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GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 483 AIRFOIL (goe483-il)
Reynolds number: 100,000
Max Cl/Cd: 62.7 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe483-il-100000.txt
Download as CSV file: xf-goe483-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 483 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3068   0.10587   0.10121  -0.0257   1.0000   0.0509
  -7.750  -0.3108   0.10526   0.10070  -0.0265   1.0000   0.0511
  -7.500  -0.3099   0.10442   0.09996  -0.0296   1.0000   0.0513
  -7.250  -0.3057   0.10304   0.09862  -0.0327   1.0000   0.0515
  -7.000  -0.2962   0.09371   0.08931  -0.0246   1.0000   0.0532
  -6.750  -0.2923   0.09079   0.08645  -0.0234   1.0000   0.0545
  -6.500  -0.2917   0.08856   0.08429  -0.0225   1.0000   0.0559
  -6.250  -0.2938   0.08674   0.08256  -0.0215   1.0000   0.0573
  -6.000  -0.2977   0.08520   0.08110  -0.0204   1.0000   0.0585
  -5.750  -0.3017   0.08370   0.07967  -0.0194   1.0000   0.0598
  -5.500  -0.3033   0.08220   0.07821  -0.0196   1.0000   0.0616
  -5.250  -0.2953   0.08153   0.07754  -0.0243   1.0000   0.0636
  -5.000  -0.2716   0.08122   0.07710  -0.0333   1.0000   0.0644
  -4.750  -0.2788   0.07614   0.07216  -0.0283   1.0000   0.0652
  -4.500  -0.2799   0.07284   0.06893  -0.0247   1.0000   0.0665
  -4.250  -0.2743   0.07020   0.06631  -0.0238   1.0000   0.0688
  -4.000  -0.2611   0.06778   0.06387  -0.0254   1.0000   0.0730
  -3.750  -0.2110   0.06341   0.05932  -0.0365   0.9949   0.0796
  -3.250  -0.1205   0.05502   0.05070  -0.0514   0.9822   0.0942
  -3.000  -0.0613   0.05181   0.04717  -0.0617   0.9741   0.1056
  -2.750  -0.0273   0.04759   0.04298  -0.0648   0.9686   0.1119
  -2.500   0.0184   0.04427   0.03944  -0.0709   0.9600   0.1225
  -2.250   0.0757   0.04173   0.03654  -0.0786   0.9534   0.1471
  -2.000   0.1170   0.03867   0.03331  -0.0826   0.9449   0.1611
  -1.750   0.1879   0.03335   0.02712  -0.0908   0.9411   0.1186
  -1.500   0.2197   0.03093   0.02477  -0.0927   0.9309   0.1354
  -1.250   0.2830   0.02383   0.01620  -0.0979   0.9284   0.0926
  -1.000   0.3230   0.02255   0.01469  -0.1000   0.9182   0.1078
  -0.750   0.3725   0.02100   0.01283  -0.1035   0.9115   0.1253
  -0.500   0.4141   0.02000   0.01167  -0.1055   0.9015   0.1507
  -0.250   0.4517   0.01946   0.01103  -0.1066   0.8899   0.1882
   0.000   0.4878   0.01896   0.01054  -0.1076   0.8782   0.2252
   0.250   0.5230   0.01838   0.00994  -0.1084   0.8665   0.2590
   0.500   0.5557   0.01773   0.00929  -0.1085   0.8542   0.2868
   0.750   0.5870   0.01709   0.00867  -0.1082   0.8413   0.3174
   1.000   0.6155   0.01650   0.00815  -0.1075   0.8272   0.3546
   1.250   0.6419   0.01586   0.00779  -0.1067   0.8123   0.4262
   1.500   0.6748   0.01472   0.00747  -0.1066   0.7974   1.0000
   1.750   0.7007   0.01479   0.00734  -0.1054   0.7812   1.0000
