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GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 342 AIRFOIL (goe342-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.66 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe342-il-1000000-n5.txt
Download as CSV file: xf-goe342-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 342 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2690   0.10180   0.10010  -0.0404   0.9617   0.0053
  -9.000  -0.2616   0.09854   0.09681  -0.0419   0.9460   0.0055
  -8.750  -0.2529   0.09624   0.09447  -0.0428   0.9299   0.0056
  -8.500  -0.2435   0.09411   0.09229  -0.0437   0.9140   0.0057
  -8.250  -0.2344   0.09172   0.08985  -0.0449   0.8984   0.0059
  -8.000  -0.2256   0.08905   0.08712  -0.0463   0.8827   0.0062
  -7.750  -0.2169   0.08609   0.08410  -0.0480   0.8669   0.0063
  -7.500  -0.2070   0.08291   0.08086  -0.0505   0.8519   0.0066
  -7.250  -0.1937   0.07857   0.07645  -0.0550   0.8380   0.0071
  -7.000  -0.1772   0.07424   0.07207  -0.0602   0.8256   0.0075
  -6.750  -0.1581   0.07175   0.06951  -0.0636   0.8132   0.0077
  -6.500  -0.1376   0.06933   0.06704  -0.0670   0.8014   0.0080
  -6.250  -0.1155   0.06654   0.06420  -0.0711   0.7916   0.0084
  -5.750  -0.0592   0.05706   0.05459  -0.0858   0.7768   0.0100
  -5.500  -0.0323   0.05473   0.05220  -0.0897   0.7703   0.0102
  -5.250  -0.0040   0.05228   0.04969  -0.0939   0.7641   0.0106
  -5.000   0.0277   0.04913   0.04647  -0.0993   0.7577   0.0116
  -4.500   0.1015   0.04128   0.03843  -0.1125   0.7487   0.0131
  -4.250   0.1331   0.03920   0.03628  -0.1159   0.7438   0.0136
  -4.000   0.1685   0.03639   0.03337  -0.1204   0.7389   0.0147
  -3.750   0.2187   0.03040   0.02712  -0.1290   0.7353   0.0161
  -3.500   0.2477   0.02924   0.02591  -0.1306   0.7313   0.0164
  -3.250   0.2778   0.02793   0.02453  -0.1323   0.7270   0.0169
  -3.000   0.3117   0.02583   0.02229  -0.1348   0.7231   0.0176
  -2.750   0.3477   0.02326   0.01956  -0.1376   0.7192   0.0183
  -2.250   0.4245   0.01638   0.01203  -0.1430   0.7097   0.0204
  -2.000   0.4540   0.01555   0.01108  -0.1437   0.7027   0.0206
  -1.750   0.4838   0.01461   0.00999  -0.1444   0.6940   0.0209
  -1.500   0.5143   0.01353   0.00874  -0.1451   0.6867   0.0212
  -1.250   0.5450   0.01243   0.00743  -0.1458   0.6799   0.0213
  -1.000   0.5745   0.01178   0.00664  -0.1462   0.6733   0.0217
  -0.750   0.6047   0.01090   0.00558  -0.1467   0.6658   0.0218
  -0.500   0.6342   0.01021   0.00471  -0.1470   0.6568   0.0219
  -0.250   0.6630   0.00973   0.00408  -0.1472   0.6411   0.0224
   0.000   0.6907   0.00948   0.00361  -0.1471   0.6042   0.0229
   0.250   0.7162   0.00962   0.00336  -0.1468   0.5303   0.0235
   0.500   0.7422   0.00977   0.00323  -0.1465   0.4778   0.0239
   0.750   0.7687   0.00986   0.00311  -0.1464   0.4347   0.0242
   1.000   0.7953   0.00995   0.00302  -0.1462   0.3992   0.0244
   1.250   0.8221   0.01001   0.00293  -0.1461   0.3711   0.0246
   1.500   0.8489   0.01011   0.00295  -0.1460   0.3516   0.0248
   2.000   0.9040   0.01001   0.00275  -0.1460   0.3296   0.0252
   2.250   0.9317   0.00992   0.00264  -0.1460   0.3222   0.0254
   2.500   0.9595   0.00985   0.00256  -0.1461   0.3154   0.0259
   2.750   0.9868   0.00991   0.00257  -0.1460   0.3065   0.0267
   3.000   1.0140   0.00997   0.00263  -0.1459   0.2981   0.0277
   3.250   1.0411   0.01006   0.00271  -0.1458   0.2917   0.0288
   3.500   1.0683   0.01013   0.00278  -0.1457   0.2860   0.0296
   3.750   1.0950   0.01026   0.00288  -0.1456   0.2771   0.0304
