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GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 654 AIRFOIL (goe654-il)
Reynolds number: 200,000
Max Cl/Cd: 67.83 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe654-il-200000-n5.txt
Download as CSV file: xf-goe654-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 654 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2392   0.12746   0.12379  -0.0385   1.0000   0.0382
 -11.750  -0.2500   0.12366   0.12003  -0.0418   1.0000   0.0389
 -11.500  -0.2519   0.12006   0.11646  -0.0435   1.0000   0.0390
 -11.250  -0.2507   0.11656   0.11302  -0.0441   1.0000   0.0391
 -11.000  -0.2393   0.11425   0.11074  -0.0425   1.0000   0.0395
 -10.750  -0.2295   0.11227   0.10879  -0.0414   1.0000   0.0402
 -10.500  -0.2222   0.10990   0.10646  -0.0416   0.9994   0.0412
 -10.250  -0.2081   0.10609   0.10266  -0.0450   0.9871   0.0435
 -10.000  -0.2136   0.09957   0.09616  -0.0546   0.9694   0.0456
  -9.750  -0.2038   0.09400   0.09057  -0.0612   0.9517   0.0458
  -9.500  -0.1801   0.08956   0.08610  -0.0650   0.9373   0.0461
  -9.250  -0.1485   0.08611   0.08260  -0.0692   0.9214   0.0468
  -9.000  -0.1166   0.08222   0.07862  -0.0754   0.9032   0.0480
  -8.750  -0.0895   0.07793   0.07423  -0.0826   0.8815   0.0503
  -8.500  -0.0977   0.06762   0.06379  -0.0922   0.8571   0.0376
  -8.000  -0.1938   0.04107   0.03630  -0.1098   0.8087   0.0334
  -7.500  -0.1687   0.03757   0.03250  -0.1088   0.7783   0.0340
  -7.250  -0.1544   0.03603   0.03078  -0.1082   0.7640   0.0346
  -7.000  -0.1449   0.03321   0.02759  -0.1073   0.7509   0.0348
  -6.750  -0.1334   0.03043   0.02437  -0.1062   0.7381   0.0347
  -6.500  -0.1181   0.02823   0.02177  -0.1051   0.7252   0.0348
  -6.250  -0.1003   0.02645   0.01964  -0.1040   0.7121   0.0349
  -6.000  -0.0805   0.02498   0.01784  -0.1030   0.6998   0.0351
  -5.750  -0.0594   0.02371   0.01626  -0.1021   0.6885   0.0353
  -5.500  -0.0372   0.02260   0.01488  -0.1012   0.6767   0.0356
  -5.250  -0.0142   0.02168   0.01372  -0.1004   0.6653   0.0361
  -5.000   0.0094   0.02090   0.01269  -0.0996   0.6536   0.0368
  -4.750   0.0332   0.02014   0.01169  -0.0987   0.6414   0.0374
  -4.500   0.0575   0.01942   0.01076  -0.0980   0.6294   0.0377
  -4.250   0.0820   0.01878   0.00993  -0.0972   0.6178   0.0379
  -3.750   0.1317   0.01772   0.00855  -0.0958   0.5964   0.0386
  -3.500   0.1569   0.01729   0.00798  -0.0951   0.5882   0.0389
  -3.250   0.1820   0.01678   0.00743  -0.0945   0.5809   0.0393
  -3.000   0.2067   0.01634   0.00693  -0.0938   0.5742   0.0398
  -2.750   0.2319   0.01597   0.00655  -0.0933   0.5677   0.0405
  -2.500   0.2571   0.01569   0.00624  -0.0927   0.5616   0.0417
  -2.250   0.2825   0.01548   0.00595  -0.0921   0.5561   0.0430
  -2.000   0.3081   0.01525   0.00569  -0.0916   0.5500   0.0442
  -1.750   0.3337   0.01507   0.00544  -0.0911   0.5440   0.0450
  -1.500   0.3593   0.01493   0.00521  -0.0905   0.5386   0.0460
  -1.250   0.3852   0.01473   0.00501  -0.0901   0.5330   0.0475
  -1.000   0.4112   0.01462   0.00485  -0.0896   0.5276   0.0496
  -0.750   0.4372   0.01457   0.00471  -0.0891   0.5226   0.0522
  -0.500   0.4631   0.01445   0.00462  -0.0887   0.5168   0.0584
  -0.250   0.4884   0.01425   0.00455  -0.0881   0.5108   0.0899
   0.000   0.5119   0.01384   0.00451  -0.0875   0.5054   0.2180
   0.250   0.5336   0.01326   0.00461  -0.0866   0.4998   0.4173
   0.500   0.5556   0.01294   0.00469  -0.0854   0.4939   0.5416
   0.750   0.5757   0.01259   0.00476  -0.0837   0.4887   0.6775
   1.250   0.6871   0.01235   0.00491  -0.0946   0.4724   1.0000
   1.500   0.7104   0.01247   0.00495  -0.0936   0.4654   1.0000
   1.750   0.7335   0.01259   0.00500  -0.0926   0.4581   1.0000
   2.000   0.7566   0.01273   0.00505  -0.0917   0.4512   1.0000
