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GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 507 AIRFOIL (goe507-il)
Reynolds number: 500,000
Max Cl/Cd: 82.01 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe507-il-500000-n5.txt
Download as CSV file: xf-goe507-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 507 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6340   0.09110   0.08855  -0.0339   1.0000   0.0110
 -12.250  -0.6600   0.08274   0.08017  -0.0387   1.0000   0.0110
 -12.000  -0.8992   0.03833   0.03524  -0.0684   1.0000   0.0088
 -11.750  -0.9082   0.03218   0.02872  -0.0688   1.0000   0.0088
 -11.500  -0.9043   0.02940   0.02571  -0.0675   1.0000   0.0090
 -11.250  -0.8977   0.02724   0.02337  -0.0659   1.0000   0.0093
 -11.000  -0.8885   0.02559   0.02158  -0.0640   1.0000   0.0096
 -10.750  -0.8636   0.02386   0.01965  -0.0652   0.9967   0.0100
 -10.500  -0.8372   0.02238   0.01797  -0.0663   0.9924   0.0105
 -10.250  -0.8100   0.02108   0.01646  -0.0673   0.9882   0.0110
 -10.000  -0.7816   0.01988   0.01508  -0.0684   0.9849   0.0115
  -9.750  -0.7549   0.01871   0.01376  -0.0691   0.9803   0.0123
  -9.500  -0.7251   0.01774   0.01264  -0.0702   0.9771   0.0130
  -9.250  -0.6965   0.01693   0.01167  -0.0709   0.9726   0.0141
  -9.000  -0.6672   0.01607   0.01069  -0.0717   0.9684   0.0151
  -8.750  -0.6376   0.01530   0.00981  -0.0725   0.9645   0.0167
  -8.500  -0.6090   0.01466   0.00903  -0.0730   0.9594   0.0183
  -8.250  -0.5791   0.01399   0.00830  -0.0738   0.9554   0.0209
  -8.000  -0.5510   0.01350   0.00776  -0.0740   0.9494   0.0240
  -7.750  -0.5210   0.01326   0.00753  -0.0746   0.9444   0.0284
  -7.500  -0.4920   0.01316   0.00742  -0.0748   0.9387   0.0321
  -7.250  -0.4626   0.01321   0.00745  -0.0750   0.9332   0.0356
  -7.000  -0.4339   0.01315   0.00731  -0.0751   0.9280   0.0385
  -6.750  -0.4062   0.01312   0.00719  -0.0750   0.9217   0.0400
  -6.500  -0.3789   0.01286   0.00684  -0.0749   0.9161   0.0415
  -6.250  -0.3527   0.01265   0.00661  -0.0746   0.9099   0.0434
  -6.000  -0.3256   0.01255   0.00646  -0.0744   0.9042   0.0451
  -5.750  -0.2984   0.01243   0.00628  -0.0742   0.8993   0.0469
  -5.500  -0.2719   0.01225   0.00604  -0.0739   0.8931   0.0486
  -5.250  -0.2451   0.01208   0.00578  -0.0736   0.8866   0.0502
  -5.000  -0.2187   0.01187   0.00548  -0.0732   0.8795   0.0512
  -4.750  -0.1923   0.01165   0.00518  -0.0728   0.8724   0.0519
  -4.500  -0.1658   0.01141   0.00488  -0.0725   0.8657   0.0524
  -4.250  -0.1395   0.01114   0.00454  -0.0721   0.8586   0.0527
  -4.000  -0.1131   0.01088   0.00422  -0.0717   0.8523   0.0529
  -3.750  -0.0868   0.01063   0.00392  -0.0713   0.8447   0.0531
  -3.500  -0.0606   0.01032   0.00354  -0.0708   0.8381   0.0536
  -3.250  -0.0350   0.00992   0.00311  -0.0704   0.8312   0.0552
