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GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 595 AIRFOIL (goe595-il)
Reynolds number: 100,000
Max Cl/Cd: 54.56 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe595-il-100000-n5.txt
Download as CSV file: xf-goe595-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 595 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4041   0.08972   0.08499  -0.0386   1.0000   0.0336
  -8.250  -0.4094   0.08701   0.08236  -0.0375   1.0000   0.0326
  -8.000  -0.4216   0.08433   0.07978  -0.0365   1.0000   0.0324
  -7.750  -0.4361   0.08201   0.07756  -0.0348   1.0000   0.0312
  -7.250  -0.4605   0.07545   0.07112  -0.0345   1.0000   0.0303
  -6.750  -0.4790   0.06223   0.05761  -0.0390   1.0000   0.0253
  -6.500  -0.4685   0.05718   0.05241  -0.0413   0.9967   0.0249
  -6.250  -0.4503   0.05154   0.04648  -0.0450   0.9915   0.0246
  -6.000  -0.4291   0.04606   0.04060  -0.0482   0.9867   0.0243
  -5.750  -0.4089   0.04091   0.03493  -0.0499   0.9812   0.0244
  -5.500  -0.3836   0.03650   0.02987  -0.0515   0.9772   0.0245
  -5.250  -0.3606   0.03314   0.02583  -0.0517   0.9718   0.0257
  -5.000  -0.3345   0.03056   0.02297  -0.0529   0.9679   0.0279
  -4.750  -0.3067   0.02825   0.02021  -0.0533   0.9641   0.0291
  -4.500  -0.2797   0.02621   0.01774  -0.0533   0.9594   0.0303
  -4.250  -0.2485   0.02459   0.01571  -0.0539   0.9558   0.0332
  -4.000  -0.2158   0.02300   0.01382  -0.0549   0.9531   0.0362
  -3.750  -0.1915   0.02182   0.01255  -0.0543   0.9472   0.0387
  -3.500  -0.1608   0.02095   0.01156  -0.0549   0.9429   0.0440
  -3.250  -0.1266   0.02000   0.01055  -0.0563   0.9395   0.0491
  -3.000  -0.1004   0.01944   0.00989  -0.0560   0.9318   0.0560
  -2.750  -0.0632   0.01877   0.00915  -0.0577   0.9265   0.0686
  -2.500  -0.0333   0.01805   0.00848  -0.0580   0.9178   0.0901
  -2.250   0.0045   0.01710   0.00791  -0.0601   0.9121   0.1780
  -2.000   0.0320   0.01642   0.00759  -0.0602   0.9037   0.2922
  -1.750   0.0654   0.01563   0.00734  -0.0615   0.8989   0.4507
  -1.500   0.0936   0.01473   0.00730  -0.0609   0.8947   0.6919
  -1.250   0.2017   0.01435   0.00725  -0.0764   0.9004   1.0000
  -1.000   0.2362   0.01426   0.00696  -0.0777   0.8947   1.0000
  -0.750   0.2626   0.01422   0.00678  -0.0774   0.8856   1.0000
  -0.500   0.2924   0.01416   0.00658  -0.0778   0.8779   1.0000
  -0.250   0.3227   0.01409   0.00638  -0.0782   0.8699   1.0000
   0.000   0.3482   0.01407   0.00627  -0.0777   0.8600   1.0000
   0.250   0.3816   0.01396   0.00607  -0.0786   0.8528   1.0000
   0.500   0.4062   0.01395   0.00599  -0.0778   0.8417   1.0000
   0.750   0.4313   0.01393   0.00592  -0.0771   0.8304   1.0000
   1.000   0.4582   0.01388   0.00583  -0.0767   0.8187   1.0000
   1.250   0.4856   0.01381   0.00571  -0.0764   0.8059   1.0000
   1.500   0.5125   0.01372   0.00558  -0.0758   0.7902   1.0000
   1.750   0.5403   0.01363   0.00546  -0.0754   0.7730   1.0000
   2.000   0.5697   0.01353   0.00529  -0.0753   0.7544   1.0000
   2.250   0.5960   0.01351   0.00522  -0.0746   0.7330   1.0000
   2.500   0.6240   0.01349   0.00514  -0.0743   0.7103   1.0000
   2.750   0.6492   0.01357   0.00516  -0.0735   0.6867   1.0000
