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GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 510 AIRFOIL (goe510-il)
Reynolds number: 100,000
Max Cl/Cd: 48.44 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe510-il-100000.txt
Download as CSV file: xf-goe510-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 510 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3354   0.12078   0.11647  -0.0186   1.0000   0.1066
  -8.000  -0.3592   0.12061   0.11639  -0.0211   0.9979   0.1086
  -7.750  -0.3892   0.12018   0.11599  -0.0324   0.9855   0.1095
  -7.500  -0.3111   0.11123   0.10697  -0.0280   0.9866   0.1130
  -7.250  -0.2870   0.10779   0.10350  -0.0322   0.9797   0.1177
  -7.000  -0.2951   0.10588   0.10160  -0.0394   0.9684   0.1226
  -6.750  -0.3077   0.10275   0.09844  -0.0475   0.9536   0.1246
  -6.500  -0.2685   0.09775   0.09345  -0.0456   0.9478   0.1270
  -6.250  -0.2364   0.09392   0.08958  -0.0496   0.9417   0.1316
  -6.000  -0.2549   0.09300   0.08846  -0.0587   0.9215   0.1391
  -5.750  -0.2356   0.08764   0.08318  -0.0581   0.9154   0.1407
  -5.500  -0.2024   0.08381   0.07936  -0.0588   0.9118   0.1442
  -5.250  -0.1939   0.08154   0.07708  -0.0588   0.9005   0.1497
  -4.750  -0.1636   0.07513   0.07055  -0.0632   0.8828   0.1605
  -4.500  -0.1478   0.07290   0.06823  -0.0645   0.8734   0.1682
  -4.250  -0.1276   0.06934   0.06454  -0.0677   0.8656   0.1746
  -3.750  -0.0856   0.06424   0.05920  -0.0705   0.8489   0.1905
  -3.500  -0.0732   0.06174   0.05675  -0.0686   0.8389   0.1936
  -3.250  -0.0417   0.05922   0.05400  -0.0716   0.8326   0.2079
  -3.000  -0.0280   0.05690   0.05173  -0.0697   0.8226   0.2123
  -2.750   0.0050   0.05435   0.04895  -0.0722   0.8164   0.2259
  -2.500   0.0459   0.05099   0.04553  -0.0748   0.8137   0.2344
  -2.000   0.0999   0.03674   0.02897  -0.0766   0.7979   0.1233
  -1.750   0.1162   0.03514   0.02718  -0.0744   0.7861   0.1221
  -1.500   0.1605   0.03232   0.02397  -0.0764   0.7827   0.1206
  -1.250   0.2135   0.02973   0.02094  -0.0797   0.7804   0.1212
  -1.000   0.2342   0.02893   0.01987  -0.0777   0.7679   0.1234
  -0.750   0.2927   0.02672   0.01755  -0.0823   0.7648   0.1274
  -0.500   0.3215   0.02588   0.01666  -0.0818   0.7536   0.1305
  -0.250   0.3847   0.02429   0.01489  -0.0873   0.7486   0.1383
   0.000   0.4197   0.02345   0.01415  -0.0881   0.7371   0.1471
   0.250   0.4815   0.02204   0.01275  -0.0935   0.7299   0.1630
   0.500   0.5130   0.02153   0.01231  -0.0936   0.7161   0.1884
   0.750   0.5462   0.02113   0.01221  -0.0939   0.7031   0.2777
   1.000   0.5846   0.02077   0.01178  -0.0953   0.6907   0.3442
   1.250   0.6284   0.02027   0.01123  -0.0981   0.6783   0.3924
   1.500   0.6519   0.01998   0.01104  -0.0971   0.6638   0.4297
   1.750   0.6708   0.01963   0.01088  -0.0952   0.6507   0.4797
   2.000   0.8939   0.01912   0.01090  -0.1336   0.6276   1.0000
   2.250   0.9097   0.01948   0.01114  -0.1312   0.6148   1.0000
   2.500   0.9314   0.01978   0.01127  -0.1299   0.6037   1.0000
   2.750   0.9556   0.02003   0.01134  -0.1291   0.5933   1.0000
   3.000   0.9689   0.02044   0.01169  -0.1263   0.5826   1.0000
   3.250   0.9974   0.02068   0.01171  -0.1263   0.5738   1.0000
   3.500   1.0065   0.02112   0.01217  -0.1228   0.5639   1.0000
   3.750   1.0328   0.02139   0.01227  -0.1225   0.5558   1.0000
   4.000   1.0428   0.02183   0.01274  -0.1191   0.5467   1.0000
   4.250   1.0709   0.02211   0.01284  -0.1191   0.5393   1.0000
   4.500   1.0781   0.02260   0.01340  -0.1152   0.5308   1.0000
