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GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il)
Reynolds number: 500,000
Max Cl/Cd: 122.78 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe304-il-500000.txt
Download as CSV file: xf-goe304-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2610   0.11637   0.11398  -0.0365   1.0000   0.0237
 -10.000  -0.2602   0.11438   0.11203  -0.0349   1.0000   0.0238
  -9.750  -0.2630   0.11287   0.11056  -0.0329   1.0000   0.0240
  -9.500  -0.2461   0.10942   0.10711  -0.0362   0.9983   0.0243
  -9.250  -0.2289   0.10594   0.10363  -0.0399   0.9962   0.0247
  -9.000  -0.2112   0.10240   0.10008  -0.0439   0.9943   0.0253
  -8.750  -0.1940   0.09880   0.09647  -0.0481   0.9911   0.0264
  -8.500  -0.1770   0.09480   0.09246  -0.0572   0.9858   0.0271
  -8.250  -0.1605   0.09057   0.08823  -0.0663   0.9789   0.0272
  -8.000  -0.1409   0.08666   0.08431  -0.0656   0.9767   0.0273
  -7.750  -0.1211   0.08335   0.08100  -0.0679   0.9723   0.0276
  -7.500  -0.1053   0.08049   0.07814  -0.0701   0.9631   0.0278
  -7.250  -0.0897   0.07769   0.07533  -0.0728   0.9530   0.0282
  -7.000  -0.0742   0.07491   0.07253  -0.0757   0.9416   0.0288
  -6.750  -0.0599   0.07218   0.06977  -0.0783   0.9277   0.0295
  -6.500  -0.0422   0.06903   0.06656  -0.0829   0.9134   0.0307
  -6.250  -0.0041   0.06355   0.06091  -0.0995   0.8971   0.0312
  -6.000   0.0066   0.06070   0.05804  -0.0982   0.8859   0.0314
  -5.750   0.0218   0.05839   0.05568  -0.0980   0.8751   0.0316
  -5.500   0.0402   0.05608   0.05332  -0.0992   0.8632   0.0319
  -5.250   0.0617   0.05368   0.05085  -0.1015   0.8516   0.0323
  -5.000   0.0856   0.05119   0.04827  -0.1044   0.8408   0.0330
  -4.750   0.1126   0.04844   0.04542  -0.1081   0.8295   0.0342
  -4.500   0.1641   0.04237   0.03903  -0.1199   0.8192   0.0360
  -4.000   0.2058   0.03857   0.03513  -0.1208   0.7991   0.0366
  -3.750   0.2309   0.03673   0.03319  -0.1221   0.7900   0.0371
  -3.500   0.2585   0.03473   0.03108  -0.1238   0.7804   0.0380
  -3.250   0.3050   0.03021   0.02603  -0.1289   0.7725   0.0412
  -3.000   0.3275   0.02835   0.02417  -0.1294   0.7633   0.0416
  -2.750   0.3523   0.02701   0.02276  -0.1299   0.7549   0.0420
  -2.500   0.3786   0.02570   0.02135  -0.1304   0.7462   0.0428
  -2.250   0.4067   0.02425   0.01976  -0.1310   0.7384   0.0442
  -2.000   0.4414   0.02138   0.01638  -0.1321   0.7305   0.0477
  -1.750   0.4673   0.02028   0.01523  -0.1323   0.7230   0.0483
  -1.500   0.4943   0.01936   0.01425  -0.1325   0.7148   0.0493
  -1.250   0.5241   0.01878   0.01337  -0.1324   0.7076   0.0536
  -1.000   0.5522   0.01703   0.01143  -0.1327   0.6999   0.0556
  -0.750   0.5793   0.01629   0.01062  -0.1328   0.6927   0.0569
  -0.500   0.6073   0.01565   0.00987  -0.1328   0.6852   0.0595
  -0.250   0.6359   0.01479   0.00876  -0.1327   0.6778   0.0647
   0.000   0.6672   0.01286   0.00622  -0.1320   0.6714   0.0473
   0.250   0.6948   0.01194   0.00523  -0.1319   0.6638   0.0480
   0.500   0.7224   0.01150   0.00468  -0.1317   0.6567   0.0484
   0.750   0.7498   0.01111   0.00428  -0.1314   0.6474   0.0490
   1.000   0.7767   0.01086   0.00398  -0.1310   0.6365   0.0500
   1.250   0.8034   0.01067   0.00372  -0.1306   0.6249   0.0513
   1.500   0.8306   0.01053   0.00356  -0.1303   0.6141   0.0532
   1.750   0.8574   0.01033   0.00332  -0.1300   0.6045   0.0555
   2.000   0.8844   0.01018   0.00319  -0.1297   0.5943   0.0579
   2.250   0.9115   0.01012   0.00313  -0.1295   0.5855   0.0607
   2.500   0.9385   0.01005   0.00304  -0.1292   0.5764   0.0644
   2.750   0.9656   0.01002   0.00304  -0.1290   0.5673   0.0699
   3.000   0.9922   0.01004   0.00303  -0.1286   0.5574   0.0765
   3.250   1.0190   0.01004   0.00307  -0.1283   0.5453   0.0924
