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GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 177 AIRFOIL (goe177-il)
Reynolds number: 200,000
Max Cl/Cd: 74.73 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe177-il-200000.txt
Download as CSV file: xf-goe177-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3199   0.09041   0.08723  -0.0188   1.0000   0.0332
  -7.000  -0.3178   0.08783   0.08471  -0.0196   1.0000   0.0346
  -6.750  -0.3135   0.08519   0.08213  -0.0223   1.0000   0.0367
  -6.500  -0.3059   0.08310   0.08009  -0.0296   1.0000   0.0381
  -6.250  -0.2937   0.08039   0.07739  -0.0353   1.0000   0.0385
  -6.000  -0.2939   0.07533   0.07240  -0.0349   1.0000   0.0392
  -5.750  -0.2935   0.07256   0.06969  -0.0306   1.0000   0.0402
  -5.500  -0.2887   0.07012   0.06729  -0.0294   1.0000   0.0413
  -5.250  -0.2833   0.06770   0.06490  -0.0293   1.0000   0.0426
  -5.000  -0.2663   0.06449   0.06168  -0.0324   0.9984   0.0447
  -4.750  -0.1813   0.05679   0.05358  -0.0556   0.9909   0.0503
  -4.500  -0.1575   0.05161   0.04847  -0.0576   0.9851   0.0521
  -4.250  -0.1174   0.04783   0.04461  -0.0630   0.9779   0.0554
  -4.000  -0.0497   0.04065   0.03689  -0.0764   0.9713   0.0632
  -3.750  -0.0142   0.03690   0.03315  -0.0799   0.9634   0.0653
  -3.500   0.0429   0.03428   0.02980  -0.0863   0.9557   0.0757
  -3.250   0.0839   0.02003   0.01430  -0.0902   0.9466   0.0384
  -3.000   0.1212   0.01633   0.00992  -0.0920   0.9334   0.0398
  -2.750   0.1555   0.01543   0.00886  -0.0928   0.9150   0.0459
  -2.500   0.1871   0.01406   0.00718  -0.0928   0.8924   0.0524
  -2.250   0.2174   0.01347   0.00640  -0.0925   0.8667   0.0637
  -2.000   0.2453   0.01303   0.00585  -0.0919   0.8388   0.0816
  -1.750   0.2722   0.01275   0.00533  -0.0911   0.8112   0.1038
  -1.500   0.2981   0.01236   0.00480  -0.0904   0.7852   0.1208
  -1.250   0.3244   0.01225   0.00448  -0.0898   0.7609   0.1321
  -1.000   0.3507   0.01206   0.00422  -0.0892   0.7384   0.1438
  -0.750   0.3770   0.01190   0.00396  -0.0887   0.7179   0.1538
  -0.500   0.4037   0.01177   0.00370  -0.0883   0.6978   0.1615
  -0.250   0.4305   0.01165   0.00352  -0.0879   0.6787   0.1732
   0.000   0.4572   0.01150   0.00339  -0.0875   0.6611   0.1948
   0.250   0.4836   0.01102   0.00338  -0.0873   0.6437   0.3438
   0.500   0.5063   0.00957   0.00324  -0.0857   0.6269   1.0000
   0.750   0.5333   0.00975   0.00320  -0.0853   0.6097   1.0000
   1.000   0.5601   0.00994   0.00319  -0.0850   0.5932   1.0000
   1.250   0.5869   0.01014   0.00320  -0.0846   0.5773   1.0000
   1.500   0.6135   0.01034   0.00323  -0.0843   0.5601   1.0000
   1.750   0.6400   0.01051   0.00326  -0.0839   0.5400   1.0000
   2.000   0.6661   0.01071   0.00327  -0.0835   0.5197   1.0000
   2.250   0.6924   0.01089   0.00333  -0.0831   0.4993   1.0000
   2.500   0.7188   0.01109   0.00341  -0.0828   0.4812   1.0000
   2.750   0.7452   0.01129   0.00350  -0.0825   0.4651   1.0000
   3.000   0.7718   0.01150   0.00363  -0.0823   0.4513   1.0000
