Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 478 AIRFOIL (goe478-il)
Reynolds number: 500,000
Max Cl/Cd: 95.42 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe478-il-500000-n5.txt
Download as CSV file: xf-goe478-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 478 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6979   0.03757   0.03382  -0.1100   0.9741   0.0270
 -12.000  -0.7024   0.03391   0.02986  -0.1117   0.9587   0.0270
 -11.750  -0.6903   0.03086   0.02651  -0.1138   0.9468   0.0271
 -11.500  -0.6665   0.02844   0.02387  -0.1167   0.9385   0.0273
 -11.250  -0.6375   0.02663   0.02190  -0.1194   0.9293   0.0275
 -11.000  -0.6077   0.02520   0.02031  -0.1217   0.9188   0.0277
 -10.750  -0.5784   0.02406   0.01903  -0.1233   0.9073   0.0279
 -10.500  -0.5545   0.02301   0.01781  -0.1238   0.8935   0.0280
 -10.250  -0.5334   0.02218   0.01683  -0.1233   0.8798   0.0282
 -10.000  -0.5132   0.02139   0.01589  -0.1225   0.8672   0.0284
  -9.500  -0.4738   0.01996   0.01416  -0.1204   0.8430   0.0288
  -9.250  -0.4532   0.01936   0.01343  -0.1193   0.8324   0.0291
  -9.000  -0.4326   0.01877   0.01269  -0.1182   0.8209   0.0294
  -8.750  -0.4117   0.01818   0.01195  -0.1171   0.8107   0.0297
  -8.500  -0.3902   0.01765   0.01128  -0.1161   0.8009   0.0300
  -8.250  -0.3682   0.01711   0.01060  -0.1151   0.7928   0.0303
  -8.000  -0.3456   0.01661   0.00998  -0.1142   0.7854   0.0305
  -7.750  -0.3226   0.01614   0.00939  -0.1133   0.7794   0.0307
  -7.500  -0.2990   0.01570   0.00885  -0.1125   0.7739   0.0309
  -7.250  -0.2759   0.01516   0.00826  -0.1117   0.7688   0.0312
  -7.000  -0.2522   0.01474   0.00777  -0.1109   0.7642   0.0315
  -6.750  -0.2278   0.01436   0.00735  -0.1102   0.7602   0.0318
  -6.500  -0.2031   0.01403   0.00699  -0.1096   0.7557   0.0321
  -6.250  -0.1783   0.01371   0.00663  -0.1089   0.7511   0.0325
  -6.000  -0.1532   0.01342   0.00628  -0.1083   0.7470   0.0329
  -5.750  -0.1279   0.01314   0.00595  -0.1078   0.7434   0.0334
  -5.500  -0.1024   0.01285   0.00564  -0.1072   0.7399   0.0338
  -5.250  -0.0769   0.01258   0.00532  -0.1066   0.7362   0.0343
  -5.000  -0.0512   0.01235   0.00505  -0.1061   0.7320   0.0348
  -4.750  -0.0256   0.01210   0.00476  -0.1055   0.7283   0.0355
  -4.250   0.0262   0.01165   0.00430  -0.1045   0.7214   0.0369
  -4.000   0.0521   0.01145   0.00409  -0.1039   0.7165   0.0378
  -3.750   0.0781   0.01127   0.00389  -0.1034   0.7120   0.0386
  -3.500   0.1043   0.01112   0.00369  -0.1029   0.7080   0.0395
  -3.250   0.1305   0.01094   0.00350  -0.1024   0.7046   0.0406
  -3.000   0.1567   0.01076   0.00335  -0.1019   0.7005   0.0419
  -2.750   0.1830   0.01061   0.00320  -0.1014   0.6957   0.0434
  -2.500   0.2092   0.01050   0.00306  -0.1009   0.6905   0.0452
  -2.250   0.2353   0.01036   0.00292  -0.1004   0.6860   0.0478
  -2.000   0.2616   0.01022   0.00280  -0.0999   0.6810   0.0509
  -1.750   0.2875   0.01008   0.00268  -0.0993   0.6751   0.0552
  -1.500   0.3131   0.00996   0.00256  -0.0987   0.6688   0.0617
  -1.250   0.3387   0.00978   0.00250  -0.0981   0.6613   0.0787
  -1.000   0.3639   0.00970   0.00245  -0.0974   0.6517   0.0969
  -0.750   0.3896   0.00962   0.00239  -0.0967   0.6408   0.1075
  -0.500   0.4145   0.00956   0.00233  -0.0959   0.6270   0.1165
  -0.250   0.4382   0.00953   0.00227  -0.0949   0.6058   0.1267
   0.250   0.4799   0.00964   0.00226  -0.0917   0.5509   0.1679
   0.500   0.5020   0.00973   0.00232  -0.0905   0.5338   0.1911
   0.750   0.5255   0.00980   0.00238  -0.0895   0.5219   0.2088
   1.000   0.5490   0.00986   0.00243  -0.0885   0.5125   0.2255
   1.250   0.5732   0.00988   0.00248  -0.0877   0.5042   0.2456
   1.500   0.5964   0.00990   0.00255  -0.0866   0.4963   0.2745
   1.750   0.6187   0.00969   0.00263  -0.0856   0.4900   0.3804
   2.000   0.6385   0.00937   0.00273  -0.0840   0.4839   0.5329
   2.250   0.6531   0.00898   0.00286  -0.0812   0.4780   0.7156
   2.500   0.7119   0.00876   0.00320  -0.0874   0.4684   0.9486
   2.750   0.7674   0.00903   0.00337  -0.0933   0.4555   0.9789
   3.250   0.8463   0.00941   0.00363  -0.0983   0.4383   0.9996
