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GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 610 B AIRFOIL (goe610b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 132.17 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe610b-il-1000000.txt
Download as CSV file: xf-goe610b-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610 B AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2385   0.10705   0.10552  -0.0355   1.0000   0.0128
 -10.500  -0.2354   0.10439   0.10288  -0.0355   1.0000   0.0130
 -10.250  -0.3219   0.11028   0.10864  -0.0317   1.0000   0.0127
 -10.000  -0.3162   0.10803   0.10640  -0.0319   1.0000   0.0129
  -9.750  -0.3123   0.10539   0.10377  -0.0323   1.0000   0.0130
  -9.500  -0.3079   0.10308   0.10148  -0.0325   1.0000   0.0132
  -9.250  -0.3042   0.10076   0.09918  -0.0326   1.0000   0.0136
  -8.250  -0.2496   0.08394   0.08237  -0.0514   0.9707   0.0158
  -8.000  -0.2234   0.07821   0.07661  -0.0605   0.9570   0.0158
  -7.750  -0.1911   0.07341   0.07177  -0.0687   0.9451   0.0166
  -7.500  -0.1556   0.06608   0.06429  -0.0825   0.9136   0.0151
  -7.250  -0.1452   0.06175   0.05977  -0.0872   0.8762   0.0151
  -7.000  -0.1430   0.05652   0.05440  -0.0908   0.8553   0.0153
  -6.750  -0.1423   0.04836   0.04608  -0.0966   0.8418   0.0161
  -6.500  -0.1222   0.04758   0.04524  -0.0971   0.8340   0.0166
  -6.250  -0.1009   0.04731   0.04494  -0.0972   0.8268   0.0172
  -6.000  -0.0851   0.04281   0.04030  -0.0998   0.8198   0.0178
  -5.750  -0.1129   0.01485   0.01060  -0.1026   0.8126   0.0255
  -5.500  -0.0837   0.01577   0.01158  -0.1026   0.8071   0.0258
  -5.250  -0.0547   0.01661   0.01253  -0.1027   0.8014   0.0261
  -5.000  -0.0264   0.01739   0.01336  -0.1026   0.7954   0.0264
  -4.750   0.0008   0.01776   0.01373  -0.1025   0.7896   0.0270
  -4.500   0.0277   0.01800   0.01397  -0.1023   0.7830   0.0280
  -4.250   0.0450   0.01404   0.00930  -0.1006   0.7770   0.0314
  -4.000   0.0712   0.01387   0.00913  -0.1004   0.7698   0.0322
  -3.750   0.0979   0.01409   0.00935  -0.1002   0.7622   0.0329
  -3.500   0.1245   0.01408   0.00935  -0.1000   0.7533   0.0339
  -3.250   0.1495   0.01338   0.00848  -0.0993   0.7428   0.0351
  -3.000   0.1744   0.01274   0.00764  -0.0986   0.7266   0.0364
  -2.750   0.1996   0.01259   0.00729  -0.0979   0.7027   0.0375
  -2.250   0.2464   0.01097   0.00516  -0.0961   0.6500   0.0397
  -1.500   0.3228   0.01026   0.00417  -0.0946   0.6043   0.0422
  -1.250   0.3489   0.00996   0.00378  -0.0941   0.5953   0.0429
  -1.000   0.3749   0.00966   0.00340  -0.0937   0.5867   0.0434
  -0.750   0.4013   0.00943   0.00311  -0.0933   0.5798   0.0444
  -0.500   0.4278   0.00930   0.00293  -0.0929   0.5732   0.0454
  -0.250   0.4542   0.00919   0.00278  -0.0926   0.5667   0.0462
   0.000   0.4809   0.00913   0.00268  -0.0922   0.5599   0.0468
   0.250   0.5073   0.00910   0.00261  -0.0919   0.5540   0.0472
   0.500   0.5329   0.00865   0.00215  -0.0914   0.5491   0.0480
   0.750   0.5584   0.00843   0.00191  -0.0909   0.5436   0.0487
   1.000   0.5842   0.00829   0.00175  -0.0904   0.5389   0.0497
   1.250   0.6107   0.00817   0.00165  -0.0901   0.5344   0.0512
   1.500   0.6370   0.00811   0.00160  -0.0897   0.5296   0.0530
   2.000   0.6899   0.00805   0.00153  -0.0891   0.5196   0.0557
   2.250   0.7163   0.00805   0.00152  -0.0887   0.5140   0.0566
   2.500   0.7425   0.00807   0.00153  -0.0884   0.5081   0.0573
   2.750   0.7692   0.00806   0.00154  -0.0881   0.5013   0.0580
   3.000   0.7951   0.00810   0.00156  -0.0877   0.4939   0.0603
   3.250   0.8217   0.00810   0.00159  -0.0874   0.4859   0.0663
   3.500   0.8473   0.00810   0.00169  -0.0869   0.4765   0.1156
   3.750   0.8568   0.00684   0.00192  -0.0835   0.4665   0.8110
   4.000   0.9516   0.00720   0.00224  -0.0992   0.3805   1.0000
   4.250   0.9675   0.00791   0.00261  -0.0970   0.3188   1.0000
