Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 629 AIRFOIL (goe629-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.69 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe629-il-1000000-n5.txt
Download as CSV file: xf-goe629-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 629 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.9164   0.09116   0.08806  -0.0597   1.0000   0.0149
 -17.250  -0.9938   0.07632   0.07300  -0.0683   1.0000   0.0142
 -17.000  -1.1566   0.04869   0.04487  -0.0853   1.0000   0.0129
 -16.750  -1.2018   0.03783   0.03373  -0.0939   1.0000   0.0128
 -16.500  -1.2203   0.03288   0.02860  -0.0968   1.0000   0.0129
 -16.250  -1.2316   0.02996   0.02556  -0.0968   1.0000   0.0131
 -16.000  -1.2394   0.02799   0.02350  -0.0951   1.0000   0.0132
 -15.750  -1.2460   0.02657   0.02199  -0.0923   1.0000   0.0134
 -15.500  -1.2535   0.02551   0.02085  -0.0884   1.0000   0.0137
 -15.250  -1.2565   0.02464   0.01991  -0.0846   0.9996   0.0139
 -15.000  -1.2397   0.02344   0.01863  -0.0847   0.9973   0.0145
 -14.750  -1.2198   0.02238   0.01751  -0.0849   0.9944   0.0152
 -14.500  -1.1995   0.02141   0.01646  -0.0849   0.9916   0.0161
 -14.250  -1.1781   0.02056   0.01555  -0.0848   0.9887   0.0169
 -14.000  -1.1557   0.01965   0.01459  -0.0850   0.9862   0.0182
 -13.500  -1.1057   0.01798   0.01284  -0.0860   0.9828   0.0222
 -13.250  -1.0855   0.01721   0.01205  -0.0854   0.9792   0.0254
 -13.000  -1.0618   0.01652   0.01134  -0.0853   0.9762   0.0286
 -12.750  -1.0355   0.01590   0.01070  -0.0856   0.9741   0.0320
 -12.500  -1.0074   0.01531   0.01010  -0.0863   0.9724   0.0354
 -12.250  -0.9772   0.01477   0.00954  -0.0873   0.9711   0.0385
 -12.000  -0.9483   0.01434   0.00909  -0.0879   0.9691   0.0413
 -11.750  -0.9240   0.01392   0.00866  -0.0875   0.9648   0.0440
 -11.500  -0.8953   0.01354   0.00827  -0.0880   0.9618   0.0465
 -11.250  -0.8648   0.01319   0.00789  -0.0888   0.9594   0.0486
 -11.000  -0.8336   0.01282   0.00751  -0.0898   0.9571   0.0510
 -10.500  -0.7801   0.01229   0.00692  -0.0896   0.9478   0.0545
 -10.250  -0.7503   0.01196   0.00659  -0.0902   0.9432   0.0569
 -10.000  -0.7236   0.01172   0.00633  -0.0900   0.9373   0.0594
  -9.750  -0.6967   0.01150   0.00607  -0.0899   0.9304   0.0611
  -9.500  -0.6680   0.01130   0.00582  -0.0901   0.9247   0.0625
  -9.250  -0.6437   0.01106   0.00556  -0.0894   0.9169   0.0644
  -9.000  -0.6168   0.01084   0.00532  -0.0892   0.9096   0.0667
  -8.750  -0.5914   0.01067   0.00511  -0.0887   0.9015   0.0686
  -8.500  -0.5648   0.01052   0.00490  -0.0883   0.8929   0.0699
  -8.250  -0.5392   0.01036   0.00469  -0.0878   0.8848   0.0706
  -8.000  -0.5136   0.01018   0.00446  -0.0873   0.8773   0.0717
  -7.750  -0.4882   0.00997   0.00423  -0.0867   0.8708   0.0735
  -7.500  -0.4627   0.00979   0.00403  -0.0862   0.8637   0.0752
  -7.250  -0.4368   0.00964   0.00383  -0.0857   0.8571   0.0766
  -7.000  -0.4110   0.00949   0.00366  -0.0852   0.8494   0.0780
  -6.750  -0.3850   0.00938   0.00348  -0.0847   0.8418   0.0793
  -6.500  -0.3588   0.00926   0.00333  -0.0843   0.8341   0.0803
  -6.250  -0.3329   0.00914   0.00317  -0.0837   0.8264   0.0817
  -6.000  -0.3070   0.00899   0.00300  -0.0832   0.8193   0.0839
