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GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il)
Reynolds number: 200,000
Max Cl/Cd: 86.12 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe304-il-200000-n5.txt
Download as CSV file: xf-goe304-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1391   0.09113   0.08743  -0.0601   0.9626   0.0353
  -7.750  -0.1254   0.08805   0.08434  -0.0650   0.9513   0.0365
  -7.500  -0.1122   0.08498   0.08125  -0.0728   0.9367   0.0368
  -7.250  -0.0935   0.08127   0.07752  -0.0766   0.9287   0.0370
  -7.000  -0.0796   0.07825   0.07449  -0.0763   0.9191   0.0373
  -6.750  -0.0623   0.07529   0.07152  -0.0783   0.9104   0.0377
  -6.500  -0.0459   0.07253   0.06873  -0.0808   0.8991   0.0382
  -6.250  -0.0280   0.06973   0.06589  -0.0838   0.8881   0.0389
  -6.000  -0.0076   0.06677   0.06287  -0.0876   0.8781   0.0399
  -5.750   0.0268   0.06288   0.05882  -0.0993   0.8652   0.0418
  -5.500   0.0537   0.05921   0.05505  -0.1050   0.8549   0.0420
  -5.250   0.0692   0.05665   0.05246  -0.1045   0.8459   0.0423
  -5.000   0.0878   0.05426   0.05003  -0.1053   0.8358   0.0427
  -4.750   0.1108   0.05179   0.04747  -0.1073   0.8268   0.0434
  -4.500   0.1358   0.04927   0.04487  -0.1101   0.8167   0.0443
  -4.250   0.1644   0.04659   0.04206  -0.1135   0.8078   0.0456
  -4.000   0.2154   0.04226   0.03728  -0.1230   0.7984   0.0477
  -3.750   0.2323   0.04018   0.03523  -0.1225   0.7897   0.0482
  -3.500   0.2548   0.03839   0.03339  -0.1230   0.7804   0.0490
  -3.250   0.2819   0.03637   0.03124  -0.1245   0.7718   0.0498
  -2.750   0.3500   0.02956   0.02376  -0.1296   0.7556   0.0415
  -2.500   0.3769   0.02784   0.02190  -0.1303   0.7471   0.0408
  -2.250   0.4067   0.02579   0.01958  -0.1312   0.7397   0.0406
  -2.000   0.4372   0.02362   0.01706  -0.1319   0.7315   0.0412
  -1.500   0.4948   0.02047   0.01337  -0.1325   0.7164   0.0407
  -1.250   0.5238   0.01907   0.01163  -0.1326   0.7091   0.0407
  -1.000   0.5525   0.01787   0.01012  -0.1326   0.7016   0.0411
  -0.750   0.5809   0.01696   0.00887  -0.1325   0.6941   0.0422
  -0.500   0.6081   0.01658   0.00848  -0.1324   0.6868   0.0434
  -0.250   0.6357   0.01607   0.00783  -0.1322   0.6790   0.0444
   0.000   0.6635   0.01554   0.00711  -0.1319   0.6722   0.0451
   0.250   0.6910   0.01508   0.00655  -0.1317   0.6643   0.0460
   0.500   0.7185   0.01472   0.00603  -0.1314   0.6572   0.0470
   0.750   0.7456   0.01443   0.00572  -0.1311   0.6495   0.0487
   1.000   0.7726   0.01424   0.00554  -0.1308   0.6419   0.0510
   1.250   0.7996   0.01404   0.00530  -0.1305   0.6343   0.0527
   1.500   0.8265   0.01389   0.00511  -0.1301   0.6262   0.0543
   1.750   0.8531   0.01369   0.00496  -0.1298   0.6177   0.0565
   2.000   0.8791   0.01363   0.00487  -0.1294   0.6058   0.0604
   2.250   0.9048   0.01354   0.00478  -0.1288   0.5916   0.0639
   2.500   0.9306   0.01352   0.00474  -0.1283   0.5784   0.0680
   2.750   0.9565   0.01354   0.00474  -0.1278   0.5674   0.0749
   3.000   0.9823   0.01358   0.00477  -0.1273   0.5553   0.0839
   3.250   1.0080   0.01357   0.00485  -0.1268   0.5427   0.1164
   3.750   1.0567   0.01246   0.00513  -0.1254   0.5183   1.0000
   4.000   1.0818   0.01267   0.00526  -0.1248   0.5057   1.0000
   4.250   1.1067   0.01289   0.00542  -0.1242   0.4929   1.0000
   4.500   1.1311   0.01314   0.00559  -0.1235   0.4792   1.0000
   4.750   1.1549   0.01341   0.00578  -0.1227   0.4641   1.0000
