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GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 675 AIRFOIL (goe675-il)
Reynolds number: 200,000
Max Cl/Cd: 69.88 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe675-il-200000-n5.txt
Download as CSV file: xf-goe675-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 675 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4556   0.03940   0.03432  -0.1412   0.9100   0.0407
 -11.000  -0.4560   0.03506   0.02963  -0.1443   0.9045   0.0411
 -10.750  -0.4429   0.03363   0.02811  -0.1444   0.8984   0.0415
 -10.500  -0.4269   0.03222   0.02659  -0.1447   0.8934   0.0419
 -10.250  -0.4094   0.03071   0.02492  -0.1449   0.8893   0.0425
 -10.000  -0.3908   0.02911   0.02309  -0.1452   0.8860   0.0433
  -9.750  -0.3745   0.02760   0.02136  -0.1450   0.8808   0.0440
  -9.500  -0.3561   0.02610   0.01960  -0.1448   0.8761   0.0448
  -9.250  -0.3351   0.02475   0.01799  -0.1446   0.8722   0.0456
  -9.000  -0.3104   0.02408   0.01726  -0.1445   0.8691   0.0463
  -8.750  -0.2856   0.02346   0.01656  -0.1444   0.8661   0.0471
  -8.500  -0.2631   0.02284   0.01586  -0.1440   0.8614   0.0481
  -8.250  -0.2393   0.02210   0.01498  -0.1437   0.8572   0.0493
  -8.000  -0.2143   0.02132   0.01403  -0.1435   0.8536   0.0507
  -7.750  -0.1871   0.02098   0.01366  -0.1435   0.8507   0.0521
  -7.500  -0.1595   0.02054   0.01311  -0.1436   0.8482   0.0540
  -7.250  -0.1359   0.02006   0.01253  -0.1431   0.8434   0.0564
  -7.000  -0.1098   0.01986   0.01232  -0.1428   0.8391   0.0583
  -6.750  -0.0830   0.01938   0.01169  -0.1427   0.8355   0.0616
  -6.500  -0.0549   0.01914   0.01141  -0.1427   0.8326   0.0640
  -6.250  -0.0263   0.01879   0.01092  -0.1428   0.8300   0.0676
  -6.000  -0.0015   0.01859   0.01068  -0.1423   0.8246   0.0704
  -5.750   0.0252   0.01839   0.01042  -0.1420   0.8193   0.0737
  -5.500   0.0534   0.01806   0.00994  -0.1420   0.8150   0.0772
  -5.250   0.0828   0.01782   0.00966  -0.1421   0.8114   0.0801
  -5.000   0.1075   0.01764   0.00943  -0.1415   0.8049   0.0831
  -4.750   0.1348   0.01733   0.00902  -0.1413   0.7995   0.0858
  -4.500   0.1634   0.01705   0.00873  -0.1414   0.7953   0.0883
  -4.250   0.1907   0.01686   0.00849  -0.1412   0.7902   0.0912
  -4.000   0.2172   0.01671   0.00823  -0.1408   0.7836   0.0947
  -3.750   0.2453   0.01645   0.00801  -0.1408   0.7783   0.0983
  -3.500   0.2733   0.01629   0.00781  -0.1407   0.7727   0.1020
  -3.250   0.2996   0.01610   0.00756  -0.1403   0.7660   0.1047
  -3.000   0.3277   0.01579   0.00720  -0.1402   0.7610   0.1066
  -2.750   0.3562   0.01550   0.00691  -0.1402   0.7565   0.1087
  -2.500   0.3819   0.01534   0.00678  -0.1397   0.7498   0.1108
  -2.250   0.4098   0.01511   0.00653  -0.1396   0.7438   0.1129
  -2.000   0.4381   0.01490   0.00627  -0.1395   0.7383   0.1152
  -1.750   0.4642   0.01477   0.00613  -0.1391   0.7309   0.1174
  -1.500   0.4922   0.01454   0.00591  -0.1390   0.7248   0.1204
  -1.250   0.5191   0.01441   0.00580  -0.1387   0.7178   0.1239
  -1.000   0.5461   0.01428   0.00566  -0.1384   0.7098   0.1279
  -0.750   0.5738   0.01416   0.00550  -0.1382   0.7024   0.1322
  -0.500   0.5999   0.01403   0.00542  -0.1378   0.6935   0.1379
  -0.250   0.6276   0.01393   0.00529  -0.1377   0.6855   0.1455
   0.000   0.6535   0.01384   0.00524  -0.1372   0.6754   0.1556
   0.250   0.6802   0.01375   0.00516  -0.1369   0.6655   0.1699
   0.500   0.7063   0.01366   0.00513  -0.1365   0.6543   0.1914
   0.750   0.7319   0.01358   0.00516  -0.1360   0.6427   0.2268
   1.000   0.7577   0.01352   0.00517  -0.1356   0.6307   0.2734
   1.250   0.7826   0.01348   0.00520  -0.1350   0.6170   0.3196
