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GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.35 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe304-il-1000000.txt
Download as CSV file: xf-goe304-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 304 (FRIEDRICHSHAFEN G02) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1380   0.08644   0.08470  -0.0634   0.9615   0.0210
  -8.000  -0.1285   0.08401   0.08225  -0.0645   0.9462   0.0214
  -7.750  -0.1205   0.08160   0.07979  -0.0655   0.9290   0.0218
  -7.500  -0.1124   0.07910   0.07723  -0.0667   0.9115   0.0223
  -7.250  -0.1009   0.07552   0.07357  -0.0721   0.8929   0.0233
  -7.000  -0.0821   0.07103   0.06899  -0.0811   0.8759   0.0235
  -6.750  -0.0667   0.06686   0.06475  -0.0851   0.8621   0.0236
  -6.500  -0.0520   0.06463   0.06247  -0.0852   0.8497   0.0238
  -6.250  -0.0342   0.06232   0.06011  -0.0870   0.8374   0.0239
  -6.000  -0.0144   0.05996   0.05768  -0.0896   0.8252   0.0242
  -5.750   0.0074   0.05747   0.05512  -0.0927   0.8131   0.0245
  -5.500   0.0311   0.05482   0.05241  -0.0963   0.8019   0.0249
  -5.250   0.0565   0.05199   0.04949  -0.1003   0.7911   0.0256
  -5.000   0.1043   0.04584   0.04314  -0.1124   0.7809   0.0271
  -4.750   0.1296   0.04161   0.03880  -0.1162   0.7715   0.0274
  -4.500   0.1525   0.03982   0.03694  -0.1174   0.7616   0.0276
  -4.250   0.1774   0.03805   0.03511  -0.1188   0.7523   0.0278
  -4.000   0.2039   0.03621   0.03317  -0.1205   0.7430   0.0282
  -3.750   0.2324   0.03414   0.03102  -0.1226   0.7341   0.0289
  -3.500   0.2629   0.03170   0.02842  -0.1248   0.7254   0.0301
  -3.250   0.3040   0.02540   0.02171  -0.1294   0.7182   0.0315
  -3.000   0.3292   0.02431   0.02055  -0.1299   0.7095   0.0318
  -2.750   0.3557   0.02333   0.01950  -0.1303   0.7016   0.0322
  -2.500   0.3829   0.02217   0.01822  -0.1308   0.6935   0.0327
  -2.250   0.4173   0.01956   0.01518  -0.1313   0.6866   0.0358
  -2.000   0.4443   0.01673   0.01211  -0.1321   0.6792   0.0364
  -1.750   0.4714   0.01599   0.01129  -0.1323   0.6722   0.0367
  -1.500   0.4991   0.01533   0.01056  -0.1324   0.6649   0.0372
  -1.000   0.5575   0.01079   0.00518  -0.1323   0.6519   0.0335
  -0.750   0.5856   0.01016   0.00440  -0.1322   0.6448   0.0339
  -0.500   0.6135   0.00971   0.00383  -0.1321   0.6382   0.0344
  -0.250   0.6416   0.00937   0.00341  -0.1320   0.6310   0.0350
   0.000   0.6692   0.00921   0.00316  -0.1318   0.6223   0.0356
   0.250   0.6967   0.00884   0.00275  -0.1316   0.6112   0.0367
   0.500   0.7242   0.00878   0.00267  -0.1314   0.5987   0.0377
   0.750   0.7515   0.00871   0.00255  -0.1312   0.5868   0.0387
   1.000   0.7791   0.00863   0.00243  -0.1310   0.5773   0.0398
   1.250   0.8069   0.00859   0.00237  -0.1309   0.5695   0.0408
   1.500   0.8345   0.00842   0.00219  -0.1308   0.5608   0.0423
   1.750   0.8621   0.00841   0.00217  -0.1306   0.5522   0.0441
   2.000   0.8894   0.00844   0.00218  -0.1304   0.5417   0.0462
   2.250   0.9168   0.00841   0.00212  -0.1303   0.5300   0.0484
   2.500   0.9439   0.00844   0.00212  -0.1301   0.5166   0.0511
   2.750   0.9706   0.00852   0.00216  -0.1298   0.5020   0.0538
   3.000   0.9974   0.00858   0.00218  -0.1295   0.4884   0.0585
   3.500   1.0507   0.00876   0.00231  -0.1290   0.4612   0.0727
   3.750   1.0741   0.00739   0.00269  -0.1286   0.4486   1.0000
   4.000   1.1003   0.00759   0.00280  -0.1283   0.4348   1.0000
   4.250   1.1263   0.00780   0.00293  -0.1279   0.4208   1.0000
   4.500   1.1521   0.00802   0.00307  -0.1275   0.4062   1.0000
   4.750   1.1776   0.00827   0.00322  -0.1271   0.3902   1.0000
   5.000   1.2029   0.00852   0.00339  -0.1266   0.3729   1.0000
