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GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 503 AIRFOIL (goe503-il)
Reynolds number: 200,000
Max Cl/Cd: 67.01 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe503-il-200000-n5.txt
Download as CSV file: xf-goe503-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 503 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0863   0.09765   0.09403  -0.0977   0.9392   0.0196
 -11.250  -0.0982   0.08867   0.08505  -0.1032   0.9346   0.0199
 -11.000  -0.2819   0.05320   0.04937  -0.1268   0.9121   0.0190
 -10.500  -0.3500   0.03410   0.02940  -0.1373   0.8768   0.0185
 -10.250  -0.3408   0.03094   0.02592  -0.1377   0.8655   0.0190
 -10.000  -0.3235   0.02862   0.02330  -0.1383   0.8559   0.0195
  -9.750  -0.3103   0.02690   0.02130  -0.1372   0.8436   0.0201
  -9.500  -0.2933   0.02540   0.01952  -0.1364   0.8325   0.0208
  -9.250  -0.2730   0.02406   0.01800  -0.1361   0.8224   0.0218
  -9.000  -0.2528   0.02298   0.01671  -0.1354   0.8116   0.0233
  -8.750  -0.2326   0.02201   0.01549  -0.1345   0.8013   0.0250
  -8.500  -0.2093   0.02112   0.01447  -0.1342   0.7924   0.0270
  -8.250  -0.1889   0.02039   0.01355  -0.1330   0.7826   0.0295
  -8.000  -0.1654   0.01974   0.01276  -0.1325   0.7740   0.0327
  -7.750  -0.1425   0.01921   0.01209  -0.1317   0.7651   0.0375
  -7.500  -0.1178   0.01877   0.01147  -0.1312   0.7574   0.0431
  -7.250  -0.0936   0.01848   0.01105  -0.1305   0.7495   0.0485
  -7.000  -0.0688   0.01814   0.01054  -0.1300   0.7424   0.0530
  -6.750  -0.0456   0.01791   0.01018  -0.1292   0.7344   0.0574
  -6.250   0.0024   0.01740   0.00945  -0.1278   0.7205   0.0653
  -6.000   0.0276   0.01726   0.00914  -0.1272   0.7138   0.0701
  -5.750   0.0514   0.01707   0.00889  -0.1265   0.7073   0.0747
  -5.500   0.0750   0.01694   0.00868  -0.1256   0.7000   0.0789
  -5.000   0.1227   0.01644   0.00798  -0.1240   0.6871   0.0856
  -4.750   0.1468   0.01623   0.00769  -0.1232   0.6807   0.0890
  -4.500   0.1709   0.01603   0.00739  -0.1224   0.6745   0.0927
  -4.250   0.1941   0.01583   0.00709  -0.1214   0.6675   0.0966
  -4.000   0.2183   0.01560   0.00682  -0.1207   0.6616   0.1015
  -3.750   0.2410   0.01546   0.00664  -0.1196   0.6549   0.1076
  -3.500   0.2646   0.01530   0.00642  -0.1187   0.6484   0.1142
  -3.250   0.2884   0.01518   0.00625  -0.1178   0.6424   0.1213
  -3.000   0.3110   0.01507   0.00609  -0.1168   0.6355   0.1282
  -2.750   0.3349   0.01498   0.00597  -0.1160   0.6296   0.1359
  -2.500   0.3578   0.01491   0.00586  -0.1149   0.6234   0.1442
  -2.250   0.3807   0.01486   0.00580  -0.1139   0.6169   0.1532
  -2.000   0.4045   0.01483   0.00572  -0.1131   0.6112   0.1623
  -1.750   0.4268   0.01481   0.00567  -0.1119   0.6047   0.1715
  -1.500   0.4499   0.01479   0.00562  -0.1110   0.5989   0.1803
  -1.250   0.4730   0.01481   0.00559  -0.1100   0.5932   0.1920
  -1.000   0.4952   0.01482   0.00559  -0.1089   0.5870   0.2038
  -0.750   0.5182   0.01481   0.00555  -0.1079   0.5818   0.2136
  -0.500   0.5406   0.01483   0.00553  -0.1069   0.5763   0.2227
  -0.250   0.5622   0.01482   0.00553  -0.1057   0.5705   0.2313
   0.000   0.5854   0.01486   0.00549  -0.1047   0.5655   0.2407
   0.250   0.6067   0.01486   0.00552  -0.1035   0.5603   0.2490
   0.500   0.6282   0.01490   0.00554  -0.1023   0.5547   0.2579
   0.750   0.6505   0.01492   0.00555  -0.1012   0.5500   0.2670
   1.000   0.6717   0.01496   0.00559  -0.1000   0.5451   0.2776
   1.250   0.6924   0.01500   0.00566  -0.0986   0.5401   0.2909
   1.500   0.7134   0.01504   0.00571  -0.0974   0.5354   0.3050
   1.750   0.7350   0.01508   0.00576  -0.0962   0.5313   0.3242
   2.000   0.7521   0.01509   0.00587  -0.0942   0.5261   0.3464
