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GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 177 AIRFOIL (goe177-il)
Reynolds number: 100,000
Max Cl/Cd: 57.83 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe177-il-100000-n5.txt
Download as CSV file: xf-goe177-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 177 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2980   0.09486   0.09049  -0.0228   1.0000   0.0395
  -7.000  -0.3001   0.09330   0.08903  -0.0251   1.0000   0.0407
  -6.750  -0.2976   0.09132   0.08715  -0.0291   1.0000   0.0412
  -6.500  -0.2915   0.08877   0.08465  -0.0326   1.0000   0.0414
  -6.250  -0.2838   0.08586   0.08179  -0.0352   1.0000   0.0415
  -6.000  -0.2790   0.08214   0.07815  -0.0357   1.0000   0.0417
  -5.750  -0.2765   0.07853   0.07460  -0.0341   1.0000   0.0421
  -5.500  -0.2614   0.07475   0.07083  -0.0374   0.9978   0.0421
  -5.250  -0.2398   0.06922   0.06523  -0.0382   0.9913   0.0294
  -5.000  -0.2028   0.06363   0.05957  -0.0466   0.9822   0.0263
  -4.750  -0.1587   0.05700   0.05280  -0.0572   0.9725   0.0238
  -4.500  -0.1046   0.04837   0.04390  -0.0699   0.9634   0.0215
  -4.250  -0.0581   0.04197   0.03723  -0.0780   0.9544   0.0213
  -4.000  -0.0228   0.03896   0.03404  -0.0823   0.9417   0.0237
  -3.750   0.0192   0.03367   0.02835  -0.0876   0.9285   0.0250
  -3.500   0.0618   0.02733   0.02128  -0.0923   0.9146   0.0252
  -3.250   0.1013   0.02261   0.01566  -0.0949   0.8992   0.0266
  -3.000   0.1379   0.01981   0.01205  -0.0962   0.8815   0.0309
  -2.750   0.1715   0.01829   0.01025  -0.0970   0.8608   0.0360
  -2.500   0.2048   0.01732   0.00903  -0.0975   0.8394   0.0461
  -2.250   0.2365   0.01670   0.00808  -0.0975   0.8171   0.0656
  -2.000   0.2660   0.01638   0.00753  -0.0975   0.7947   0.0898
  -1.750   0.2947   0.01601   0.00689  -0.0972   0.7730   0.1081
  -1.500   0.3225   0.01567   0.00638  -0.0969   0.7522   0.1211
  -1.250   0.3499   0.01541   0.00595  -0.0966   0.7323   0.1330
  -1.000   0.3771   0.01516   0.00551  -0.0961   0.7136   0.1408
  -0.750   0.4039   0.01497   0.00518  -0.0956   0.6953   0.1493
  -0.500   0.4306   0.01482   0.00492  -0.0951   0.6777   0.1624
  -0.250   0.4577   0.01470   0.00470  -0.0948   0.6606   0.1802
   0.000   0.4847   0.01454   0.00457  -0.0945   0.6442   0.2208
   0.250   0.5113   0.01432   0.00452  -0.0942   0.6283   0.3254
   0.500   0.5301   0.01315   0.00447  -0.0921   0.6139   0.7400
   1.000   0.5884   0.01326   0.00428  -0.0921   0.5835   1.0000
   1.250   0.6150   0.01346   0.00430  -0.0917   0.5693   1.0000
   1.500   0.6417   0.01368   0.00435  -0.0914   0.5554   1.0000
   1.750   0.6682   0.01390   0.00443  -0.0911   0.5418   1.0000
   2.000   0.6947   0.01413   0.00454  -0.0908   0.5288   1.0000
   2.250   0.7212   0.01437   0.00467  -0.0905   0.5165   1.0000
   2.500   0.7474   0.01462   0.00483  -0.0902   0.5028   1.0000
   2.750   0.7733   0.01487   0.00497  -0.0898   0.4873   1.0000
   3.000   0.7989   0.01512   0.00512  -0.0894   0.4710   1.0000
