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GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 7K AIRFOIL (goe07k-il)
Reynolds number: 1,000,000
Max Cl/Cd: 159.87 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe07k-il-1000000.txt
Download as CSV file: xf-goe07k-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 7K 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1894   0.11004   0.10814  -0.1104   0.9752   0.0126
 -11.500  -0.1796   0.10619   0.10429  -0.1133   0.9749   0.0126
 -10.500  -0.1679   0.08938   0.08750  -0.1212   0.9656   0.0129
 -10.250  -0.1599   0.08499   0.08312  -0.1247   0.9648   0.0130
 -10.000  -0.1453   0.08249   0.08061  -0.1274   0.9642   0.0133
  -9.750  -0.1316   0.07949   0.07760  -0.1305   0.9637   0.0138
  -9.500  -0.1327   0.07715   0.07529  -0.1299   0.9581   0.0141
  -9.250  -0.1264   0.07330   0.07143  -0.1330   0.9558   0.0145
  -9.000  -0.1191   0.06885   0.06700  -0.1375   0.9541   0.0151
  -8.750  -0.3162   0.02241   0.01916  -0.1472   0.9308   0.0106
  -8.500  -0.3038   0.01916   0.01546  -0.1460   0.9283   0.0109
  -8.250  -0.2796   0.01720   0.01316  -0.1465   0.9269   0.0112
  -8.000  -0.2487   0.01602   0.01177  -0.1481   0.9259   0.0118
  -7.750  -0.2440   0.01519   0.01077  -0.1434   0.9208   0.0121
  -7.500  -0.2195   0.01457   0.01001  -0.1431   0.9183   0.0125
  -7.250  -0.1923   0.01373   0.00899  -0.1434   0.9164   0.0127
  -7.000  -0.1656   0.01231   0.00735  -0.1440   0.9146   0.0141
  -6.750  -0.1296   0.01182   0.00678  -0.1463   0.9135   0.0148
  -6.500  -0.0922   0.01143   0.00632  -0.1489   0.9124   0.0159
  -6.250  -0.0877   0.01117   0.00600  -0.1438   0.9077   0.0163
  -6.000  -0.0632   0.01089   0.00564  -0.1432   0.9051   0.0169
  -5.750  -0.0386   0.01004   0.00467  -0.1429   0.9028   0.0184
  -5.500  -0.0064   0.00977   0.00437  -0.1442   0.9011   0.0198
  -5.250   0.0293   0.00960   0.00417  -0.1463   0.8996   0.0216
  -5.000   0.0531   0.00936   0.00386  -0.1457   0.8969   0.0227
  -4.750   0.0628   0.00905   0.00353  -0.1416   0.8926   0.0250
  -4.500   0.0894   0.00894   0.00342  -0.1416   0.8901   0.0274
  -4.250   0.1195   0.00886   0.00332  -0.1423   0.8880   0.0291
  -4.000   0.1503   0.00859   0.00304  -0.1432   0.8861   0.0335
  -3.750   0.1876   0.00860   0.00305  -0.1457   0.8844   0.0369
  -3.500   0.1962   0.00861   0.00306  -0.1413   0.8804   0.0379
  -3.250   0.2144   0.00830   0.00274  -0.1393   0.8770   0.0422
  -3.000   0.2422   0.00822   0.00265  -0.1395   0.8745   0.0457
  -2.750   0.2736   0.00816   0.00257  -0.1405   0.8724   0.0483
  -2.500   0.3079   0.00798   0.00235  -0.1423   0.8703   0.0518
  -2.250   0.3126   0.00786   0.00223  -0.1370   0.8658   0.0543
  -2.000   0.3342   0.00775   0.00211  -0.1357   0.8625   0.0572
  -1.750   0.3608   0.00765   0.00199  -0.1356   0.8600   0.0595
  -1.500   0.3926   0.00757   0.00188  -0.1367   0.8578   0.0615
  -1.250   0.4168   0.00749   0.00179  -0.1361   0.8550   0.0652
  -1.000   0.4267   0.00739   0.00172  -0.1320   0.8506   0.0709
  -0.750   0.4491   0.00730   0.00165  -0.1309   0.8473   0.0797
  -0.500   0.4696   0.00674   0.00162  -0.1297   0.8444   0.2764
  -0.250   0.4801   0.00616   0.00166  -0.1262   0.8405   0.5006
   0.000   0.4740   0.00565   0.00170  -0.1185   0.8350   0.6892
   0.250   0.6668   0.00551   0.00228  -0.1576   0.8421   0.9462
   0.500   0.6833   0.00563   0.00242  -0.1549   0.8369   0.9617
   0.750   0.7159   0.00580   0.00257  -0.1561   0.8332   0.9736
   1.000   0.7674   0.00597   0.00271  -0.1616   0.8292   0.9811
   1.250   0.7993   0.00600   0.00275  -0.1626   0.8208   0.9866
   1.500   0.8409   0.00603   0.00273  -0.1659   0.8141   0.9895
   1.750   0.8679   0.00606   0.00279  -0.1659   0.8071   0.9943
   2.000   0.9194   0.00602   0.00273  -0.1715   0.8016   0.9972
   2.250   0.9503   0.00596   0.00268  -0.1725   0.7924   1.0000