  -5.750  -0.2812   0.00886   0.00284  -0.0827   0.8115   0.0861
  -5.500  -0.2551   0.00874   0.00270  -0.0822   0.8042   0.0883
  -5.250  -0.2290   0.00864   0.00257  -0.0818   0.7959   0.0905
  -5.000  -0.2030   0.00854   0.00245  -0.0812   0.7876   0.0932
  -4.750  -0.1772   0.00842   0.00233  -0.0807   0.7781   0.0974
  -4.500  -0.1512   0.00833   0.00222  -0.0802   0.7693   0.1020
  -4.250  -0.1255   0.00823   0.00213  -0.0796   0.7599   0.1090
  -4.000  -0.0992   0.00815   0.00204  -0.0791   0.7509   0.1150
  -3.750  -0.0737   0.00808   0.00196  -0.0785   0.7400   0.1215
  -3.500  -0.0478   0.00804   0.00189  -0.0780   0.7267   0.1270
  -3.250  -0.0224   0.00802   0.00183  -0.0773   0.7113   0.1311
  -3.000   0.0026   0.00799   0.00177  -0.0766   0.6943   0.1366
  -2.750   0.0279   0.00800   0.00172  -0.0759   0.6779   0.1411
  -2.500   0.0534   0.00801   0.00168  -0.0752   0.6619   0.1437
  -2.250   0.0785   0.00801   0.00163  -0.0745   0.6452   0.1477
  -2.000   0.1033   0.00803   0.00160  -0.0737   0.6268   0.1517
  -1.750   0.1283   0.00806   0.00157  -0.0730   0.6090   0.1553
  -1.500   0.1535   0.00811   0.00155  -0.0723   0.5919   0.1582
  -1.250   0.1790   0.00814   0.00153  -0.0717   0.5775   0.1611
  -1.000   0.2044   0.00815   0.00152  -0.0710   0.5648   0.1668
  -0.750   0.2301   0.00816   0.00151  -0.0705   0.5546   0.1717
  -0.500   0.2564   0.00816   0.00151  -0.0700   0.5460   0.1763
  -0.250   0.2821   0.00814   0.00150  -0.0694   0.5380   0.1857
   0.000   0.3083   0.00813   0.00151  -0.0690   0.5311   0.1944
   0.250   0.3341   0.00811   0.00152  -0.0684   0.5234   0.2071
   0.500   0.3596   0.00810   0.00153  -0.0679   0.5161   0.2242
   0.750   0.3851   0.00803   0.00155  -0.0673   0.5088   0.2521
   1.000   0.4102   0.00800   0.00158  -0.0666   0.5022   0.2798
   1.250   0.4360   0.00795   0.00161  -0.0661   0.4965   0.3039
   1.500   0.4615   0.00792   0.00165  -0.0655   0.4899   0.3287
   1.750   0.4862   0.00789   0.00170  -0.0648   0.4826   0.3595
   2.000   0.5110   0.00787   0.00174  -0.0641   0.4712   0.3909
   2.250   0.5347   0.00788   0.00180  -0.0632   0.4560   0.4265
   2.500   0.5581   0.00788   0.00187  -0.0622   0.4405   0.4672
   2.750   0.5807   0.00790   0.00194  -0.0611   0.4218   0.5104
   3.000   0.6013   0.00797   0.00204  -0.0596   0.3944   0.5593
   3.250   0.6196   0.00812   0.00218  -0.0577   0.3594   0.6149
   3.500   0.6374   0.00816   0.00234  -0.0556   0.3365   0.6877
   3.750   0.6546   0.00814   0.00248  -0.0533   0.3196   0.7679
   4.000   0.6700   0.00809   0.00266  -0.0505   0.3024   0.8619
   4.250   0.7246   0.00830   0.00298  -0.0564   0.2852   0.9490
   4.500   0.7768   0.00857   0.00321  -0.0617   0.2717   0.9665
   4.750   0.8142   0.00881   0.00339  -0.0639   0.2578   0.9746
   5.000   0.8444   0.00911   0.00359  -0.0645   0.2396   0.9830
   5.250   0.8777   0.00951   0.00385  -0.0659   0.2117   0.9908
   5.750   0.9465   0.01044   0.00447  -0.0694   0.1590   1.0000
   6.000   0.9620   0.01073   0.00469  -0.0669   0.1459   1.0000
   6.250   0.9781   0.01100   0.00491  -0.0645   0.1341   1.0000
   6.500   0.9930   0.01133   0.00516  -0.0620   0.1200   1.0000
   6.750   1.0078   0.01166   0.00543  -0.0594   0.1066   1.0000