   5.250   1.2279   0.00879   0.00358  -0.1261   0.3552   1.0000
   5.500   1.2524   0.00911   0.00379  -0.1256   0.3346   1.0000
   5.750   1.2758   0.00950   0.00405  -0.1248   0.3109   1.0000
   6.000   1.2994   0.00986   0.00431  -0.1241   0.2886   1.0000
   6.250   1.3223   0.01028   0.00460  -0.1233   0.2668   1.0000
   6.500   1.3450   0.01069   0.00490  -0.1225   0.2472   1.0000
   6.750   1.3680   0.01107   0.00520  -0.1217   0.2314   1.0000
   7.250   1.4138   0.01180   0.00580  -0.1202   0.2062   1.0000
   7.500   1.4363   0.01217   0.00612  -0.1194   0.1940   1.0000
   7.750   1.4584   0.01255   0.00645  -0.1185   0.1830   1.0000
   8.000   1.4799   0.01296   0.00680  -0.1175   0.1723   1.0000
   8.250   1.5016   0.01333   0.00713  -0.1166   0.1618   1.0000
   8.500   1.5223   0.01376   0.00751  -0.1155   0.1498   1.0000
   8.750   1.5417   0.01425   0.00793  -0.1141   0.1361   1.0000
   9.000   1.5589   0.01484   0.00842  -0.1125   0.1195   1.0000
   9.250   1.5748   0.01546   0.00894  -0.1106   0.1058   1.0000
   9.500   1.5904   0.01597   0.00943  -0.1087   0.0991   1.0000
   9.750   1.6052   0.01654   0.00997  -0.1066   0.0934   1.0000
  10.000   1.6220   0.01700   0.01046  -0.1049   0.0906   1.0000
  10.250   1.6380   0.01751   0.01099  -0.1031   0.0882   1.0000
  10.500   1.6528   0.01810   0.01159  -0.1012   0.0855   1.0000
  10.750   1.6663   0.01878   0.01228  -0.0992   0.0823   1.0000
  11.000   1.6820   0.01934   0.01289  -0.0976   0.0804   1.0000
  11.250   1.6984   0.01987   0.01347  -0.0962   0.0788   1.0000
  11.500   1.7131   0.02052   0.01416  -0.0945   0.0766   1.0000
  11.750   1.7260   0.02130   0.01495  -0.0928   0.0741   1.0000
  12.000   1.7370   0.02224   0.01592  -0.0908   0.0709   1.0000
  12.250   1.7529   0.02286   0.01660  -0.0895   0.0688   1.0000
  12.500   1.7663   0.02367   0.01743  -0.0881   0.0649   1.0000
  12.750   1.7767   0.02473   0.01848  -0.0863   0.0595   1.0000
  13.000   1.7825   0.02616   0.01984  -0.0843   0.0473   1.0000
  13.250   1.7816   0.02817   0.02177  -0.0818   0.0370   1.0000
  13.500   1.7837   0.03006   0.02366  -0.0797   0.0325   1.0000
  13.750   1.7871   0.03188   0.02553  -0.0779   0.0299   1.0000
  14.000   1.7899   0.03383   0.02753  -0.0763   0.0278   1.0000
  14.250   1.7948   0.03565   0.02941  -0.0749   0.0264   1.0000
  14.500   1.7966   0.03780   0.03161  -0.0735   0.0250   1.0000
  14.750   1.7964   0.04021   0.03409  -0.0721   0.0236   1.0000
  15.000   1.8012   0.04220   0.03615  -0.0711   0.0228   1.0000
  15.250   1.8035   0.04449   0.03852  -0.0702   0.0220   1.0000
  15.500   1.8035   0.04709   0.04119  -0.0692   0.0211   1.0000
  15.750   1.8004   0.05011   0.04428  -0.0684   0.0203   1.0000
  16.000   1.7983   0.05311   0.04737  -0.0677   0.0197   1.0000
  16.250   1.7995   0.05578   0.05012  -0.0673   0.0192   1.0000
  16.500   1.7989   0.05870   0.05314  -0.0669   0.0187   1.0000
  16.750   1.7966   0.06189   0.05642  -0.0666   0.0182   1.0000
  17.000   1.7926   0.06539   0.05999  -0.0664   0.0177   1.0000
  17.250   1.7860   0.06927   0.06396  -0.0665   0.0172   1.0000
  17.500   1.7752   0.07379   0.06858  -0.0666   0.0168   1.0000
  17.750   1.7660   0.07822   0.07311  -0.0670   0.0164   1.0000
  18.000   1.7617   0.08201   0.07701  -0.0674   0.0161   1.0000
  18.250   1.7552   0.08618   0.08128  -0.0680   0.0159   1.0000
  18.500   1.7473   0.09058   0.08578  -0.0687   0.0156   1.0000
  18.750   1.7382   0.09524   0.09054  -0.0696   0.0153   1.0000
  19.000   1.7281   0.10012   0.09553  -0.0707   0.0151   1.0000
  19.250   1.7170   0.10525   0.10076  -0.0720   0.0149   1.0000
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