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GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il)
Reynolds number: 200,000
Max Cl/Cd: 88.78 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe304-il-200000.txt
Download as CSV file: xf-goe304-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2610   0.11104   0.10753  -0.0301   1.0000   0.0379
  -8.750  -0.2713   0.11021   0.10678  -0.0271   1.0000   0.0382
  -8.500  -0.2756   0.10880   0.10542  -0.0259   0.9992   0.0387
  -8.250  -0.2555   0.10501   0.10162  -0.0314   0.9954   0.0398
  -8.000  -0.2385   0.10230   0.09890  -0.0407   0.9879   0.0408
  -7.750  -0.2194   0.09842   0.09501  -0.0500   0.9798   0.0412
  -7.500  -0.1983   0.09375   0.09034  -0.0490   0.9781   0.0416
  -7.250  -0.1750   0.08989   0.08647  -0.0526   0.9736   0.0423
  -7.000  -0.1482   0.08600   0.08256  -0.0583   0.9691   0.0432
  -6.750  -0.1242   0.08241   0.07896  -0.0638   0.9613   0.0443
  -6.500  -0.0896   0.07824   0.07476  -0.0732   0.9574   0.0460
  -6.250  -0.0446   0.07385   0.07023  -0.0923   0.9456   0.0472
  -6.000  -0.0261   0.06992   0.06633  -0.0907   0.9433   0.0478
  -5.750  -0.0058   0.06691   0.06332  -0.0918   0.9360   0.0486
  -5.500   0.0219   0.06369   0.06008  -0.0961   0.9294   0.0498
  -5.250   0.0511   0.06049   0.05682  -0.1011   0.9221   0.0514
  -5.000   0.1112   0.05634   0.05231  -0.1183   0.9122   0.0543
  -4.750   0.1239   0.05311   0.04915  -0.1167   0.9040   0.0548
  -4.500   0.1431   0.05051   0.04655  -0.1167   0.8964   0.0556
  -4.250   0.1655   0.04820   0.04420  -0.1178   0.8875   0.0569
  -4.000   0.2224   0.04595   0.04143  -0.1278   0.8791   0.0627
  -3.750   0.2381   0.04236   0.03791  -0.1275   0.8698   0.0634
  -3.500   0.2588   0.04006   0.03561  -0.1275   0.8620   0.0644
  -3.250   0.2815   0.03824   0.03374  -0.1279   0.8523   0.0661
  -3.000   0.3122   0.03623   0.03157  -0.1297   0.8448   0.0698
  -2.750   0.3467   0.03374   0.02876  -0.1325   0.8354   0.0742
  -2.500   0.3708   0.03201   0.02699  -0.1327   0.8279   0.0762
  -2.250   0.3976   0.03063   0.02551  -0.1332   0.8186   0.0806
  -2.000   0.4293   0.02873   0.02332  -0.1346   0.8112   0.0872
  -1.750   0.4541   0.02757   0.02214  -0.1346   0.8022   0.0920
  -1.500   0.4855   0.02608   0.02034  -0.1355   0.7948   0.1006
  -1.250   0.5109   0.02498   0.01921  -0.1355   0.7862   0.1058
  -1.000   0.5402   0.02376   0.01777  -0.1359   0.7785   0.1164
  -0.750   0.5684   0.02292   0.01675  -0.1361   0.7705   0.1302
  -0.500   0.5959   0.02208   0.01578  -0.1362   0.7624   0.1460
  -0.250   0.6223   0.02114   0.01478  -0.1362   0.7548   0.1633
   0.000   0.6478   0.02028   0.01394  -0.1361   0.7464   0.1852
   0.250   0.6897   0.01842   0.01109  -0.1353   0.7402   0.0963
   0.500   0.7186   0.01708   0.00949  -0.1348   0.7316   0.0818
   1.000   0.7744   0.01592   0.00806  -0.1340   0.7156   0.0811
   1.250   0.8031   0.01549   0.00748  -0.1337   0.7085   0.0820
   1.500   0.8293   0.01516   0.00714  -0.1331   0.6990   0.0830
   1.750   0.8574   0.01485   0.00672  -0.1327   0.6907   0.0850
   2.000   0.8827   0.01446   0.00644  -0.1319   0.6785   0.0908
   2.250   0.9087   0.01426   0.00622  -0.1312   0.6666   0.0958
   2.500   0.9358   0.01403   0.00596  -0.1308   0.6568   0.1031
   2.750   0.9616   0.01393   0.00592  -0.1302   0.6462   0.1165
   3.000   0.9884   0.01370   0.00589  -0.1299   0.6371   0.1930
   3.250   1.0135   0.01243   0.00588  -0.1290   0.6270   1.0000
   3.500   1.0391   0.01259   0.00594  -0.1284   0.6158   1.0000