   3.000   0.6752   0.01367   0.00521  -0.0728   0.6645   1.0000
   3.250   0.6995   0.01382   0.00531  -0.0719   0.6402   1.0000
   3.500   0.7235   0.01400   0.00546  -0.0710   0.6154   1.0000
   3.750   0.7475   0.01422   0.00561  -0.0701   0.5914   1.0000
   4.000   0.7708   0.01447   0.00581  -0.0691   0.5683   1.0000
   4.250   0.7938   0.01476   0.00607  -0.0680   0.5462   1.0000
   4.500   0.8163   0.01508   0.00635  -0.0669   0.5246   1.0000
   4.750   0.8388   0.01543   0.00666  -0.0658   0.5047   1.0000
   5.000   0.8610   0.01578   0.00702  -0.0647   0.4858   1.0000
   5.250   0.8818   0.01620   0.00741  -0.0633   0.4630   1.0000
   5.500   0.9009   0.01664   0.00780  -0.0617   0.4355   1.0000
   5.750   0.9191   0.01710   0.00821  -0.0599   0.4066   1.0000
   6.000   0.9379   0.01754   0.00865  -0.0583   0.3798   1.0000
   6.250   0.9571   0.01798   0.00915  -0.0568   0.3558   1.0000
   6.500   0.9764   0.01842   0.00965  -0.0552   0.3321   1.0000
   6.750   0.9938   0.01893   0.01015  -0.0535   0.3029   1.0000
   7.000   1.0082   0.01962   0.01070  -0.0512   0.2659   1.0000
   7.250   1.0223   0.02041   0.01138  -0.0491   0.2323   1.0000
   7.500   1.0343   0.02141   0.01219  -0.0467   0.1781   1.0000
   7.750   1.0363   0.02333   0.01341  -0.0432   0.0820   1.0000
   8.000   1.0433   0.02490   0.01481  -0.0403   0.0625   1.0000
   8.250   1.0494   0.02639   0.01632  -0.0371   0.0531   1.0000
   8.500   1.0578   0.02755   0.01765  -0.0342   0.0462   1.0000
   8.750   1.0598   0.02913   0.01931  -0.0307   0.0413   1.0000
   9.000   1.0650   0.03051   0.02087  -0.0276   0.0375   1.0000
   9.250   1.0704   0.03193   0.02240  -0.0248   0.0338   1.0000
   9.500   1.0723   0.03365   0.02417  -0.0220   0.0312   1.0000
   9.750   1.0767   0.03546   0.02609  -0.0193   0.0294   1.0000
  10.000   1.0857   0.03706   0.02787  -0.0173   0.0271   1.0000
  10.250   1.0940   0.03871   0.02966  -0.0154   0.0247   1.0000
  10.500   1.1017   0.04050   0.03158  -0.0137   0.0230   1.0000
  10.750   1.1114   0.04271   0.03383  -0.0122   0.0218   1.0000
  11.000   1.1267   0.04534   0.03661  -0.0110   0.0208   1.0000
  11.250   1.1361   0.04757   0.03915  -0.0095   0.0198   1.0000
  11.500   1.1427   0.05008   0.04194  -0.0079   0.0188   1.0000
  11.750   1.1451   0.05268   0.04483  -0.0063   0.0179   1.0000
  12.000   1.1449   0.05564   0.04806  -0.0048   0.0173   1.0000
  12.250   1.1413   0.05893   0.05163  -0.0035   0.0170   1.0000
  12.500   1.1345   0.06244   0.05541  -0.0025   0.0167   1.0000
  12.750   1.1248   0.06631   0.05955  -0.0019   0.0166   1.0000
  13.000   1.1120   0.07063   0.06412  -0.0019   0.0164   1.0000
  13.250   1.0973   0.07539   0.06913  -0.0026   0.0163   1.0000
  13.500   1.0813   0.08061   0.07459  -0.0041   0.0164   1.0000
  13.750   1.0633   0.08648   0.08070  -0.0064   0.0164   1.0000
  14.000   1.0435   0.09311   0.08754  -0.0096   0.0165   1.0000
  14.250   1.0235   0.10041   0.09504  -0.0137   0.0166   1.0000
  14.500   1.0016   0.10878   0.10360  -0.0188   0.0168   1.0000
  14.750   0.9788   0.11819   0.11316  -0.0249   0.0172   1.0000
  15.000   0.9542   0.12915   0.12423  -0.0319   0.0175   1.0000
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