   2.500   0.9558   0.00598   0.00267  -0.1676   0.7818   1.0000
   2.750   0.9624   0.00602   0.00268  -0.1629   0.7698   1.0000
   3.000   0.9667   0.00610   0.00271  -0.1576   0.7539   1.0000
   3.250   0.9730   0.00621   0.00277  -0.1528   0.7378   1.0000
   3.500   0.9767   0.00636   0.00285  -0.1474   0.7185   1.0000
   3.750   0.9836   0.00653   0.00296  -0.1428   0.6999   1.0000
   4.000   0.9809   0.00682   0.00312  -0.1359   0.6647   1.0000
   4.250   0.9769   0.00721   0.00335  -0.1289   0.6216   1.0000
   4.500   0.9556   0.00805   0.00381  -0.1182   0.5420   1.0000
   4.750   0.9442   0.00896   0.00436  -0.1100   0.4678   1.0000
   5.000   0.9397   0.00980   0.00487  -0.1035   0.3982   1.0000
   5.250   0.9362   0.01073   0.00541  -0.0974   0.3159   1.0000
   5.500   0.9332   0.01174   0.00603  -0.0915   0.2349   1.0000
   5.750   0.9389   0.01250   0.00654  -0.0875   0.1813   1.0000
   6.000   0.9443   0.01332   0.00707  -0.0835   0.1206   1.0000
   6.250   0.9530   0.01406   0.00761  -0.0802   0.0782   1.0000
   6.500   0.9672   0.01456   0.00803  -0.0779   0.0632   1.0000
   6.750   0.9833   0.01497   0.00842  -0.0759   0.0532   1.0000
   7.000   0.9989   0.01543   0.00883  -0.0739   0.0408   1.0000
   7.250   1.0128   0.01599   0.00931  -0.0716   0.0292   1.0000
   7.500   1.0287   0.01646   0.00979  -0.0697   0.0253   1.0000
   7.750   1.0422   0.01709   0.01042  -0.0674   0.0210   1.0000
   8.000   1.0593   0.01751   0.01088  -0.0658   0.0196   1.0000
   8.250   1.0751   0.01801   0.01140  -0.0639   0.0181   1.0000
   8.500   1.0895   0.01861   0.01202  -0.0619   0.0166   1.0000
   8.750   1.1003   0.01945   0.01293  -0.0592   0.0152   1.0000
   9.000   1.1174   0.01989   0.01341  -0.0577   0.0146   1.0000
   9.250   1.1322   0.02049   0.01406  -0.0559   0.0140   1.0000
   9.500   1.1476   0.02106   0.01466  -0.0542   0.0131   1.0000
   9.750   1.1617   0.02172   0.01534  -0.0523   0.0124   1.0000
  10.000   1.1711   0.02269   0.01637  -0.0497   0.0116   1.0000
  10.250   1.1762   0.02401   0.01781  -0.0465   0.0111   1.0000
  10.500   1.1921   0.02458   0.01842  -0.0450   0.0107   1.0000
  10.750   1.2049   0.02538   0.01928  -0.0431   0.0103   1.0000
  11.000   1.2183   0.02613   0.02009  -0.0413   0.0101   1.0000
  11.250   1.2309   0.02696   0.02097  -0.0394   0.0096   1.0000
  11.500   1.2452   0.02764   0.02168  -0.0380   0.0091   1.0000
  11.750   1.2545   0.02875   0.02288  -0.0357   0.0091   1.0000
  12.000   1.2667   0.02962   0.02378  -0.0341   0.0085   1.0000
  12.250   1.2724   0.03106   0.02531  -0.0315   0.0082   1.0000
  12.500   1.2736   0.03309   0.02751  -0.0283   0.0078   1.0000
  12.750   1.2836   0.03426   0.02877  -0.0265   0.0077   1.0000
  13.000   1.2947   0.03525   0.02984  -0.0249   0.0075   1.0000
  13.250   1.3027   0.03660   0.03130  -0.0229   0.0074   1.0000
  13.500   1.3091   0.03817   0.03299  -0.0208   0.0073   1.0000
  13.750   1.3163   0.03957   0.03450  -0.0189   0.0071   1.0000
  14.000   1.3232   0.04100   0.03603  -0.0172   0.0069   1.0000
  14.250   1.3275   0.04272   0.03788  -0.0152   0.0067   1.0000
  14.500   1.3300   0.04466   0.03995  -0.0132   0.0066   1.0000
  14.750   1.3328   0.04654   0.04195  -0.0114   0.0065   1.0000
  15.000   1.3336   0.04869   0.04423  -0.0095   0.0064   1.0000
  15.250   1.3406   0.05001   0.04556  -0.0086   0.0061   1.0000
  15.500   1.3390   0.05250   0.04819  -0.0069   0.0061   1.0000
  15.750   1.3363   0.05512   0.05095  -0.0053   0.0060   1.0000
  16.000   1.3381   0.05722   0.05309  -0.0044   0.0058   1.0000
  16.250   1.3294   0.06071   0.05673  -0.0030   0.0057   1.0000
  16.500   1.3168   0.06482   0.06103  -0.0018   0.0057   1.0000
  16.750   1.2959   0.07014   0.06656  -0.0010   0.0055   1.0000
  17.000   1.2801   0.07511   0.07172  -0.0007   0.0055   1.0000
  17.250   1.2534   0.08199   0.07883  -0.0013   0.0055   1.0000
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