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GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 507 AIRFOIL (goe507-il)
Reynolds number: 100,000
Max Cl/Cd: 53.56 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe507-il-100000-n5.txt
Download as CSV file: xf-goe507-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4437   0.09158   0.08635  -0.0352   1.0000   0.0385
  -9.250  -0.4515   0.08657   0.08142  -0.0377   1.0000   0.0391
  -9.000  -0.4608   0.08172   0.07666  -0.0400   1.0000   0.0395
  -8.750  -0.4755   0.07679   0.07183  -0.0422   1.0000   0.0399
  -8.500  -0.4940   0.07102   0.06618  -0.0452   1.0000   0.0402
  -8.250  -0.5118   0.06386   0.05903  -0.0488   1.0000   0.0404
  -8.000  -0.5210   0.05944   0.05460  -0.0492   1.0000   0.0411
  -7.750  -0.5185   0.05841   0.05359  -0.0473   1.0000   0.0421
  -7.500  -0.5178   0.05654   0.05169  -0.0458   1.0000   0.0432
  -7.250  -0.5215   0.05288   0.04792  -0.0450   1.0000   0.0443
  -7.000  -0.5239   0.04866   0.04350  -0.0443   1.0000   0.0463
  -6.750  -0.5239   0.04188   0.03618  -0.0453   0.9986   0.0493
  -6.500  -0.5044   0.03444   0.02755  -0.0489   0.9922   0.0540
  -6.250  -0.4762   0.03350   0.02663  -0.0502   0.9879   0.0573
  -6.000  -0.4488   0.03126   0.02393  -0.0516   0.9834   0.0618
  -5.750  -0.4213   0.02866   0.02053  -0.0527   0.9785   0.0661
  -5.500  -0.3923   0.02740   0.01923  -0.0538   0.9746   0.0696
  -5.250  -0.3642   0.02617   0.01774  -0.0545   0.9699   0.0730
  -5.000  -0.3323   0.02489   0.01602  -0.0557   0.9665   0.0765
  -4.750  -0.3042   0.02376   0.01452  -0.0560   0.9615   0.0789
  -4.500  -0.2736   0.02262   0.01326  -0.0569   0.9576   0.0806
  -4.250  -0.2400   0.02174   0.01227  -0.0583   0.9548   0.0825
  -4.000  -0.2133   0.02114   0.01156  -0.0583   0.9490   0.0854
  -3.750  -0.1805   0.02049   0.01077  -0.0594   0.9452   0.0882
  -3.500  -0.1473   0.01984   0.00999  -0.0605   0.9416   0.0897
  -3.250  -0.1171   0.01928   0.00931  -0.0610   0.9349   0.0913
  -3.000  -0.0790   0.01859   0.00862  -0.0630   0.9306   0.0936
  -2.750  -0.0496   0.01811   0.00814  -0.0633   0.9228   0.0964
  -2.500  -0.0146   0.01768   0.00768  -0.0646   0.9177   0.1000
  -2.250   0.0148   0.01736   0.00733  -0.0648   0.9116   0.1044
  -2.000   0.0445   0.01704   0.00704  -0.0651   0.9054   0.1102
  -1.750   0.0789   0.01669   0.00676  -0.0663   0.9012   0.1228
  -1.500   0.1040   0.01645   0.00669  -0.0658   0.8933   0.1521
  -1.250   0.1360   0.01617   0.00654  -0.0665   0.8878   0.1993
  -1.000   0.1657   0.01593   0.00640  -0.0668   0.8815   0.2367
  -0.750   0.1943   0.01567   0.00629  -0.0668   0.8742   0.2781
  -0.500   0.2277   0.01514   0.00615  -0.0679   0.8694   0.3684
  -0.250   0.2465   0.01435   0.00618  -0.0660   0.8599   0.5864
   0.250   0.3709   0.01343   0.00594  -0.0787   0.8525   1.0000
   0.500   0.3955   0.01346   0.00590  -0.0778   0.8423   1.0000
   0.750   0.4201   0.01349   0.00588  -0.0769   0.8318   1.0000
   1.000   0.4482   0.01344   0.00577  -0.0765   0.8227   1.0000
   1.250   0.4717   0.01348   0.00577  -0.0753   0.8105   1.0000
   1.500   0.4958   0.01350   0.00576  -0.0742   0.7976   1.0000
   1.750   0.5204   0.01348   0.00571  -0.0731   0.7837   1.0000
   2.000   0.5450   0.01346   0.00566  -0.0719   0.7681   1.0000
   2.250   0.5694   0.01344   0.00562  -0.0707   0.7514   1.0000
