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GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.15 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe303-il-1000000-n5.txt
Download as CSV file: xf-goe303-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2166   0.06573   0.06368  -0.0797   0.8782   0.0145
  -8.000  -0.1996   0.06292   0.06083  -0.0836   0.8700   0.0147
  -7.750  -0.2120   0.01890   0.01531  -0.1255   0.8586   0.0200
  -7.500  -0.1877   0.01693   0.01299  -0.1259   0.8512   0.0206
  -7.250  -0.1621   0.01572   0.01153  -0.1260   0.8426   0.0210
  -7.000  -0.1353   0.01504   0.01067  -0.1260   0.8333   0.0213
  -6.750  -0.1085   0.01451   0.00996  -0.1259   0.8221   0.0215
  -6.500  -0.0829   0.01338   0.00861  -0.1259   0.8090   0.0219
  -6.250  -0.0559   0.01293   0.00803  -0.1257   0.7939   0.0222
  -6.000  -0.0290   0.01258   0.00754  -0.1256   0.7769   0.0224
  -5.750  -0.0020   0.01227   0.00710  -0.1254   0.7593   0.0227
  -5.500   0.0253   0.01204   0.00675  -0.1252   0.7433   0.0230
  -5.250   0.0526   0.01178   0.00636  -0.1251   0.7286   0.0233
  -4.750   0.1075   0.01110   0.00542  -0.1249   0.7022   0.0239
  -4.500   0.1352   0.01079   0.00500  -0.1248   0.6911   0.0242
  -4.250   0.1629   0.01051   0.00460  -0.1247   0.6800   0.0245
  -4.000   0.1907   0.01025   0.00425  -0.1246   0.6691   0.0248
  -3.750   0.2187   0.01001   0.00393  -0.1246   0.6592   0.0251
  -3.500   0.2464   0.00983   0.00364  -0.1245   0.6485   0.0253
  -3.250   0.2743   0.00968   0.00342  -0.1244   0.6362   0.0256
  -3.000   0.3023   0.00959   0.00325  -0.1243   0.6239   0.0259
  -2.750   0.3300   0.00941   0.00299  -0.1242   0.6117   0.0261
  -2.500   0.3576   0.00917   0.00266  -0.1241   0.6007   0.0267
  -2.250   0.3857   0.00901   0.00246  -0.1241   0.5910   0.0271
  -2.000   0.4136   0.00892   0.00232  -0.1240   0.5809   0.0276
  -1.750   0.4413   0.00886   0.00220  -0.1239   0.5689   0.0280
  -1.500   0.4693   0.00880   0.00210  -0.1239   0.5581   0.0284
  -1.250   0.4973   0.00875   0.00201  -0.1238   0.5496   0.0289
  -1.000   0.5252   0.00872   0.00193  -0.1238   0.5395   0.0294
  -0.750   0.5531   0.00870   0.00186  -0.1237   0.5297   0.0300
  -0.500   0.5809   0.00871   0.00182  -0.1236   0.5191   0.0306
  -0.250   0.6087   0.00872   0.00179  -0.1236   0.5085   0.0313
   0.000   0.6366   0.00871   0.00175  -0.1235   0.5002   0.0323
   0.250   0.6644   0.00872   0.00173  -0.1235   0.4913   0.0340
   0.500   0.6923   0.00873   0.00172  -0.1234   0.4829   0.0357
   0.750   0.7199   0.00877   0.00173  -0.1233   0.4742   0.0381
   1.000   0.7478   0.00876   0.00175  -0.1233   0.4666   0.0494
   1.250   0.7753   0.00878   0.00181  -0.1233   0.4579   0.0746
   1.500   0.8030   0.00881   0.00185  -0.1232   0.4495   0.0889
   1.750   0.8303   0.00886   0.00192  -0.1231   0.4402   0.1093
   2.000   0.8577   0.00887   0.00201  -0.1231   0.4299   0.1566
   2.250   0.8849   0.00892   0.00210  -0.1230   0.4195   0.1920
   2.500   0.9117   0.00892   0.00222  -0.1229   0.4077   0.2691
   3.000   0.9625   0.00788   0.00260  -0.1224   0.3795   1.0000
   3.250   0.9885   0.00811   0.00273  -0.1221   0.3616   1.0000
   3.500   1.0141   0.00837   0.00287  -0.1217   0.3416   1.0000
   3.750   1.0395   0.00865   0.00304  -0.1213   0.3222   1.0000
   4.000   1.0647   0.00894   0.00322  -0.1209   0.3037   1.0000
   4.250   1.0899   0.00922   0.00341  -0.1205   0.2872   1.0000
   4.500   1.1152   0.00948   0.00360  -0.1201   0.2735   1.0000
   4.750   1.1408   0.00971   0.00378  -0.1197   0.2629   1.0000
   5.000   1.1661   0.00995   0.00397  -0.1193   0.2538   1.0000