   3.750   1.0654   0.01274   0.00597  -0.1278   0.6054   1.0000
   4.000   1.0905   0.01288   0.00607  -0.1271   0.5935   1.0000
   4.250   1.1156   0.01305   0.00620  -0.1264   0.5816   1.0000
   4.500   1.1409   0.01322   0.00630  -0.1258   0.5700   1.0000
   4.750   1.1657   0.01339   0.00639  -0.1251   0.5575   1.0000
   5.000   1.1899   0.01356   0.00657  -0.1242   0.5440   1.0000
   5.250   1.2141   0.01376   0.00676  -0.1235   0.5308   1.0000
   5.500   1.2381   0.01398   0.00694  -0.1227   0.5174   1.0000
   5.750   1.2617   0.01422   0.00714  -0.1218   0.5032   1.0000
   6.000   1.2846   0.01447   0.00736  -0.1208   0.4876   1.0000
   6.250   1.3065   0.01476   0.00760  -0.1196   0.4697   1.0000
   6.500   1.3278   0.01508   0.00788  -0.1184   0.4511   1.0000
   6.750   1.3489   0.01546   0.00820  -0.1172   0.4331   1.0000
   7.000   1.3690   0.01588   0.00857  -0.1158   0.4140   1.0000
   7.250   1.3881   0.01635   0.00897  -0.1143   0.3943   1.0000
   7.500   1.4066   0.01686   0.00942  -0.1127   0.3740   1.0000
   7.750   1.4242   0.01740   0.00991  -0.1110   0.3528   1.0000
   8.000   1.4404   0.01802   0.01046  -0.1091   0.3323   1.0000
   8.250   1.4554   0.01871   0.01106  -0.1071   0.3134   1.0000
   8.500   1.4696   0.01943   0.01170  -0.1049   0.2962   1.0000
   8.750   1.4833   0.02018   0.01239  -0.1027   0.2806   1.0000
   9.000   1.4953   0.02091   0.01311  -0.1003   0.2666   1.0000
   9.250   1.5071   0.02169   0.01388  -0.0978   0.2537   1.0000
   9.500   1.5182   0.02254   0.01472  -0.0954   0.2414   1.0000
   9.750   1.5277   0.02350   0.01563  -0.0929   0.2294   1.0000
  10.000   1.5355   0.02459   0.01664  -0.0902   0.2177   1.0000
  10.250   1.5451   0.02557   0.01768  -0.0880   0.2054   1.0000
  10.500   1.5536   0.02668   0.01882  -0.0857   0.1938   1.0000
  10.750   1.5604   0.02796   0.02008  -0.0833   0.1837   1.0000
  11.000   1.5673   0.02927   0.02137  -0.0811   0.1742   1.0000
  11.250   1.5758   0.03053   0.02271  -0.0792   0.1653   1.0000
  11.500   1.5809   0.03206   0.02418  -0.0771   0.1580   1.0000
  11.750   1.5905   0.03332   0.02557  -0.0756   0.1508   1.0000
  12.000   1.5962   0.03489   0.02712  -0.0738   0.1449   1.0000
  12.250   1.6043   0.03634   0.02867  -0.0723   0.1395   1.0000
  12.500   1.6116   0.03787   0.03029  -0.0709   0.1342   1.0000
  12.750   1.6154   0.03973   0.03211  -0.0693   0.1296   1.0000
  13.000   1.6236   0.04127   0.03384  -0.0681   0.1247   1.0000
  13.250   1.6284   0.04313   0.03577  -0.0670   0.1200   1.0000
  13.500   1.6310   0.04523   0.03788  -0.0657   0.1157   1.0000
  13.750   1.6361   0.04718   0.04000  -0.0647   0.1107   1.0000
  14.000   1.6364   0.04960   0.04246  -0.0637   0.1061   1.0000
  14.250   1.6375   0.05205   0.04501  -0.0629   0.1012   1.0000
  14.500   1.6369   0.05478   0.04783  -0.0622   0.0959   1.0000
  14.750   1.6327   0.05790   0.05098  -0.0614   0.0908   1.0000
  15.000   1.6296   0.06113   0.05435  -0.0611   0.0849   1.0000
  15.250   1.6219   0.06484   0.05805  -0.0605   0.0796   1.0000
  15.500   1.6165   0.06857   0.06194  -0.0605   0.0738   1.0000
  15.750   1.6079   0.07261   0.06600  -0.0604   0.0692   1.0000
  16.000   1.6030   0.07653   0.07008  -0.0608   0.0642   1.0000
  16.250   1.5947   0.08075   0.07428  -0.0611   0.0609   1.0000
  16.500   1.5908   0.08468   0.07840  -0.0616   0.0571   1.0000
  16.750   1.5850   0.08887   0.08267  -0.0624   0.0543   1.0000
  17.000   1.5778   0.09319   0.08700  -0.0631   0.0521   1.0000
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