   5.000   1.1781   0.01372   0.00600  -0.1218   0.4477   1.0000
   5.250   1.2009   0.01405   0.00624  -0.1208   0.4307   1.0000
   5.500   1.2234   0.01440   0.00652  -0.1199   0.4142   1.0000
   5.750   1.2457   0.01477   0.00682  -0.1189   0.3981   1.0000
   6.000   1.2674   0.01516   0.00715  -0.1178   0.3811   1.0000
   6.250   1.2884   0.01558   0.00750  -0.1167   0.3629   1.0000
   6.500   1.3090   0.01603   0.00788  -0.1155   0.3450   1.0000
   6.750   1.3287   0.01652   0.00831  -0.1142   0.3263   1.0000
   7.000   1.3469   0.01708   0.00877  -0.1126   0.3062   1.0000
   7.250   1.3645   0.01767   0.00927  -0.1110   0.2872   1.0000
   7.500   1.3819   0.01826   0.00981  -0.1094   0.2711   1.0000
   8.000   1.4154   0.01946   0.01094  -0.1060   0.2443   1.0000
   8.250   1.4303   0.02007   0.01154  -0.1040   0.2335   1.0000
   8.500   1.4438   0.02075   0.01221  -0.1018   0.2238   1.0000
   8.750   1.4583   0.02140   0.01288  -0.0999   0.2142   1.0000
   9.000   1.4717   0.02214   0.01361  -0.0978   0.2056   1.0000
   9.250   1.4846   0.02291   0.01440  -0.0958   0.1967   1.0000
   9.500   1.4977   0.02370   0.01523  -0.0938   0.1886   1.0000
   9.750   1.5095   0.02459   0.01613  -0.0918   0.1806   1.0000
  10.000   1.5218   0.02547   0.01705  -0.0900   0.1731   1.0000
  10.250   1.5323   0.02649   0.01809  -0.0880   0.1650   1.0000
  10.500   1.5434   0.02750   0.01915  -0.0862   0.1571   1.0000
  10.750   1.5519   0.02873   0.02039  -0.0843   0.1490   1.0000
  11.000   1.5625   0.02985   0.02157  -0.0826   0.1409   1.0000
  11.250   1.5696   0.03126   0.02299  -0.0808   0.1339   1.0000
  11.500   1.5794   0.03252   0.02432  -0.0793   0.1272   1.0000
  12.000   1.5936   0.03557   0.02746  -0.0762   0.1150   1.0000
  12.250   1.5984   0.03736   0.02926  -0.0747   0.1095   1.0000
  12.500   1.6048   0.03906   0.03103  -0.0734   0.1050   1.0000
  12.750   1.6097   0.04093   0.03296  -0.0721   0.1007   1.0000
  13.000   1.6120   0.04309   0.03515  -0.0708   0.0972   1.0000
  13.250   1.6171   0.04504   0.03721  -0.0697   0.0941   1.0000
  13.500   1.6209   0.04713   0.03940  -0.0687   0.0910   1.0000
  13.750   1.6225   0.04951   0.04185  -0.0677   0.0880   1.0000
  14.000   1.6211   0.05228   0.04466  -0.0669   0.0853   1.0000
  14.250   1.6254   0.05449   0.04701  -0.0662   0.0825   1.0000
  14.500   1.6282   0.05691   0.04957  -0.0655   0.0795   1.0000
  14.750   1.6278   0.05976   0.05251  -0.0650   0.0765   1.0000
  15.000   1.6238   0.06312   0.05592  -0.0647   0.0738   1.0000
  15.250   1.6284   0.06551   0.05849  -0.0644   0.0702   1.0000
  15.500   1.6289   0.06844   0.06155  -0.0642   0.0663   1.0000
  15.750   1.6265   0.07182   0.06502  -0.0642   0.0627   1.0000
  16.000   1.6275   0.07482   0.06817  -0.0643   0.0574   1.0000
  16.250   1.6243   0.07844   0.07188  -0.0646   0.0525   1.0000
  16.750   1.6112   0.08683   0.08040  -0.0657   0.0442   1.0000
  17.000   1.6014   0.09165   0.08527  -0.0667   0.0415   1.0000
  17.250   1.5920   0.09648   0.09020  -0.0677   0.0393   1.0000
  17.500   1.5816   0.10158   0.09540  -0.0690   0.0374   1.0000
  17.750   1.5693   0.10705   0.10097  -0.0706   0.0360   1.0000
  18.000   1.5574   0.11257   0.10660  -0.0724   0.0348   1.0000
  18.250   1.5474   0.11786   0.11203  -0.0742   0.0335   1.0000
  18.500   1.5364   0.12343   0.11773  -0.0764   0.0324   1.0000
  18.750   1.5245   0.12924   0.12365  -0.0788   0.0315   1.0000
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