   4.500   0.9891   0.00822   0.00282  -0.0958   0.2982   1.0000
   4.750   1.0117   0.00845   0.00301  -0.0948   0.2856   1.0000
   5.000   1.0340   0.00871   0.00320  -0.0937   0.2704   1.0000
   5.250   1.0561   0.00898   0.00340  -0.0927   0.2538   1.0000
   5.500   1.0778   0.00926   0.00360  -0.0915   0.2361   1.0000
   5.750   1.0991   0.00957   0.00382  -0.0903   0.2178   1.0000
   6.000   1.1186   0.00998   0.00409  -0.0889   0.1876   1.0000
   6.250   1.1316   0.01082   0.00461  -0.0863   0.1289   1.0000
   6.500   1.1514   0.01121   0.00495  -0.0848   0.1180   1.0000
   6.750   1.1715   0.01157   0.00528  -0.0835   0.1108   1.0000
   7.000   1.1931   0.01182   0.00555  -0.0824   0.1058   1.0000
   7.250   1.2141   0.01210   0.00584  -0.0812   0.0999   1.0000
   7.500   1.2346   0.01241   0.00615  -0.0799   0.0922   1.0000
   7.750   1.2490   0.01309   0.00659  -0.0776   0.0558   1.0000
   8.000   1.2592   0.01401   0.00732  -0.0747   0.0271   1.0000
   8.250   1.2749   0.01457   0.00786  -0.0726   0.0206   1.0000
   8.500   1.2903   0.01512   0.00842  -0.0704   0.0178   1.0000
   8.750   1.3055   0.01566   0.00901  -0.0683   0.0162   1.0000
   9.000   1.3198   0.01612   0.00951  -0.0659   0.0153   1.0000
   9.250   1.3325   0.01660   0.01003  -0.0633   0.0144   1.0000
   9.500   1.3442   0.01716   0.01063  -0.0606   0.0136   1.0000
   9.750   1.3498   0.01810   0.01165  -0.0571   0.0124   1.0000
  10.000   1.3614   0.01876   0.01238  -0.0547   0.0120   1.0000
  10.250   1.3754   0.01932   0.01298  -0.0528   0.0115   1.0000
  10.500   1.3863   0.02009   0.01381  -0.0505   0.0111   1.0000
  10.750   1.3973   0.02088   0.01466  -0.0484   0.0106   1.0000
  11.000   1.4082   0.02172   0.01555  -0.0464   0.0102   1.0000
  11.250   1.4175   0.02271   0.01660  -0.0444   0.0099   1.0000
  11.500   1.4238   0.02397   0.01793  -0.0422   0.0096   1.0000
  11.750   1.4195   0.02611   0.02019  -0.0393   0.0090   1.0000
  12.000   1.4197   0.02803   0.02222  -0.0371   0.0088   1.0000
  12.250   1.4283   0.02935   0.02361  -0.0357   0.0087   1.0000
  12.500   1.4363   0.03074   0.02508  -0.0344   0.0085   1.0000
  12.750   1.4418   0.03240   0.02682  -0.0330   0.0083   1.0000
  13.000   1.4464   0.03419   0.02869  -0.0318   0.0081   1.0000
  13.250   1.4528   0.03584   0.03042  -0.0307   0.0078   1.0000
  13.500   1.4588   0.03758   0.03224  -0.0298   0.0077   1.0000
  13.750   1.4604   0.03980   0.03454  -0.0288   0.0075   1.0000
  14.000   1.4645   0.04184   0.03665  -0.0281   0.0073   1.0000
  14.250   1.4659   0.04420   0.03910  -0.0274   0.0071   1.0000
  14.500   1.4661   0.04678   0.04175  -0.0268   0.0070   1.0000
  14.750   1.4659   0.04948   0.04453  -0.0264   0.0068   1.0000
  15.000   1.4605   0.05284   0.04797  -0.0260   0.0066   1.0000
  15.250   1.4497   0.05689   0.05215  -0.0256   0.0065   1.0000
  15.500   1.4355   0.06137   0.05677  -0.0251   0.0063   1.0000
  15.750   1.4285   0.06515   0.06068  -0.0250   0.0063   1.0000
  16.000   1.4263   0.06855   0.06418  -0.0253   0.0062   1.0000
  16.250   1.4244   0.07198   0.06772  -0.0258   0.0062   1.0000
  16.500   1.4210   0.07567   0.07152  -0.0265   0.0061   1.0000
  16.750   1.4155   0.07969   0.07566  -0.0272   0.0061   1.0000
  17.000   1.4110   0.08378   0.07986  -0.0282   0.0060   1.0000
  17.250   1.4026   0.08836   0.08457  -0.0292   0.0060   1.0000
  17.500   1.3936   0.09316   0.08949  -0.0305   0.0060   1.0000
  17.750   1.3863   0.09801   0.09446  -0.0322   0.0058   1.0000
  18.000   1.3775   0.10315   0.09971  -0.0340   0.0058   1.0000
  18.250   1.3643   0.10911   0.10582  -0.0362   0.0058   1.0000
  18.500   1.3553   0.11465   0.11147  -0.0386   0.0057   1.0000
  18.750   1.3438   0.12079   0.11774  -0.0414   0.0057   1.0000
  19.000   1.3315   0.12721   0.12430  -0.0445   0.0057   1.0000
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