   3.250   0.8246   0.01538   0.00530  -0.0890   0.4556   1.0000
   3.500   0.8504   0.01564   0.00555  -0.0887   0.4428   1.0000
   3.750   0.8763   0.01592   0.00580  -0.0883   0.4320   1.0000
   4.000   0.9019   0.01621   0.00605  -0.0880   0.4208   1.0000
   4.250   0.9274   0.01650   0.00637  -0.0876   0.4088   1.0000
   4.500   0.9529   0.01679   0.00668  -0.0873   0.3967   1.0000
   4.750   0.9783   0.01709   0.00702  -0.0869   0.3853   1.0000
   5.000   1.0035   0.01740   0.00737  -0.0865   0.3750   1.0000
   5.250   1.0265   0.01775   0.00766  -0.0859   0.3479   1.0000
   5.500   1.0494   0.01817   0.00798  -0.0852   0.3195   1.0000
   5.750   1.0723   0.01865   0.00838  -0.0846   0.2886   1.0000
   6.000   1.0944   0.01927   0.00884  -0.0839   0.2446   1.0000
   6.250   1.1068   0.02122   0.00997  -0.0824   0.1218   1.0000
   6.500   1.1219   0.02295   0.01138  -0.0811   0.0574   1.0000
   6.750   1.1433   0.02376   0.01231  -0.0802   0.0482   1.0000
   7.000   1.1628   0.02478   0.01335  -0.0791   0.0219   1.0000
   7.250   1.1815   0.02584   0.01457  -0.0778   0.0188   1.0000
   7.500   1.1999   0.02689   0.01584  -0.0765   0.0176   1.0000
   7.750   1.2166   0.02806   0.01726  -0.0750   0.0168   1.0000
   8.000   1.2304   0.02945   0.01892  -0.0733   0.0159   1.0000
   8.250   1.2401   0.03113   0.02096  -0.0712   0.0147   1.0000
   8.500   1.2452   0.03305   0.02316  -0.0687   0.0138   1.0000
   8.750   1.2466   0.03502   0.02538  -0.0659   0.0134   1.0000
   9.000   1.2440   0.03710   0.02768  -0.0629   0.0132   1.0000
   9.250   1.2401   0.03947   0.03024  -0.0604   0.0131   1.0000
   9.500   1.2356   0.04214   0.03308  -0.0584   0.0130   1.0000
   9.750   1.2322   0.04497   0.03605  -0.0569   0.0129   1.0000
  10.000   1.2306   0.04781   0.03900  -0.0556   0.0128   1.0000
  10.250   1.2327   0.05042   0.04170  -0.0540   0.0127   1.0000
  10.500   1.2393   0.05277   0.04411  -0.0521   0.0127   1.0000
  10.750   1.2503   0.05496   0.04635  -0.0501   0.0126   1.0000
  11.000   1.2595   0.05732   0.04887  -0.0488   0.0125   1.0000
  11.250   1.2658   0.05988   0.05165  -0.0479   0.0122   1.0000
  11.500   1.2701   0.06271   0.05469  -0.0472   0.0119   1.0000
  11.750   1.2729   0.06578   0.05799  -0.0466   0.0116   1.0000
  12.000   1.2739   0.06915   0.06159  -0.0462   0.0113   1.0000
  12.250   1.2726   0.07286   0.06554  -0.0460   0.0112   1.0000
  12.500   1.2694   0.07692   0.06984  -0.0461   0.0112   1.0000
  12.750   1.2637   0.08136   0.07453  -0.0466   0.0112   1.0000
  13.000   1.2554   0.08617   0.07958  -0.0477   0.0113   1.0000
  13.250   1.2452   0.09134   0.08499  -0.0492   0.0114   1.0000
  13.500   1.2337   0.09682   0.09069  -0.0511   0.0114   1.0000
  13.750   1.2210   0.10263   0.09672  -0.0536   0.0115   1.0000
  14.000   1.2080   0.10877   0.10307  -0.0565   0.0116   1.0000
  14.250   1.1946   0.11528   0.10978  -0.0599   0.0117   1.0000
  14.500   1.1812   0.12212   0.11681  -0.0637   0.0117   1.0000
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