   3.500   1.0425   0.00859   0.00334  -0.1278   0.5329   1.0000
   3.750   1.0684   0.00877   0.00341  -0.1273   0.5200   1.0000
   4.000   1.0941   0.00896   0.00350  -0.1268   0.5069   1.0000
   4.250   1.1199   0.00913   0.00362  -0.1264   0.4934   1.0000
   4.500   1.1455   0.00933   0.00376  -0.1259   0.4799   1.0000
   4.750   1.1708   0.00955   0.00392  -0.1254   0.4661   1.0000
   5.000   1.1957   0.00979   0.00409  -0.1249   0.4519   1.0000
   5.250   1.2203   0.01005   0.00429  -0.1242   0.4370   1.0000
   5.500   1.2445   0.01033   0.00450  -0.1236   0.4208   1.0000
   5.750   1.2682   0.01064   0.00473  -0.1229   0.4026   1.0000
   6.000   1.2916   0.01097   0.00499  -0.1221   0.3842   1.0000
   6.250   1.3147   0.01132   0.00526  -0.1213   0.3657   1.0000
   6.500   1.3370   0.01172   0.00556  -0.1204   0.3456   1.0000
   6.750   1.3587   0.01215   0.00589  -0.1194   0.3235   1.0000
   7.000   1.3798   0.01261   0.00626  -0.1183   0.3012   1.0000
   7.500   1.4201   0.01363   0.00708  -0.1159   0.2622   1.0000
   7.750   1.4400   0.01414   0.00753  -0.1146   0.2465   1.0000
   8.000   1.4592   0.01466   0.00798  -0.1133   0.2325   1.0000
   8.250   1.4781   0.01519   0.00845  -0.1119   0.2189   1.0000
   8.500   1.4968   0.01569   0.00892  -0.1105   0.2064   1.0000
   8.750   1.5150   0.01620   0.00940  -0.1090   0.1955   1.0000
   9.000   1.5303   0.01675   0.00992  -0.1070   0.1848   1.0000
   9.250   1.5453   0.01734   0.01047  -0.1049   0.1736   1.0000
   9.500   1.5610   0.01790   0.01101  -0.1031   0.1628   1.0000
   9.750   1.5751   0.01855   0.01165  -0.1011   0.1517   1.0000
  10.000   1.5881   0.01929   0.01235  -0.0990   0.1402   1.0000
  10.250   1.6000   0.02011   0.01312  -0.0968   0.1289   1.0000
  10.500   1.6126   0.02090   0.01389  -0.0948   0.1200   1.0000
  10.750   1.6245   0.02176   0.01476  -0.0928   0.1132   1.0000
  11.000   1.6355   0.02270   0.01569  -0.0908   0.1073   1.0000
  11.250   1.6463   0.02369   0.01670  -0.0889   0.1027   1.0000
  11.500   1.6577   0.02466   0.01771  -0.0871   0.0990   1.0000
  11.750   1.6669   0.02582   0.01889  -0.0852   0.0955   1.0000
  12.000   1.6744   0.02716   0.02026  -0.0833   0.0921   1.0000
  12.250   1.6863   0.02819   0.02138  -0.0819   0.0897   1.0000
  12.500   1.6954   0.02947   0.02272  -0.0804   0.0866   1.0000
  12.750   1.7010   0.03110   0.02438  -0.0786   0.0833   1.0000
  13.000   1.7076   0.03267   0.02601  -0.0771   0.0802   1.0000
  13.250   1.7190   0.03387   0.02731  -0.0760   0.0769   1.0000
  13.500   1.7246   0.03563   0.02911  -0.0747   0.0728   1.0000
  13.750   1.7319   0.03726   0.03081  -0.0735   0.0683   1.0000
  14.000   1.7377   0.03906   0.03262  -0.0724   0.0612   1.0000
  14.250   1.7417   0.04108   0.03462  -0.0713   0.0505   1.0000
  14.500   1.7388   0.04386   0.03735  -0.0700   0.0425   1.0000
  14.750   1.7338   0.04695   0.04045  -0.0688   0.0382   1.0000
  15.000   1.7300   0.05003   0.04361  -0.0678   0.0356   1.0000
  15.250   1.7227   0.05363   0.04726  -0.0670   0.0336   1.0000
  15.500   1.7187   0.05693   0.05067  -0.0665   0.0322   1.0000
  15.750   1.7140   0.06040   0.05425  -0.0661   0.0309   1.0000
  16.000   1.7068   0.06430   0.05824  -0.0658   0.0299   1.0000
  16.250   1.6962   0.06874   0.06277  -0.0658   0.0289   1.0000
  16.500   1.6833   0.07358   0.06772  -0.0661   0.0281   1.0000
  16.750   1.6788   0.07740   0.07167  -0.0663   0.0274   1.0000
  17.000   1.6719   0.08163   0.07601  -0.0667   0.0266   1.0000
  17.250   1.6635   0.08614   0.08063  -0.0674   0.0260   1.0000
  17.500   1.6534   0.09095   0.08556  -0.0682   0.0254   1.0000
  17.750   1.6413   0.09619   0.09089  -0.0693   0.0249   1.0000
  18.000   1.6275   0.10176   0.09656  -0.0706   0.0244   1.0000
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