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GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il)
Reynolds number: 200,000
Max Cl/Cd: 83.22 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe303-il-200000.txt
Download as CSV file: xf-goe303-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2962   0.10511   0.10178  -0.0275   1.0000   0.0421
  -8.250  -0.3072   0.10389   0.10062  -0.0254   1.0000   0.0429
  -8.000  -0.3236   0.10320   0.10001  -0.0230   1.0000   0.0436
  -7.750  -0.3107   0.09945   0.09626  -0.0404   0.9901   0.0444
  -7.500  -0.2951   0.09421   0.09103  -0.0391   0.9879   0.0450
  -7.250  -0.2732   0.09037   0.08718  -0.0393   0.9856   0.0460
  -7.000  -0.2487   0.08653   0.08333  -0.0437   0.9806   0.0476
  -6.750  -0.2201   0.08218   0.07895  -0.0522   0.9742   0.0509
  -6.500  -0.1806   0.07526   0.07191  -0.0720   0.9638   0.0534
  -6.250  -0.1598   0.07177   0.06844  -0.0713   0.9609   0.0544
  -6.000  -0.1286   0.06815   0.06479  -0.0754   0.9584   0.0563
  -5.750  -0.0792   0.06352   0.05992  -0.0910   0.9480   0.0625
  -5.500  -0.0476   0.05768   0.05403  -0.0969   0.9452   0.0641
  -5.250  -0.0243   0.05498   0.05134  -0.0977   0.9391   0.0657
  -5.000   0.0094   0.05179   0.04809  -0.1019   0.9338   0.0687
  -4.750   0.0662   0.04595   0.04178  -0.1145   0.9300   0.0760
  -4.500   0.0869   0.04347   0.03938  -0.1144   0.9214   0.0776
  -4.250   0.1187   0.04112   0.03699  -0.1166   0.9161   0.0813
  -4.000   0.1600   0.03755   0.03290  -0.1219   0.9077   0.0901
  -3.750   0.1866   0.03499   0.03038  -0.1228   0.9004   0.0921
  -3.500   0.2132   0.03315   0.02847  -0.1234   0.8909   0.0956
  -3.250   0.2490   0.03071   0.02560  -0.1257   0.8829   0.1061
  -3.000   0.2718   0.02907   0.02399  -0.1253   0.8713   0.1096
  -2.750   0.3034   0.02753   0.02207  -0.1262   0.8618   0.1221
  -2.500   0.3397   0.02163   0.01525  -0.1266   0.8523   0.0774
  -2.250   0.3681   0.01972   0.01302  -0.1262   0.8410   0.0708
  -2.000   0.3974   0.01832   0.01129  -0.1260   0.8310   0.0706
  -1.750   0.4257   0.01718   0.00988  -0.1255   0.8194   0.0707
  -1.500   0.4534   0.01621   0.00868  -0.1251   0.8071   0.0706
  -1.250   0.4815   0.01546   0.00773  -0.1246   0.7957   0.0715
  -1.000   0.5100   0.01486   0.00696  -0.1243   0.7848   0.0732
  -0.750   0.5374   0.01429   0.00628  -0.1238   0.7725   0.0763
  -0.500   0.5642   0.01388   0.00588  -0.1234   0.7595   0.0814
  -0.250   0.5914   0.01357   0.00548  -0.1228   0.7465   0.0871
   0.000   0.6184   0.01317   0.00508  -0.1224   0.7340   0.0974
   0.250   0.6456   0.01283   0.00477  -0.1220   0.7221   0.1293
   0.500   0.6721   0.01256   0.00466  -0.1216   0.7095   0.1929
   0.750   0.7009   0.01069   0.00464  -0.1218   0.6971   1.0000
   1.000   0.7277   0.01085   0.00457  -0.1213   0.6851   1.0000
   1.250   0.7549   0.01102   0.00453  -0.1209   0.6746   1.0000
   1.500   0.7812   0.01118   0.00459  -0.1205   0.6634   1.0000
   1.750   0.8080   0.01136   0.00465  -0.1201   0.6535   1.0000
   2.000   0.8350   0.01154   0.00470  -0.1198   0.6441   1.0000
   2.250   0.8613   0.01171   0.00482  -0.1194   0.6340   1.0000
   2.500   0.8883   0.01191   0.00491  -0.1191   0.6252   1.0000
   2.750   0.9144   0.01208   0.00504  -0.1187   0.6150   1.0000
   3.000   0.9407   0.01227   0.00516  -0.1183   0.6053   1.0000
   3.250   0.9671   0.01246   0.00526  -0.1179   0.5955   1.0000