   4.750   1.1061   0.02287   0.01351  -0.1152   0.5237   1.0000
   5.000   1.1137   0.02341   0.01413  -0.1115   0.5160   1.0000
   5.250   1.1361   0.02374   0.01436  -0.1105   0.5087   1.0000
   5.500   1.1511   0.02424   0.01486  -0.1081   0.5016   1.0000
   5.750   1.1660   0.02469   0.01532  -0.1058   0.4944   1.0000
   6.000   1.1946   0.02507   0.01558  -0.1060   0.4881   1.0000
   6.250   1.1985   0.02572   0.01634  -0.1016   0.4809   1.0000
   6.500   1.2248   0.02608   0.01661  -0.1014   0.4743   1.0000
   6.750   1.2355   0.02673   0.01732  -0.0984   0.4676   1.0000
   7.000   1.2491   0.02729   0.01791  -0.0959   0.4608   1.0000
   7.250   1.2843   0.02774   0.01821  -0.0974   0.4548   1.0000
   7.500   1.2797   0.02858   0.01925  -0.0917   0.4482   1.0000
   7.750   1.3008   0.02907   0.01972  -0.0906   0.4417   1.0000
   8.000   1.3214   0.02974   0.02038  -0.0895   0.4356   1.0000
   8.250   1.3224   0.03058   0.02136  -0.0849   0.4291   1.0000
   8.500   1.3518   0.03103   0.02175  -0.0853   0.4230   1.0000
   8.750   1.3579   0.03196   0.02278  -0.0818   0.4171   1.0000
   9.000   1.3610   0.03279   0.02373  -0.0777   0.4108   1.0000
   9.250   1.3992   0.03317   0.02400  -0.0797   0.4047   1.0000
   9.500   1.3891   0.03433   0.02535  -0.0735   0.3990   1.0000
   9.750   1.3930   0.03513   0.02626  -0.0696   0.3928   1.0000
  10.000   1.4341   0.03523   0.02623  -0.0719   0.3856   1.0000
  10.250   1.4093   0.03646   0.02769  -0.0634   0.3799   1.0000
  10.500   1.4630   0.03558   0.02655  -0.0673   0.3695   1.0000
  10.750   1.4298   0.03693   0.02815  -0.0575   0.3649   1.0000
  11.000   1.4334   0.03704   0.02829  -0.0535   0.3571   1.0000
  11.250   1.4444   0.03711   0.02833  -0.0507   0.3492   1.0000
  11.500   1.4333   0.03804   0.02939  -0.0451   0.3430   1.0000
  11.750   1.4648   0.03741   0.02862  -0.0453   0.3348   1.0000
  12.000   1.4411   0.03906   0.03051  -0.0386   0.3297   1.0000
  12.250   1.4600   0.03877   0.03017  -0.0371   0.3221   1.0000
  12.500   1.4518   0.03989   0.03141  -0.0328   0.3159   1.0000
  12.750   1.4435   0.04105   0.03269  -0.0287   0.3096   1.0000
  13.000   1.4636   0.04081   0.03238  -0.0276   0.3022   1.0000
  13.250   1.4413   0.04312   0.03492  -0.0228   0.2970   1.0000
  13.500   1.4638   0.04247   0.03415  -0.0218   0.2887   1.0000
  13.750   1.4408   0.04519   0.03710  -0.0177   0.2835   1.0000
  14.000   1.4365   0.04653   0.03853  -0.0151   0.2763   1.0000
  14.250   1.4373   0.04779   0.03983  -0.0132   0.2698   1.0000
  14.500   1.4197   0.05079   0.04303  -0.0107   0.2642   1.0000
  14.750   1.4399   0.05051   0.04264  -0.0098   0.2570   1.0000
  15.000   1.4089   0.05511   0.04752  -0.0075   0.2519   1.0000
  15.250   1.4039   0.05729   0.04975  -0.0063   0.2446   1.0000
  15.500   1.3922   0.06048   0.05304  -0.0053   0.2383   1.0000
  15.750   1.3732   0.06485   0.05758  -0.0047   0.2327   1.0000
  16.000   1.3774   0.06643   0.05915  -0.0042   0.2254   1.0000
  16.250   1.3442   0.07310   0.06604  -0.0045   0.2203   1.0000
  16.500   1.3429   0.07570   0.06867  -0.0044   0.2136   1.0000
  16.750   1.3215   0.08131   0.07444  -0.0052   0.2085   1.0000
  17.000   1.2838   0.08963   0.08295  -0.0069   0.2038   1.0000
  17.250   1.2946   0.09067   0.08394  -0.0068   0.1957   1.0000
  17.500   1.2385   0.10248   0.09599  -0.0101   0.1926   1.0000
  17.750   0.9232   0.17238   0.16568  -0.0388   0.1941   1.0000
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