   2.250   0.7702   0.01509   0.00594  -0.0923   0.5215   0.3799
   2.750   0.9240   0.01483   0.00697  -0.1136   0.5099   0.9721
   3.000   0.9680   0.01512   0.00720  -0.1173   0.5046   0.9885
   3.250   1.0141   0.01542   0.00739  -0.1215   0.4999   0.9987
   3.500   1.0338   0.01559   0.00757  -0.1202   0.4952   1.0000
   3.750   1.0476   0.01576   0.00772  -0.1176   0.4906   1.0000
   4.000   1.0620   0.01593   0.00784  -0.1151   0.4864   1.0000
   4.250   1.0768   0.01610   0.00797  -0.1127   0.4825   1.0000
   4.500   1.0866   0.01626   0.00815  -0.1093   0.4777   1.0000
   4.750   1.0989   0.01643   0.00832  -0.1064   0.4733   1.0000
   5.000   1.1135   0.01663   0.00846  -0.1040   0.4691   1.0000
   5.250   1.1277   0.01683   0.00867  -0.1016   0.4650   1.0000
   5.500   1.1400   0.01705   0.00892  -0.0988   0.4603   1.0000
   5.750   1.1543   0.01728   0.00914  -0.0964   0.4558   1.0000
   6.000   1.1704   0.01752   0.00932  -0.0945   0.4515   1.0000
   6.250   1.1826   0.01779   0.00965  -0.0918   0.4465   1.0000
   6.500   1.1951   0.01807   0.00995  -0.0892   0.4408   1.0000
   6.750   1.2096   0.01836   0.01018  -0.0871   0.4357   1.0000
   7.000   1.2205   0.01870   0.01058  -0.0844   0.4293   1.0000
   7.250   1.2322   0.01905   0.01092  -0.0818   0.4229   1.0000
   7.500   1.2448   0.01942   0.01131  -0.0795   0.4171   1.0000
   7.750   1.2565   0.01984   0.01177  -0.0772   0.4107   1.0000
   8.000   1.2697   0.02026   0.01218  -0.0751   0.4057   1.0000
   8.250   1.2825   0.02073   0.01270  -0.0730   0.4002   1.0000
   8.500   1.2949   0.02122   0.01324  -0.0710   0.3948   1.0000
   8.750   1.3075   0.02174   0.01374  -0.0690   0.3896   1.0000
   9.000   1.3197   0.02230   0.01437  -0.0671   0.3844   1.0000
   9.250   1.3315   0.02291   0.01502  -0.0651   0.3789   1.0000
   9.500   1.3436   0.02352   0.01564  -0.0633   0.3741   1.0000
   9.750   1.3549   0.02421   0.01640  -0.0615   0.3688   1.0000
  10.000   1.3653   0.02496   0.01720  -0.0596   0.3631   1.0000
  10.250   1.3758   0.02572   0.01796  -0.0578   0.3579   1.0000
  10.500   1.3838   0.02665   0.01898  -0.0558   0.3510   1.0000
  10.750   1.3885   0.02774   0.02005  -0.0535   0.3426   1.0000
  11.000   1.3948   0.02887   0.02126  -0.0516   0.3347   1.0000
  11.250   1.3972   0.03023   0.02260  -0.0494   0.3254   1.0000
  11.500   1.4016   0.03159   0.02403  -0.0476   0.3167   1.0000
  11.750   1.4048   0.03309   0.02554  -0.0458   0.3084   1.0000
  12.000   1.4080   0.03467   0.02717  -0.0441   0.2998   1.0000
  12.250   1.4116   0.03629   0.02883  -0.0426   0.2922   1.0000
  12.500   1.4116   0.03823   0.03079  -0.0410   0.2827   1.0000
  12.750   1.4123   0.04022   0.03282  -0.0396   0.2728   1.0000
  13.000   1.4112   0.04241   0.03503  -0.0381   0.2638   1.0000
  13.250   1.4090   0.04478   0.03742  -0.0368   0.2535   1.0000
  13.500   1.4072   0.04720   0.03987  -0.0356   0.2434   1.0000
  13.750   1.4036   0.04985   0.04255  -0.0345   0.2339   1.0000
  14.000   1.3988   0.05272   0.04543  -0.0335   0.2238   1.0000
  14.250   1.3970   0.05536   0.04812  -0.0327   0.2152   1.0000
  14.500   1.3904   0.05855   0.05132  -0.0319   0.2054   1.0000
  14.750   1.3838   0.06184   0.05462  -0.0312   0.1956   1.0000
  15.000   1.3756   0.06538   0.05818  -0.0306   0.1844   1.0000
  15.250   1.3655   0.06922   0.06201  -0.0302   0.1731   1.0000
  15.500   1.3567   0.07299   0.06579  -0.0299   0.1640   1.0000
  15.750   1.3442   0.07727   0.07005  -0.0296   0.1523   1.0000
  16.000   1.3373   0.08098   0.07380  -0.0296   0.1408   1.0000
  16.250   1.3219   0.08578   0.07856  -0.0296   0.1219   1.0000
  16.500   1.2966   0.09194   0.08457  -0.0299   0.0909   1.0000
  16.750   1.2682   0.09866   0.09113  -0.0304   0.0647   1.0000
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