   2.500   0.5940   0.01346   0.00562  -0.0696   0.7346   1.0000
   2.750   0.6186   0.01349   0.00565  -0.0686   0.7175   1.0000
   3.000   0.6434   0.01354   0.00568  -0.0676   0.6997   1.0000
   3.250   0.6667   0.01363   0.00578  -0.0663   0.6776   1.0000
   3.500   0.6907   0.01370   0.00579  -0.0650   0.6523   1.0000
   3.750   0.7136   0.01381   0.00583  -0.0636   0.6207   1.0000
   4.000   0.7361   0.01399   0.00588  -0.0621   0.5843   1.0000
   4.250   0.7583   0.01426   0.00599  -0.0606   0.5491   1.0000
   4.500   0.7801   0.01461   0.00619  -0.0592   0.5167   1.0000
   4.750   0.8018   0.01498   0.00650  -0.0578   0.4877   1.0000
   5.000   0.8232   0.01537   0.00683  -0.0565   0.4581   1.0000
   5.250   0.8443   0.01577   0.00719  -0.0551   0.4286   1.0000
   5.500   0.8643   0.01623   0.00758  -0.0536   0.3928   1.0000
   5.750   0.8833   0.01677   0.00798  -0.0520   0.3535   1.0000
   6.000   0.9021   0.01735   0.00845  -0.0504   0.3142   1.0000
   6.250   0.9195   0.01806   0.00899  -0.0487   0.2693   1.0000
   6.500   0.9349   0.01898   0.00966  -0.0468   0.2142   1.0000
   6.750   0.9490   0.02011   0.01045  -0.0448   0.1502   1.0000
   7.000   0.9632   0.02129   0.01134  -0.0429   0.1149   1.0000
   7.250   0.9781   0.02236   0.01230  -0.0410   0.0988   1.0000
   7.500   0.9935   0.02335   0.01332  -0.0392   0.0885   1.0000
   7.750   1.0074   0.02444   0.01442  -0.0373   0.0804   1.0000
   8.000   1.0210   0.02553   0.01556  -0.0353   0.0729   1.0000
   8.250   1.0343   0.02665   0.01677  -0.0333   0.0662   1.0000
   8.500   1.0455   0.02792   0.01805  -0.0311   0.0604   1.0000
   8.750   1.0595   0.02907   0.01937  -0.0292   0.0546   1.0000
   9.000   1.0710   0.03029   0.02065  -0.0271   0.0497   1.0000
   9.250   1.0826   0.03169   0.02211  -0.0250   0.0458   1.0000
   9.500   1.0973   0.03300   0.02362  -0.0232   0.0418   1.0000
   9.750   1.1101   0.03435   0.02509  -0.0214   0.0384   1.0000
  10.000   1.1208   0.03569   0.02651  -0.0195   0.0358   1.0000
  10.250   1.1324   0.03771   0.02858  -0.0179   0.0335   1.0000
  10.500   1.1469   0.03958   0.03072  -0.0164   0.0318   1.0000
  10.750   1.1582   0.04146   0.03285  -0.0147   0.0299   1.0000
  11.000   1.1665   0.04329   0.03488  -0.0129   0.0284   1.0000
  11.250   1.1719   0.04506   0.03680  -0.0111   0.0270   1.0000
  11.500   1.1768   0.04715   0.03905  -0.0094   0.0263   1.0000
  11.750   1.1796   0.04947   0.04153  -0.0077   0.0255   1.0000
  12.000   1.1791   0.05236   0.04458  -0.0062   0.0248   1.0000
  12.250   1.1744   0.05569   0.04815  -0.0047   0.0243   1.0000
  12.500   1.1662   0.05906   0.05188  -0.0035   0.0239   1.0000
  12.750   1.1552   0.06285   0.05597  -0.0028   0.0236   1.0000
  13.000   1.1408   0.06717   0.06058  -0.0027   0.0232   1.0000
  13.250   1.1251   0.07190   0.06557  -0.0035   0.0230   1.0000
  13.500   1.1067   0.07739   0.07131  -0.0051   0.0228   1.0000
  13.750   1.0866   0.08360   0.07775  -0.0078   0.0229   1.0000
  14.000   1.0637   0.09089   0.08526  -0.0117   0.0229   1.0000
  14.250   1.0398   0.09915   0.09367  -0.0166   0.0232   1.0000
  14.500   1.0146   0.10860   0.10328  -0.0225   0.0236   1.0000
  14.750   0.9885   0.11929   0.11409  -0.0294   0.0240   1.0000
  15.000   0.9647   0.13052   0.12538  -0.0362   0.0244   1.0000
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