   3.500   0.8696   0.00952   0.00372  -0.0973   0.4315   1.0000
   3.750   0.8891   0.00967   0.00382  -0.0955   0.4237   1.0000
   4.000   0.9093   0.00980   0.00392  -0.0939   0.4170   1.0000
   4.250   0.9299   0.00993   0.00403  -0.0923   0.4102   1.0000
   4.500   0.9489   0.01010   0.00415  -0.0905   0.4032   1.0000
   4.750   0.9698   0.01023   0.00427  -0.0890   0.3962   1.0000
   5.000   0.9892   0.01040   0.00441  -0.0872   0.3883   1.0000
   5.250   1.0086   0.01057   0.00455  -0.0854   0.3795   1.0000
   5.500   1.0259   0.01079   0.00471  -0.0833   0.3681   1.0000
   5.750   1.0444   0.01098   0.00487  -0.0814   0.3560   1.0000
   6.000   1.0609   0.01121   0.00505  -0.0791   0.3440   1.0000
   6.250   1.0750   0.01146   0.00524  -0.0763   0.3303   1.0000
   6.500   1.0881   0.01176   0.00546  -0.0734   0.3129   1.0000
   6.750   1.0999   0.01215   0.00574  -0.0704   0.2914   1.0000
   7.000   1.1105   0.01263   0.00608  -0.0673   0.2677   1.0000
   7.250   1.1211   0.01316   0.00649  -0.0642   0.2436   1.0000
   7.500   1.1336   0.01367   0.00689  -0.0616   0.2259   1.0000
   7.750   1.1474   0.01414   0.00730  -0.0592   0.2117   1.0000
   8.000   1.1616   0.01462   0.00773  -0.0570   0.1998   1.0000
   8.250   1.1755   0.01514   0.00819  -0.0548   0.1883   1.0000
   8.500   1.1902   0.01564   0.00865  -0.0528   0.1778   1.0000
   8.750   1.2048   0.01615   0.00913  -0.0508   0.1685   1.0000
   9.000   1.2183   0.01674   0.00968  -0.0488   0.1591   1.0000
   9.250   1.2330   0.01730   0.01022  -0.0470   0.1506   1.0000
   9.500   1.2465   0.01793   0.01082  -0.0451   0.1423   1.0000
   9.750   1.2597   0.01860   0.01146  -0.0432   0.1341   1.0000
  10.000   1.2737   0.01926   0.01211  -0.0416   0.1275   1.0000
  10.250   1.2863   0.02001   0.01284  -0.0398   0.1205   1.0000
  10.500   1.2997   0.02074   0.01358  -0.0382   0.1147   1.0000
  10.750   1.3118   0.02158   0.01440  -0.0365   0.1084   1.0000
  11.000   1.3244   0.02241   0.01524  -0.0350   0.1030   1.0000
  11.250   1.3352   0.02340   0.01621  -0.0334   0.0965   1.0000
  11.500   1.3471   0.02433   0.01715  -0.0320   0.0914   1.0000
  11.750   1.3572   0.02542   0.01823  -0.0305   0.0859   1.0000
  12.000   1.3677   0.02650   0.01933  -0.0291   0.0811   1.0000
  12.250   1.3771   0.02770   0.02054  -0.0277   0.0768   1.0000
  12.500   1.3870   0.02890   0.02176  -0.0265   0.0736   1.0000
  12.750   1.3961   0.03018   0.02307  -0.0252   0.0707   1.0000
  13.000   1.4041   0.03158   0.02448  -0.0240   0.0683   1.0000
  13.250   1.4125   0.03298   0.02593  -0.0229   0.0665   1.0000
  13.500   1.4208   0.03442   0.02743  -0.0218   0.0649   1.0000
  13.750   1.4282   0.03595   0.02901  -0.0208   0.0633   1.0000
  14.000   1.4346   0.03762   0.03071  -0.0198   0.0620   1.0000
  14.250   1.4392   0.03948   0.03261  -0.0189   0.0605   1.0000
  14.500   1.4439   0.04139   0.03458  -0.0180   0.0593   1.0000
  14.750   1.4501   0.04319   0.03645  -0.0173   0.0586   1.0000
  15.000   1.4551   0.04515   0.03849  -0.0166   0.0578   1.0000
  15.250   1.4598   0.04720   0.04061  -0.0161   0.0570   1.0000
  15.500   1.4632   0.04943   0.04291  -0.0156   0.0561   1.0000
  15.750   1.4654   0.05184   0.04538  -0.0152   0.0552   1.0000
  16.000   1.4656   0.05453   0.04812  -0.0149   0.0540   1.0000
  16.250   1.4649   0.05741   0.05106  -0.0147   0.0531   1.0000
  16.500   1.4660   0.06014   0.05386  -0.0147   0.0523   1.0000
  16.750   1.4698   0.06259   0.05640  -0.0147   0.0514   1.0000
  17.000   1.4718   0.06528   0.05917  -0.0148   0.0506   1.0000
  17.250   1.4725   0.06814   0.06211  -0.0150   0.0497   1.0000
  17.500   1.4723   0.07117   0.06521  -0.0153   0.0488   1.0000
  17.750   1.4707   0.07439   0.06849  -0.0156   0.0482   1.0000
  18.000   1.4682   0.07774   0.07191  -0.0161   0.0474   1.0000
  18.250   1.4645   0.08124   0.07547  -0.0166   0.0469   1.0000
  18.500   1.4607   0.08480   0.07911  -0.0172   0.0463   1.0000
  18.750   1.4609   0.08786   0.08227  -0.0177   0.0458   1.0000
<< Back to GOE 478 AIRFOIL (goe478-il)

Polar data table (+)

Polar graphs


<< Back to GOE 478 AIRFOIL (goe478-il)