  -3.000  -0.0086   0.00966   0.00282  -0.0700   0.8254   0.0562
  -2.750   0.0180   0.00945   0.00259  -0.0697   0.8194   0.0574
  -2.500   0.0448   0.00927   0.00239  -0.0693   0.8130   0.0585
  -2.250   0.0716   0.00913   0.00221  -0.0690   0.8070   0.0597
  -2.000   0.0986   0.00900   0.00207  -0.0687   0.8002   0.0609
  -1.750   0.1255   0.00889   0.00192  -0.0684   0.7935   0.0621
  -1.500   0.1526   0.00879   0.00181  -0.0682   0.7865   0.0632
  -1.250   0.1796   0.00871   0.00170  -0.0678   0.7790   0.0642
  -1.000   0.2067   0.00864   0.00161  -0.0676   0.7715   0.0651
  -0.750   0.2336   0.00857   0.00152  -0.0673   0.7633   0.0661
  -0.500   0.2606   0.00850   0.00144  -0.0669   0.7545   0.0687
  -0.250   0.2873   0.00844   0.00138  -0.0666   0.7451   0.0722
   0.000   0.3137   0.00839   0.00132  -0.0661   0.7313   0.0777
   0.250   0.3386   0.00816   0.00129  -0.0655   0.7136   0.1492
   0.500   0.3642   0.00812   0.00128  -0.0650   0.6914   0.1796
   0.750   0.3894   0.00813   0.00128  -0.0643   0.6649   0.2048
   1.000   0.4141   0.00817   0.00128  -0.0636   0.6325   0.2264
   1.500   0.4604   0.00836   0.00137  -0.0617   0.5505   0.3070
   1.750   0.4802   0.00791   0.00148  -0.0603   0.5242   0.5438
   2.000   0.5317   0.00711   0.00174  -0.0653   0.4985   0.9764
   2.250   0.5745   0.00732   0.00185  -0.0686   0.4736   0.9940
   2.500   0.6086   0.00754   0.00196  -0.0701   0.4489   1.0000
   2.750   0.6317   0.00774   0.00206  -0.0691   0.4253   1.0000
   3.000   0.6541   0.00799   0.00218  -0.0680   0.3969   1.0000
   3.250   0.6766   0.00825   0.00233  -0.0669   0.3694   1.0000
   3.500   0.6985   0.00855   0.00249  -0.0658   0.3373   1.0000
   3.750   0.7203   0.00888   0.00267  -0.0646   0.3046   1.0000
   4.000   0.7417   0.00925   0.00289  -0.0634   0.2698   1.0000
   4.250   0.7633   0.00961   0.00311  -0.0622   0.2398   1.0000
   4.500   0.7852   0.00996   0.00335  -0.0611   0.2139   1.0000
   4.750   0.8065   0.01036   0.00362  -0.0599   0.1828   1.0000
   5.000   0.8217   0.01131   0.00410  -0.0579   0.0954   1.0000
   5.250   0.8429   0.01176   0.00446  -0.0567   0.0774   1.0000
   5.500   0.8652   0.01211   0.00478  -0.0557   0.0696   1.0000
   5.750   0.8879   0.01243   0.00509  -0.0547   0.0646   1.0000
   6.000   0.9102   0.01279   0.00544  -0.0537   0.0603   1.0000
   6.250   0.9334   0.01306   0.00575  -0.0529   0.0580   1.0000
   6.500   0.9566   0.01333   0.00605  -0.0520   0.0552   1.0000
   6.750   0.9791   0.01365   0.00639  -0.0511   0.0518   1.0000
   7.000   1.0007   0.01406   0.00680  -0.0500   0.0475   1.0000
   7.250   1.0241   0.01429   0.00709  -0.0493   0.0454   1.0000
   7.500   1.0469   0.01458   0.00741  -0.0484   0.0402   1.0000
   7.750   1.0682   0.01498   0.00776  -0.0474   0.0326   1.0000