   1.500   0.8068   0.01341   0.00527  -0.1343   0.6020   0.3792
   1.750   0.8297   0.01323   0.00539  -0.1334   0.5866   0.4988
   2.250   0.8791   0.01265   0.00563  -0.1315   0.5539   1.0000
   2.500   0.9011   0.01291   0.00574  -0.1303   0.5365   1.0000
   2.750   0.9224   0.01320   0.00589  -0.1291   0.5198   1.0000
   3.000   0.9434   0.01351   0.00605  -0.1278   0.5049   1.0000
   3.500   0.9853   0.01415   0.00646  -0.1252   0.4795   1.0000
   3.750   1.0060   0.01449   0.00670  -0.1240   0.4690   1.0000
   4.000   1.0269   0.01483   0.00695  -0.1227   0.4594   1.0000
   4.250   1.0481   0.01517   0.00721  -0.1216   0.4516   1.0000
   4.500   1.0692   0.01550   0.00748  -0.1204   0.4440   1.0000
   5.000   1.1101   0.01619   0.00806  -0.1179   0.4307   1.0000
   5.250   1.1309   0.01654   0.00838  -0.1168   0.4246   1.0000
   5.500   1.1517   0.01694   0.00870  -0.1157   0.4191   1.0000
   5.750   1.1732   0.01728   0.00905  -0.1147   0.4136   1.0000
   6.000   1.1942   0.01764   0.00941  -0.1136   0.4080   1.0000
   6.250   1.2148   0.01805   0.00977  -0.1126   0.4028   1.0000
   6.500   1.2358   0.01846   0.01016  -0.1116   0.3979   1.0000
   6.750   1.2560   0.01883   0.01057  -0.1105   0.3921   1.0000
   7.000   1.2752   0.01927   0.01100  -0.1092   0.3861   1.0000
   7.250   1.2942   0.01976   0.01144  -0.1080   0.3804   1.0000
   7.500   1.3128   0.02017   0.01192  -0.1067   0.3740   1.0000
   7.750   1.3305   0.02066   0.01241  -0.1053   0.3675   1.0000
   8.000   1.3479   0.02120   0.01292  -0.1040   0.3617   1.0000
   8.250   1.3659   0.02167   0.01347  -0.1027   0.3553   1.0000
   8.500   1.3826   0.02222   0.01403  -0.1013   0.3492   1.0000
   8.750   1.3991   0.02281   0.01461  -0.0999   0.3438   1.0000
   9.000   1.4163   0.02336   0.01525  -0.0987   0.3375   1.0000
   9.250   1.4319   0.02400   0.01591  -0.0972   0.3315   1.0000
   9.500   1.4473   0.02466   0.01658  -0.0958   0.3259   1.0000
   9.750   1.4631   0.02532   0.01732  -0.0945   0.3194   1.0000
  10.000   1.4768   0.02609   0.01811  -0.0930   0.3130   1.0000
  10.250   1.4910   0.02685   0.01892  -0.0915   0.3064   1.0000
  10.500   1.5037   0.02771   0.01982  -0.0900   0.2987   1.0000
  10.750   1.5147   0.02867   0.02081  -0.0883   0.2904   1.0000
  11.000   1.5249   0.02972   0.02188  -0.0867   0.2809   1.0000
  11.250   1.5356   0.03078   0.02298  -0.0851   0.2722   1.0000
  11.500   1.5444   0.03198   0.02419  -0.0834   0.2637   1.0000
  11.750   1.5545   0.03314   0.02541  -0.0819   0.2548   1.0000
  12.000   1.5611   0.03457   0.02683  -0.0802   0.2458   1.0000
  12.250   1.5681   0.03601   0.02830  -0.0786   0.2350   1.0000
  12.500   1.5736   0.03762   0.02993  -0.0770   0.2243   1.0000
  12.750   1.5777   0.03940   0.03172  -0.0754   0.2142   1.0000
  13.000   1.5812   0.04131   0.03364  -0.0739   0.2036   1.0000
  13.250   1.5843   0.04331   0.03567  -0.0725   0.1930   1.0000
  13.500   1.5840   0.04568   0.03803  -0.0710   0.1812   1.0000
  13.750   1.5816   0.04834   0.04068  -0.0696   0.1689   1.0000
  14.000   1.5787   0.05117   0.04350  -0.0683   0.1575   1.0000
  14.250   1.5743   0.05422   0.04656  -0.0671   0.1459   1.0000
  14.500   1.5694   0.05743   0.04979  -0.0661   0.1341   1.0000
  14.750   1.5628   0.06095   0.05331  -0.0653   0.1215   1.0000
  15.000   1.5530   0.06495   0.05731  -0.0646   0.1077   1.0000
  15.250   1.5400   0.06944   0.06179  -0.0641   0.0949   1.0000
  15.500   1.5266   0.07414   0.06649  -0.0638   0.0847   1.0000
  15.750   1.5138   0.07891   0.07129  -0.0638   0.0762   1.0000
  16.000   1.5020   0.08367   0.07610  -0.0639   0.0686   1.0000
  16.250   1.4901   0.08852   0.08101  -0.0643   0.0618   1.0000
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