   2.250   0.7800   0.01287   0.00512  -0.0907   0.4434   1.0000
   2.500   0.8029   0.01302   0.00519  -0.0898   0.4362   1.0000
   2.750   0.8262   0.01317   0.00529  -0.0889   0.4274   1.0000
   3.000   0.8489   0.01334   0.00538  -0.0879   0.4191   1.0000
   3.250   0.8716   0.01352   0.00549  -0.0869   0.4098   1.0000
   3.500   0.8943   0.01371   0.00561  -0.0859   0.4014   1.0000
   3.750   0.9166   0.01392   0.00576  -0.0849   0.3934   1.0000
   4.000   0.9391   0.01414   0.00592  -0.0839   0.3861   1.0000
   4.250   0.9611   0.01439   0.00610  -0.0829   0.3787   1.0000
   4.500   0.9831   0.01465   0.00630  -0.0818   0.3719   1.0000
   4.750   1.0051   0.01491   0.00651  -0.0808   0.3654   1.0000
   5.000   1.0263   0.01522   0.00674  -0.0797   0.3599   1.0000
   5.250   1.0488   0.01548   0.00700  -0.0788   0.3546   1.0000
   5.500   1.0704   0.01578   0.00727  -0.0778   0.3494   1.0000
   5.750   1.0912   0.01612   0.00754  -0.0766   0.3447   1.0000
   6.000   1.1131   0.01642   0.00785  -0.0757   0.3402   1.0000
   6.250   1.1344   0.01673   0.00817  -0.0747   0.3356   1.0000
   6.500   1.1551   0.01707   0.00848  -0.0736   0.3314   1.0000
   6.750   1.1751   0.01747   0.00882  -0.0724   0.3274   1.0000
   7.000   1.1962   0.01777   0.00918  -0.0714   0.3233   1.0000
   7.250   1.2162   0.01811   0.00955  -0.0702   0.3190   1.0000
   7.500   1.2350   0.01850   0.00991  -0.0689   0.3148   1.0000
   7.750   1.2530   0.01892   0.01030  -0.0674   0.3110   1.0000
   8.000   1.2705   0.01924   0.01071  -0.0658   0.3065   1.0000
   8.250   1.2873   0.01962   0.01112  -0.0641   0.3022   1.0000
   8.500   1.3033   0.02005   0.01155  -0.0624   0.2982   1.0000
   8.750   1.3198   0.02052   0.01202  -0.0609   0.2946   1.0000
   9.000   1.3366   0.02092   0.01252  -0.0594   0.2910   1.0000
   9.250   1.3520   0.02137   0.01304  -0.0577   0.2866   1.0000
   9.500   1.3655   0.02189   0.01356  -0.0558   0.2820   1.0000
   9.750   1.3793   0.02245   0.01415  -0.0541   0.2778   1.0000
  10.000   1.3924   0.02298   0.01480  -0.0524   0.2722   1.0000
  10.250   1.4031   0.02364   0.01548  -0.0504   0.2666   1.0000
  10.500   1.4141   0.02435   0.01623  -0.0486   0.2613   1.0000
  10.750   1.4254   0.02507   0.01706  -0.0470   0.2553   1.0000
  11.000   1.4343   0.02596   0.01796  -0.0453   0.2500   1.0000
  11.250   1.4449   0.02683   0.01892  -0.0438   0.2449   1.0000
  11.500   1.4537   0.02784   0.02001  -0.0423   0.2385   1.0000
  11.750   1.4596   0.02906   0.02125  -0.0408   0.2326   1.0000
  12.000   1.4672   0.03028   0.02257  -0.0395   0.2247   1.0000
  12.250   1.4704   0.03184   0.02416  -0.0381   0.2170   1.0000
  12.500   1.4742   0.03348   0.02585  -0.0369   0.2083   1.0000
  12.750   1.4766   0.03531   0.02773  -0.0358   0.2003   1.0000
  13.000   1.4768   0.03742   0.02987  -0.0348   0.1925   1.0000
  13.250   1.4763   0.03967   0.03218  -0.0340   0.1836   1.0000
  13.500   1.4728   0.04232   0.03485  -0.0333   0.1759   1.0000
  13.750   1.4684   0.04518   0.03775  -0.0328   0.1670   1.0000
  14.000   1.4613   0.04844   0.04103  -0.0324   0.1575   1.0000
  14.250   1.4518   0.05212   0.04472  -0.0323   0.1488   1.0000
  14.500   1.4430   0.05586   0.04850  -0.0324   0.1403   1.0000
  14.750   1.4346   0.05968   0.05238  -0.0326   0.1326   1.0000
  15.000   1.4245   0.06384   0.05658  -0.0330   0.1260   1.0000
  15.250   1.4157   0.06791   0.06072  -0.0335   0.1187   1.0000
  15.500   1.4038   0.07252   0.06537  -0.0343   0.1122   1.0000
  15.750   1.3898   0.07753   0.07043  -0.0353   0.1031   1.0000
  16.000   1.3753   0.08274   0.07570  -0.0364   0.0933   1.0000
  16.250   1.3514   0.08948   0.08242  -0.0382   0.0762   1.0000
  16.500   1.3245   0.09690   0.08981  -0.0404   0.0604   1.0000
  16.750   1.3024   0.10379   0.09670  -0.0426   0.0487   1.0000
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