   8.000   1.0888   0.01544   0.00817  -0.0462   0.0264   1.0000
   8.250   1.1091   0.01592   0.00867  -0.0450   0.0227   1.0000
   8.500   1.1284   0.01645   0.00920  -0.0437   0.0199   1.0000
   8.750   1.1474   0.01699   0.00978  -0.0423   0.0178   1.0000
   9.000   1.1661   0.01753   0.01036  -0.0409   0.0162   1.0000
   9.250   1.1829   0.01820   0.01105  -0.0392   0.0148   1.0000
   9.500   1.2006   0.01876   0.01168  -0.0377   0.0140   1.0000
   9.750   1.2172   0.01935   0.01234  -0.0360   0.0130   1.0000
  10.000   1.2316   0.01997   0.01301  -0.0339   0.0123   1.0000
  10.250   1.2426   0.02076   0.01383  -0.0314   0.0116   1.0000
  10.500   1.2557   0.02142   0.01457  -0.0292   0.0111   1.0000
  10.750   1.2683   0.02213   0.01536  -0.0271   0.0105   1.0000
  11.000   1.2798   0.02293   0.01624  -0.0249   0.0101   1.0000
  11.250   1.2908   0.02378   0.01717  -0.0228   0.0097   1.0000
  11.500   1.3000   0.02477   0.01822  -0.0206   0.0094   1.0000
  11.750   1.3063   0.02600   0.01952  -0.0183   0.0090   1.0000
  12.000   1.3154   0.02709   0.02072  -0.0164   0.0087   1.0000
  12.250   1.3235   0.02826   0.02200  -0.0145   0.0085   1.0000
  12.500   1.3306   0.02956   0.02340  -0.0127   0.0082   1.0000
  12.750   1.3375   0.03092   0.02486  -0.0111   0.0080   1.0000
  13.000   1.3428   0.03247   0.02651  -0.0095   0.0077   1.0000
  13.250   1.3488   0.03400   0.02815  -0.0082   0.0075   1.0000
  13.500   1.3529   0.03578   0.03001  -0.0070   0.0073   1.0000
  13.750   1.3539   0.03791   0.03224  -0.0058   0.0072   1.0000
  14.000   1.3514   0.04049   0.03492  -0.0048   0.0070   1.0000
  14.250   1.3516   0.04294   0.03750  -0.0041   0.0069   1.0000
  14.500   1.3521   0.04546   0.04017  -0.0037   0.0068   1.0000
  14.750   1.3487   0.04855   0.04340  -0.0035   0.0067   1.0000
  15.000   1.3465   0.05165   0.04665  -0.0037   0.0065   1.0000
  15.250   1.3407   0.05539   0.05052  -0.0042   0.0065   1.0000
  15.500   1.3360   0.05918   0.05446  -0.0051   0.0064   1.0000
  15.750   1.3285   0.06360   0.05903  -0.0064   0.0062   1.0000
  16.000   1.3214   0.06816   0.06373  -0.0081   0.0062   1.0000
  16.250   1.3120   0.07331   0.06902  -0.0102   0.0061   1.0000
  16.500   1.3007   0.07890   0.07476  -0.0126   0.0061   1.0000
  16.750   1.2878   0.08504   0.08105  -0.0154   0.0060   1.0000
  17.000   1.2755   0.09128   0.08742  -0.0185   0.0060   1.0000
  17.250   1.2605   0.09818   0.09448  -0.0220   0.0060   1.0000
  17.500   1.2462   0.10524   0.10168  -0.0257   0.0059   1.0000
  17.750   1.2296   0.11297   0.10955  -0.0299   0.0059   1.0000
  18.000   1.2113   0.12124   0.11797  -0.0344   0.0059   1.0000
  18.250   1.1944   0.12949   0.12636  -0.0391   0.0059   1.0000
  18.500   1.1744   0.13874   0.13576  -0.0443   0.0059   1.0000
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