   5.500   1.2158   0.01050   0.00440  -0.1184   0.2324   1.0000
   5.750   1.2404   0.01077   0.00463  -0.1180   0.2244   1.0000
   6.000   1.2660   0.01096   0.00481  -0.1176   0.2202   1.0000
   6.250   1.2911   0.01117   0.00502  -0.1172   0.2160   1.0000
   6.500   1.3158   0.01141   0.00524  -0.1168   0.2118   1.0000
   6.750   1.3405   0.01163   0.00547  -0.1163   0.2072   1.0000
   7.000   1.3653   0.01184   0.00568  -0.1159   0.2028   1.0000
   7.250   1.3894   0.01209   0.00593  -0.1154   0.1985   1.0000
   7.500   1.4129   0.01237   0.00620  -0.1147   0.1934   1.0000
   7.750   1.4372   0.01259   0.00643  -0.1142   0.1888   1.0000
   8.000   1.4595   0.01293   0.00674  -0.1134   0.1799   1.0000
   8.250   1.4824   0.01321   0.00701  -0.1127   0.1723   1.0000
   8.500   1.5034   0.01360   0.00735  -0.1117   0.1603   1.0000
   8.750   1.5191   0.01431   0.00788  -0.1098   0.1328   1.0000
   9.000   1.5291   0.01530   0.00867  -0.1070   0.1018   1.0000
   9.250   1.5418   0.01599   0.00928  -0.1045   0.0871   1.0000
   9.500   1.5550   0.01661   0.00987  -0.1022   0.0781   1.0000
   9.750   1.5704   0.01714   0.01039  -0.1002   0.0721   1.0000
  10.000   1.5843   0.01776   0.01101  -0.0981   0.0661   1.0000
  10.250   1.5998   0.01831   0.01157  -0.0964   0.0617   1.0000
  10.500   1.6124   0.01904   0.01228  -0.0942   0.0557   1.0000
  10.750   1.6263   0.01972   0.01296  -0.0924   0.0506   1.0000
  11.000   1.6380   0.02054   0.01377  -0.0903   0.0452   1.0000
  11.250   1.6493   0.02142   0.01465  -0.0882   0.0393   1.0000
  11.500   1.6573   0.02253   0.01573  -0.0859   0.0311   1.0000
  12.000   1.6647   0.02552   0.01866  -0.0806   0.0149   1.0000
  12.250   1.6733   0.02673   0.01993  -0.0787   0.0132   1.0000
  12.500   1.6819   0.02801   0.02125  -0.0770   0.0120   1.0000
  12.750   1.6890   0.02942   0.02272  -0.0752   0.0110   1.0000
  13.000   1.6975   0.03077   0.02413  -0.0738   0.0104   1.0000
  13.250   1.7051   0.03225   0.02568  -0.0723   0.0099   1.0000
  13.500   1.7111   0.03391   0.02740  -0.0709   0.0093   1.0000
  13.750   1.7157   0.03576   0.02931  -0.0695   0.0088   1.0000
  14.000   1.7190   0.03779   0.03142  -0.0682   0.0084   1.0000
  14.250   1.7239   0.03975   0.03345  -0.0672   0.0081   1.0000
  14.500   1.7278   0.04186   0.03565  -0.0663   0.0078   1.0000
  14.750   1.7305   0.04416   0.03802  -0.0654   0.0075   1.0000
  15.000   1.7322   0.04666   0.04060  -0.0647   0.0072   1.0000
  15.250   1.7325   0.04938   0.04340  -0.0641   0.0069   1.0000
  15.500   1.7316   0.05233   0.04643  -0.0636   0.0067   1.0000
  15.750   1.7289   0.05553   0.04971  -0.0633   0.0064   1.0000
  16.000   1.7254   0.05891   0.05319  -0.0630   0.0062   1.0000
  16.250   1.7232   0.06223   0.05660  -0.0629   0.0061   1.0000
  16.500   1.7198   0.06575   0.06023  -0.0630   0.0060   1.0000
  16.750   1.7151   0.06948   0.06406  -0.0631   0.0059   1.0000
  17.000   1.7093   0.07341   0.06809  -0.0634   0.0058   1.0000
  17.250   1.7026   0.07757   0.07235  -0.0639   0.0056   1.0000
  17.500   1.6953   0.08188   0.07675  -0.0645   0.0055   1.0000
  17.750   1.6865   0.08642   0.08140  -0.0652   0.0054   1.0000
  18.000   1.6768   0.09116   0.08625  -0.0660   0.0053   1.0000
  18.250   1.6663   0.09613   0.09132  -0.0671   0.0053   1.0000
  18.500   1.6550   0.10129   0.09659  -0.0684   0.0052   1.0000
  18.750   1.6430   0.10662   0.10202  -0.0698   0.0051   1.0000
  19.000   1.6304   0.11209   0.10760  -0.0714   0.0050   1.0000
  19.250   1.6177   0.11769   0.11331  -0.0732   0.0049   1.0000
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