   2.000   0.7264   0.01487   0.00728  -0.1043   0.7653   1.0000
   2.250   0.7521   0.01494   0.00721  -0.1032   0.7495   1.0000
   2.500   0.7777   0.01502   0.00717  -0.1021   0.7340   1.0000
   2.750   0.8035   0.01510   0.00715  -0.1011   0.7185   1.0000
   3.000   0.8281   0.01527   0.00727  -0.1001   0.7010   1.0000
   3.250   0.8532   0.01541   0.00741  -0.0992   0.6840   1.0000
   3.500   0.8786   0.01556   0.00749  -0.0982   0.6674   1.0000
   3.750   0.9042   0.01570   0.00758  -0.0973   0.6510   1.0000
   4.000   0.9296   0.01589   0.00771  -0.0964   0.6343   1.0000
   4.250   0.9542   0.01614   0.00797  -0.0955   0.6159   1.0000
   4.500   0.9793   0.01640   0.00827  -0.0946   0.5984   1.0000
   4.750   1.0046   0.01671   0.00854  -0.0938   0.5816   1.0000
   5.000   1.0296   0.01709   0.00893  -0.0930   0.5646   1.0000
   5.250   1.0540   0.01755   0.00944  -0.0922   0.5470   1.0000
   5.500   1.0786   0.01803   0.00998  -0.0914   0.5301   1.0000
   5.750   1.1022   0.01837   0.01034  -0.0902   0.5086   1.0000
   6.000   1.1226   0.01846   0.01045  -0.0884   0.4780   1.0000
   6.250   1.1420   0.01849   0.01050  -0.0865   0.4446   1.0000
   6.500   1.1623   0.01864   0.01073  -0.0848   0.4144   1.0000
   6.750   1.1781   0.01879   0.01083  -0.0824   0.3589   1.0000
   7.000   1.1892   0.01982   0.01140  -0.0796   0.2524   1.0000
   7.250   1.1880   0.02317   0.01329  -0.0763   0.0753   1.0000
   7.500   1.1997   0.02516   0.01517  -0.0739   0.0561   1.0000
   7.750   1.2122   0.02685   0.01699  -0.0717   0.0492   1.0000
   8.000   1.2221   0.02861   0.01889  -0.0693   0.0441   1.0000
   8.250   1.2266   0.03076   0.02115  -0.0663   0.0421   1.0000
   8.500   1.2362   0.03257   0.02306  -0.0637   0.0412   1.0000
   8.750   1.2500   0.03453   0.02510  -0.0616   0.0404   1.0000
   9.000   1.2724   0.03688   0.02750  -0.0603   0.0399   1.0000
   9.250   1.3018   0.03976   0.03056  -0.0599   0.0396   1.0000
   9.500   1.3253   0.04253   0.03359  -0.0590   0.0382   1.0000
   9.750   1.3454   0.04562   0.03700  -0.0578   0.0373   1.0000
  10.000   1.3627   0.04951   0.04131  -0.0563   0.0385   1.0000
  10.250   1.3746   0.05390   0.04611  -0.0545   0.0399   1.0000
  10.500   1.3869   0.06027   0.05275  -0.0537   0.0417   1.0000
  10.750   1.3892   0.06150   0.05459  -0.0500   0.0444   1.0000
  11.000   1.3693   0.06549   0.05921  -0.0459   0.0469   1.0000
  11.250   1.3532   0.06966   0.06372  -0.0429   0.0488   1.0000
  11.500   1.3396   0.07432   0.06861  -0.0410   0.0506   1.0000
  11.750   1.3358   0.07904   0.07361  -0.0396   0.0549   1.0000
  12.000   1.3081   0.08320   0.07803  -0.0390   0.0552   1.0000
  12.250   1.2823   0.08815   0.08321  -0.0399   0.0553   1.0000
  12.500   1.2567   0.09393   0.08918  -0.0421   0.0553   1.0000
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