   7.000   1.0232   0.01198   0.00568  -0.0570   0.0963   1.0000
   7.250   1.0373   0.01225   0.00592  -0.0543   0.0890   1.0000
   7.500   1.0497   0.01257   0.00619  -0.0513   0.0810   1.0000
   7.750   1.0652   0.01282   0.00643  -0.0488   0.0766   1.0000
   8.000   1.0793   0.01316   0.00673  -0.0463   0.0692   1.0000
   8.250   1.0938   0.01353   0.00706  -0.0438   0.0611   1.0000
   8.750   1.1182   0.01458   0.00795  -0.0384   0.0373   1.0000
   9.000   1.1338   0.01499   0.00835  -0.0364   0.0342   1.0000
   9.250   1.1500   0.01539   0.00876  -0.0345   0.0327   1.0000
   9.500   1.1662   0.01581   0.00919  -0.0327   0.0315   1.0000
   9.750   1.1814   0.01630   0.00968  -0.0307   0.0299   1.0000
  10.000   1.1983   0.01671   0.01012  -0.0291   0.0294   1.0000
  10.250   1.2146   0.01717   0.01060  -0.0274   0.0288   1.0000
  10.500   1.2306   0.01766   0.01112  -0.0258   0.0283   1.0000
  10.750   1.2460   0.01819   0.01168  -0.0242   0.0278   1.0000
  11.000   1.2610   0.01877   0.01228  -0.0225   0.0273   1.0000
  11.250   1.2754   0.01940   0.01293  -0.0209   0.0268   1.0000
  11.500   1.2890   0.02009   0.01365  -0.0192   0.0262   1.0000
  11.750   1.3016   0.02086   0.01445  -0.0175   0.0256   1.0000
  12.000   1.3151   0.02161   0.01524  -0.0159   0.0253   1.0000
  12.250   1.3293   0.02233   0.01600  -0.0146   0.0250   1.0000
  12.500   1.3424   0.02314   0.01685  -0.0131   0.0247   1.0000
  12.750   1.3555   0.02397   0.01772  -0.0118   0.0243   1.0000
  13.000   1.3680   0.02487   0.01867  -0.0105   0.0240   1.0000
  13.250   1.3800   0.02582   0.01967  -0.0092   0.0236   1.0000
  13.500   1.3906   0.02691   0.02080  -0.0080   0.0233   1.0000
  13.750   1.4011   0.02804   0.02197  -0.0068   0.0228   1.0000
  14.000   1.4103   0.02930   0.02327  -0.0056   0.0225   1.0000
  14.250   1.4186   0.03066   0.02469  -0.0044   0.0223   1.0000
  14.500   1.4250   0.03223   0.02631  -0.0033   0.0218   1.0000
  14.750   1.4295   0.03403   0.02817  -0.0023   0.0214   1.0000
  15.000   1.4380   0.03553   0.02972  -0.0015   0.0213   1.0000
  15.250   1.4463   0.03709   0.03134  -0.0008   0.0210   1.0000
  15.500   1.4529   0.03885   0.03318  -0.0002   0.0208   1.0000
  15.750   1.4603   0.04059   0.03497   0.0003   0.0205   1.0000
  16.000   1.4652   0.04262   0.03708   0.0007   0.0203   1.0000
  16.250   1.4713   0.04456   0.03908   0.0010   0.0199   1.0000
  16.500   1.4754   0.04680   0.04138   0.0013   0.0196   1.0000
  16.750   1.4779   0.04925   0.04390   0.0014   0.0194   1.0000
  17.000   1.4801   0.05179   0.04651   0.0014   0.0192   1.0000
  17.250   1.4815   0.05445   0.04923   0.0013   0.0189   1.0000
  17.500   1.4812   0.05739   0.05225   0.0010   0.0187   1.0000
  17.750   1.4799   0.06051   0.05543   0.0007   0.0183   1.0000
  18.000   1.4751   0.06412   0.05911   0.0001   0.0180   1.0000
  18.250   1.4694   0.06788   0.06296  -0.0006   0.0180   1.0000
  18.500   1.4697   0.07091   0.06608  -0.0011   0.0177   1.0000
  18.750   1.4647   0.07471   0.06997  -0.0020   0.0176   1.0000
  19.000   1.4636   0.07801   0.07334  -0.0027   0.0173   1.0000
  19.250   1.4582   0.08191   0.07733  -0.0037   0.0171   1.0000
<< Back to GOE 629 AIRFOIL (goe629-il)

Polar data table (+)

Polar graphs


<< Back to GOE 629 AIRFOIL (goe629-il)