   3.250   0.7984   0.01172   0.00378  -0.0821   0.4387   1.0000
   3.500   0.8250   0.01193   0.00398  -0.0818   0.4269   1.0000
   3.750   0.8515   0.01216   0.00416  -0.0816   0.4159   1.0000
   4.000   0.8778   0.01241   0.00435  -0.0814   0.4060   1.0000
   4.250   0.9045   0.01262   0.00458  -0.0812   0.3959   1.0000
   4.500   0.9307   0.01284   0.00482  -0.0809   0.3836   1.0000
   4.750   0.9560   0.01308   0.00498  -0.0806   0.3653   1.0000
   5.000   0.9817   0.01332   0.00520  -0.0803   0.3506   1.0000
   5.250   1.0072   0.01356   0.00541  -0.0799   0.3293   1.0000
   5.500   1.0328   0.01382   0.00567  -0.0796   0.3147   1.0000
   5.750   1.0575   0.01416   0.00594  -0.0793   0.2876   1.0000
   6.000   1.0808   0.01468   0.00622  -0.0788   0.2405   1.0000
   6.250   1.0966   0.01635   0.00712  -0.0776   0.1235   1.0000
   6.500   1.1190   0.01714   0.00782  -0.0770   0.0982   1.0000
   6.750   1.1405   0.01802   0.00859  -0.0762   0.0614   1.0000
   7.000   1.1620   0.01887   0.00952  -0.0753   0.0504   1.0000
   7.250   1.1853   0.01946   0.01023  -0.0746   0.0379   1.0000
   7.500   1.2070   0.02020   0.01096  -0.0737   0.0257   1.0000
   7.750   1.2281   0.02101   0.01184  -0.0727   0.0228   1.0000
   8.000   1.2481   0.02192   0.01290  -0.0715   0.0219   1.0000
   8.250   1.2665   0.02296   0.01416  -0.0701   0.0216   1.0000
   8.500   1.2822   0.02420   0.01566  -0.0684   0.0212   1.0000
   8.750   1.2943   0.02567   0.01733  -0.0664   0.0202   1.0000
   9.000   1.3029   0.02732   0.01914  -0.0641   0.0193   1.0000
   9.250   1.3093   0.02903   0.02100  -0.0615   0.0192   1.0000
   9.500   1.3118   0.03079   0.02289  -0.0584   0.0192   1.0000
   9.750   1.3134   0.03270   0.02492  -0.0554   0.0193   1.0000
  10.000   1.3160   0.03477   0.02710  -0.0527   0.0195   1.0000
  10.250   1.3214   0.03696   0.02939  -0.0503   0.0199   1.0000
  10.500   1.3316   0.03928   0.03183  -0.0481   0.0206   1.0000
  10.750   1.3520   0.04207   0.03471  -0.0465   0.0216   1.0000
  11.000   1.3842   0.04505   0.03782  -0.0462   0.0229   1.0000
  11.250   1.2717   0.03955   0.03281  -0.0324   0.0224   1.0000
  12.000   1.2978   0.05355   0.04816  -0.0259   0.0325   1.0000
  12.250   1.2734   0.05913   0.05411  -0.0236   0.0348   1.0000
  12.500   1.2502   0.06543   0.06091  -0.0217   0.0424   1.0000
  12.750   1.2213   0.07062   0.06634  -0.0213   0.0430   1.0000
  13.000   1.1940   0.07601   0.07193  -0.0217   0.0431   1.0000
  13.250   1.1692   0.08131   0.07735  -0.0225   0.0428   1.0000
  13.500   1.1444   0.08670   0.08287  -0.0238   0.0424   1.0000
  13.750   1.1203   0.09195   0.08825  -0.0253   0.0419   1.0000
  14.000   1.0965   0.09709   0.09350  -0.0270   0.0414   1.0000
  14.250   1.0713   0.10157   0.09808  -0.0283   0.0410   1.0000
  14.500   1.0465   0.10619   0.10280  -0.0301   0.0407   1.0000
  14.750   1.0227   0.11138   0.10809  -0.0326   0.0404   1.0000
  15.000   0.9997   0.11694   0.11374  -0.0356   0.0402   1.0000
  15.250   0.9761   0.12299   0.11986  -0.0389   0.0397   1.0000
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