   4.000   1.1218   0.01037   0.00300  -0.1454   0.2690   0.0313
   4.250   1.1481   0.01053   0.00313  -0.1452   0.2587   0.0323
   4.500   1.1746   0.01067   0.00326  -0.1450   0.2493   0.0327
   4.750   1.2006   0.01086   0.00341  -0.1447   0.2359   0.0352
   5.000   1.2262   0.01108   0.00362  -0.1444   0.2183   0.0996
   5.500   1.2673   0.01135   0.00479  -0.1426   0.1208   1.0000
   5.750   1.2916   0.01174   0.00511  -0.1421   0.1075   1.0000
   6.000   1.3161   0.01208   0.00541  -0.1416   0.0967   1.0000
   6.250   1.3402   0.01246   0.00572  -0.1410   0.0857   1.0000
   6.500   1.3639   0.01287   0.00606  -0.1404   0.0722   1.0000
   6.750   1.3873   0.01329   0.00642  -0.1398   0.0606   1.0000
   7.000   1.4113   0.01364   0.00674  -0.1392   0.0552   1.0000
   7.250   1.4347   0.01403   0.00711  -0.1385   0.0488   1.0000
   7.500   1.4580   0.01442   0.00749  -0.1379   0.0428   1.0000
   7.750   1.4806   0.01487   0.00791  -0.1371   0.0360   1.0000
   8.000   1.5002   0.01561   0.00852  -0.1359   0.0197   1.0000
   8.250   1.5209   0.01622   0.00911  -0.1348   0.0139   1.0000
   8.500   1.5422   0.01672   0.00963  -0.1338   0.0114   1.0000
   8.750   1.5633   0.01721   0.01016  -0.1328   0.0101   1.0000
   9.000   1.5834   0.01779   0.01076  -0.1317   0.0088   1.0000
   9.250   1.6035   0.01831   0.01133  -0.1305   0.0081   1.0000
   9.500   1.6233   0.01884   0.01190  -0.1293   0.0075   1.0000
   9.750   1.6422   0.01940   0.01251  -0.1280   0.0070   1.0000
  10.000   1.6599   0.02004   0.01319  -0.1265   0.0064   1.0000
  10.250   1.6754   0.02080   0.01400  -0.1246   0.0058   1.0000
  10.500   1.6914   0.02141   0.01467  -0.1228   0.0056   1.0000
  10.750   1.7050   0.02204   0.01536  -0.1206   0.0053   1.0000
  11.000   1.7173   0.02274   0.01613  -0.1182   0.0050   1.0000
  11.250   1.7291   0.02351   0.01698  -0.1159   0.0048   1.0000
  11.500   1.7400   0.02437   0.01789  -0.1135   0.0046   1.0000
  11.750   1.7501   0.02531   0.01891  -0.1111   0.0044   1.0000
  12.000   1.7589   0.02638   0.02005  -0.1087   0.0041   1.0000
  12.250   1.7653   0.02769   0.02144  -0.1061   0.0039   1.0000
  12.500   1.7722   0.02899   0.02284  -0.1037   0.0038   1.0000
  12.750   1.7802   0.03025   0.02418  -0.1017   0.0037   1.0000
  13.000   1.7870   0.03164   0.02568  -0.0996   0.0036   1.0000
  13.250   1.7930   0.03316   0.02730  -0.0976   0.0035   1.0000
  13.500   1.7978   0.03484   0.02907  -0.0956   0.0034   1.0000
  13.750   1.8018   0.03663   0.03097  -0.0937   0.0034   1.0000
  14.000   1.8049   0.03859   0.03303  -0.0920   0.0033   1.0000
  14.250   1.8072   0.04068   0.03523  -0.0904   0.0032   1.0000
  14.500   1.8084   0.04295   0.03760  -0.0889   0.0031   1.0000
  14.750   1.8092   0.04533   0.04008  -0.0875   0.0030   1.0000
  15.000   1.8089   0.04789   0.04275  -0.0863   0.0029   1.0000
  15.250   1.8070   0.05070   0.04566  -0.0852   0.0029   1.0000
  15.500   1.8044   0.05368   0.04876  -0.0843   0.0028   1.0000
  15.750   1.7997   0.05706   0.05225  -0.0836   0.0027   1.0000
  16.000   1.7935   0.06076   0.05606  -0.0832   0.0027   1.0000
  16.250   1.7850   0.06491   0.06034  -0.0830   0.0026   1.0000
  16.500   1.7746   0.06957   0.06513  -0.0832   0.0026   1.0000
  16.750   1.7618   0.07487   0.07057  -0.0839   0.0025   1.0000
  17.000   1.7466   0.08077   0.07662  -0.0852   0.0025   1.0000
  17.250   1.7300   0.08722   0.08323  -0.0869   0.0025   1.0000
  17.500   1.7115   0.09427   0.09043  -0.0892   0.0024   1.0000
  17.750   1.6927   0.10158   0.09789  -0.0919   0.0024   1.0000
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