4374   1.0000
   3.500   0.8110   0.01217   0.00416  -0.0816   0.4223   1.0000
   3.750   0.8320   0.01243   0.00434  -0.0802   0.4077   1.0000
   4.000   0.8529   0.01269   0.00453  -0.0789   0.3934   1.0000
   4.250   0.8736   0.01297   0.00474  -0.0776   0.3800   1.0000
   4.750   0.9156   0.01354   0.00521  -0.0750   0.3567   1.0000
   5.000   0.9368   0.01382   0.00547  -0.0738   0.3475   1.0000
   5.250   0.9577   0.01414   0.00575  -0.0726   0.3388   1.0000
   5.500   0.9793   0.01443   0.00605  -0.0715   0.3301   1.0000
   5.750   0.9999   0.01477   0.00635  -0.0702   0.3224   1.0000
   6.000   1.0213   0.01506   0.00667  -0.0691   0.3134   1.0000
   6.250   1.0414   0.01540   0.00700  -0.0678   0.3028   1.0000
   6.500   1.0601   0.01575   0.00731  -0.0662   0.2878   1.0000
   6.750   1.0788   0.01611   0.00763  -0.0647   0.2737   1.0000
   7.000   1.0973   0.01648   0.00797  -0.0632   0.2610   1.0000
   7.250   1.1160   0.01684   0.00832  -0.0617   0.2489   1.0000
   7.500   1.1349   0.01718   0.00871  -0.0602   0.2373   1.0000
   7.750   1.1517   0.01758   0.00909  -0.0584   0.2231   1.0000
   8.000   1.1673   0.01802   0.00950  -0.0564   0.2068   1.0000
   8.250   1.1810   0.01859   0.00997  -0.0542   0.1813   1.0000
   8.500   1.1891   0.01953   0.01064  -0.0513   0.1381   1.0000
   8.750   1.1915   0.02096   0.01172  -0.0477   0.0898   1.0000
   9.000   1.1816   0.02325   0.01352  -0.0427   0.0237   1.0000
   9.250   1.1920   0.02417   0.01449  -0.0403   0.0202   1.0000
   9.500   1.2036   0.02503   0.01547  -0.0382   0.0188   1.0000
   9.750   1.2140   0.02597   0.01655  -0.0361   0.0177   1.0000
  10.000   1.2220   0.02710   0.01781  -0.0338   0.0164   1.0000
  10.250   1.2280   0.02839   0.01925  -0.0314   0.0154   1.0000
  10.500   1.2321   0.02986   0.02088  -0.0290   0.0147   1.0000
  10.750   1.2365   0.03133   0.02253  -0.0269   0.0142   1.0000
  11.000   1.2410   0.03286   0.02420  -0.0249   0.0139   1.0000
  11.250   1.2436   0.03459   0.02608  -0.0230   0.0136   1.0000
  11.500   1.2443   0.03656   0.02820  -0.0213   0.0134   1.0000
  11.750   1.2428   0.03882   0.03061  -0.0197   0.0131   1.0000
  12.000   1.2406   0.04130   0.03323  -0.0185   0.0128   1.0000
  12.250   1.2371   0.04405   0.03611  -0.0175   0.0124   1.0000
  12.500   1.2329   0.04703   0.03921  -0.0169   0.0121   1.0000
  12.750   1.2278   0.05027   0.04257  -0.0166   0.0117   1.0000
  13.000   1.2207   0.05393   0.04636  -0.0166   0.0114   1.0000
  13.250   1.2150   0.05764   0.05018  -0.0169   0.0113   1.0000
  13.500   1.2065   0.06185   0.05451  -0.0176   0.0110   1.0000
  13.750   1.2004   0.06589   0.05864  -0.0183   0.0108   1.0000
  14.000   1.1943   0.06997   0.06280  -0.0190   0.0107   1.0000
  14.250   1.1885   0.07390   0.06678  -0.0195   0.0105   1.0000
  14.500   1.1865   0.07716   0.07006  -0.0195   0.0103   1.0000
  14.750   1.1875   0.08036   0.07334  -0.0200   0.0102   1.0000
  15.000   1.1889   0.08354   0.07663  -0.0205   0.0101   1.0000
  15.250   1.1912   0.08654   0.07971  -0.0209   0.0100   1.0000
  15.500   1.1927   0.08978   0.08308  -0.0215   0.0098   1.0000
  15.750   1.1957   0.09272   0.08612  -0.0219   0.0097   1.0000
  16.000   1.1981   0.09584   0.08935  -0.0225   0.0096   1.0000
  16.250   1.2003   0.09902   0.09264  -0.0231   0.0095   1.0000
  16.500   1.2008   0.10258   0.09634  -0.0241   0.0093   1.0000
  16.750   1.2003   0.10639   0.10030  -0.0254   0.0091   1.0000
  17.000   1.1992   0.11036   0.10441  -0.0269   0.0089   1.0000
  17.250   1.1973   0.11454   0.10872  -0.0286   0.0087   1.0000
  17.500   1.1954   0.11874   0.11306  -0.0304   0.0086   1.0000
  17.750   1.1929   0.12310   0.11753  -0.0326   0.0083   1.0000
  18.000   1.1897   0.12766   0.12223  -0.0347   0.0082   1.0000
  18.250   1.1874   0.13206   0.12674  -0.0370   0.0081   1.0000
  18.500   1.1828   0.13711   0.13193  -0.0397   0.0080   1.0000
  18.750   1.1784   0.14214   0.13710  -0.0425   0.0080   1.0000
  19.000   1.1738   0.14726   0.14235  -0.0454   0.0079   1.0000
  19.250   1.1676   0.15291   0.14815  -0.0488   0.0079   1.0000
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