   3.500   0.9926   0.01263   0.00543  -0.1174   0.5845   1.0000
   3.750   1.0185   0.01283   0.00558  -0.1169   0.5742   1.0000
   4.000   1.0444   0.01303   0.00571  -0.1165   0.5638   1.0000
   4.250   1.0695   0.01322   0.00592  -0.1159   0.5524   1.0000
   4.500   1.0947   0.01343   0.00610  -0.1153   0.5412   1.0000
   4.750   1.1198   0.01365   0.00626  -0.1148   0.5297   1.0000
   5.000   1.1441   0.01386   0.00648  -0.1140   0.5166   1.0000
   5.250   1.1680   0.01408   0.00669  -0.1133   0.5023   1.0000
   5.500   1.1914   0.01432   0.00691  -0.1124   0.4869   1.0000
   5.750   1.2142   0.01459   0.00714  -0.1114   0.4703   1.0000
   6.000   1.2364   0.01490   0.00741  -0.1104   0.4526   1.0000
   6.250   1.2579   0.01524   0.00772  -0.1092   0.4329   1.0000
   6.500   1.2787   0.01563   0.00807  -0.1079   0.4123   1.0000
   6.750   1.2987   0.01610   0.00845  -0.1066   0.3922   1.0000
   7.000   1.3180   0.01663   0.00886  -0.1051   0.3737   1.0000
   7.250   1.3377   0.01716   0.00931  -0.1038   0.3571   1.0000
   7.500   1.3574   0.01771   0.00980  -0.1025   0.3431   1.0000
   7.750   1.3774   0.01822   0.01032  -0.1013   0.3303   1.0000
   8.000   1.3973   0.01875   0.01086  -0.1001   0.3192   1.0000
   8.250   1.4166   0.01934   0.01140  -0.0988   0.3096   1.0000
   8.500   1.4362   0.01987   0.01196  -0.0976   0.3007   1.0000
   8.750   1.4561   0.02047   0.01258  -0.0964   0.2934   1.0000
   9.000   1.4752   0.02101   0.01318  -0.0951   0.2858   1.0000
   9.250   1.4940   0.02164   0.01382  -0.0938   0.2787   1.0000
   9.500   1.5113   0.02218   0.01447  -0.0923   0.2711   1.0000
   9.750   1.5278   0.02284   0.01514  -0.0906   0.2635   1.0000
  10.000   1.5403   0.02339   0.01579  -0.0883   0.2552   1.0000
  10.250   1.5519   0.02406   0.01651  -0.0859   0.2465   1.0000
  10.500   1.5616   0.02478   0.01724  -0.0833   0.2371   1.0000
  10.750   1.5711   0.02546   0.01809  -0.0807   0.2274   1.0000
  11.000   1.5795   0.02634   0.01900  -0.0782   0.2180   1.0000
  11.250   1.5866   0.02726   0.02000  -0.0757   0.2072   1.0000
  11.500   1.5939   0.02823   0.02110  -0.0734   0.1947   1.0000
  11.750   1.6004   0.02936   0.02232  -0.0712   0.1809   1.0000
  12.000   1.6053   0.03071   0.02372  -0.0691   0.1649   1.0000
  12.250   1.6078   0.03236   0.02538  -0.0670   0.1466   1.0000
  12.500   1.6071   0.03441   0.02738  -0.0648   0.1299   1.0000
  12.750   1.6043   0.03677   0.02971  -0.0628   0.1173   1.0000
  13.000   1.6004   0.03936   0.03230  -0.0609   0.1077   1.0000
  13.250   1.5948   0.04225   0.03519  -0.0593   0.0996   1.0000
  13.500   1.5918   0.04502   0.03805  -0.0580   0.0919   1.0000
  13.750   1.5832   0.04848   0.04153  -0.0568   0.0856   1.0000
  14.000   1.5781   0.05174   0.04489  -0.0560   0.0781   1.0000
  14.250   1.5696   0.05551   0.04874  -0.0554   0.0710   1.0000
  14.500   1.5565   0.05999   0.05324  -0.0551   0.0648   1.0000
  14.750   1.5473   0.06423   0.05758  -0.0550   0.0574   1.0000
  15.000   1.5328   0.06920   0.06260  -0.0552   0.0527   1.0000
  15.250   1.5228   0.07378   0.06727  -0.0555   0.0482   1.0000
  15.500   1.5074   0.07911   0.07261  -0.0561   0.0456   1.0000
  15.750   1.5007   0.08342   0.07707  -0.0567   0.0426   1.0000
  16.000   1.4921   0.08804   0.08178  -0.0574   0.0404   1.0000
  16.250   1.4813   0.09300   0.08677  -0.0584   0.0387   1.0000
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