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GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 342 AIRFOIL (goe342-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.77 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe342-il-1000000.txt
Download as CSV file: xf-goe342-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 342 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2101   0.08558   0.08397  -0.0513   0.9709   0.0128
  -7.250  -0.1938   0.08209   0.08046  -0.0556   0.9566   0.0128
  -7.000  -0.1855   0.07864   0.07698  -0.0553   0.9427   0.0130
  -6.750  -0.1719   0.07622   0.07452  -0.0569   0.9274   0.0132
  -6.500  -0.1556   0.07372   0.07195  -0.0595   0.9119   0.0136
  -6.250  -0.1370   0.07093   0.06910  -0.0629   0.8968   0.0142
  -6.000  -0.1144   0.06768   0.06577  -0.0675   0.8821   0.0155
  -5.750  -0.0757   0.06313   0.06112  -0.0785   0.8677   0.0159
  -5.500  -0.0428   0.05896   0.05685  -0.0863   0.8555   0.0160
  -5.250  -0.0216   0.05472   0.05254  -0.0896   0.8447   0.0162
  -5.000  -0.0020   0.05250   0.05027  -0.0910   0.8341   0.0164
  -4.750   0.0241   0.05017   0.04786  -0.0942   0.8239   0.0169
  -4.500   0.0551   0.04738   0.04501  -0.0987   0.8155   0.0179
  -4.250   0.1091   0.04311   0.04054  -0.1088   0.8085   0.0195
  -4.000   0.1475   0.03948   0.03679  -0.1142   0.8020   0.0196
  -3.750   0.1804   0.03487   0.03205  -0.1190   0.7956   0.0200
  -3.500   0.2067   0.03308   0.03019  -0.1207   0.7896   0.0203
  -3.250   0.2365   0.03122   0.02826  -0.1229   0.7834   0.0208
  -3.000   0.2688   0.02921   0.02613  -0.1253   0.7779   0.0216
  -2.750   0.3101   0.02683   0.02356  -0.1283   0.7734   0.0238
  -2.500   0.3475   0.02436   0.02088  -0.1306   0.7685   0.0240
  -2.250   0.3817   0.02194   0.01821  -0.1324   0.7629   0.0241
   0.000   0.6553   0.01063   0.00555  -0.1399   0.7122   0.0326
   0.250   0.6839   0.01024   0.00506  -0.1400   0.7032   0.0340
   0.500   0.7123   0.01034   0.00509  -0.1398   0.6955   0.0365
   0.750   0.7418   0.00952   0.00408  -0.1401   0.6878   0.0382
   1.000   0.7705   0.00898   0.00356  -0.1404   0.6781   0.0397
   1.250   0.7987   0.00870   0.00325  -0.1404   0.6653   0.0416
   1.500   0.8266   0.00857   0.00306  -0.1403   0.6471   0.0444
   1.750   0.8542   0.00825   0.00265  -0.1404   0.6159   0.0515
   2.000   0.8795   0.00843   0.00234  -0.1395   0.5294   0.0350
   2.250   0.9037   0.00888   0.00241  -0.1390   0.4505   0.0348
   2.500   0.9294   0.00915   0.00247  -0.1387   0.4036   0.0351
   2.750   0.9560   0.00931   0.00252  -0.1385   0.3770   0.0357
   3.000   0.9828   0.00943   0.00254  -0.1384   0.3574   0.0355
   3.250   1.0097   0.00954   0.00259  -0.1382   0.3422   0.0359
   3.500   1.0367   0.00965   0.00266  -0.1381   0.3312   0.0369
   3.750   1.0639   0.00972   0.00270  -0.1380   0.3224   0.0394
   4.250   1.1176   0.00996   0.00291  -0.1377   0.3059   0.0462
   4.500   1.1418   0.00882   0.00333  -0.1375   0.2989   1.0000
   4.750   1.1686   0.00896   0.00347  -0.1373   0.2920   1.0000
   5.000   1.1948   0.00918   0.00364  -0.1370   0.2829   1.0000
   5.250   1.2214   0.00934   0.00379  -0.1368   0.2737   1.0000
   5.500   1.2471   0.00959   0.00397  -0.1365   0.2573   1.0000
   5.750   1.2724   0.00989   0.00418  -0.1361   0.2365   1.0000
   6.000   1.2944   0.01056   0.00455  -0.1353   0.1822   1.0000
   6.250   1.3135   0.01159   0.00522  -0.1340   0.1213   1.0000
   6.500   1.3373   0.01204   0.00560  -0.1334   0.1075   1.0000
   6.750   1.3614   0.01242   0.00595  -0.1329   0.0968   1.0000
   7.000   1.3852   0.01283   0.00631  -0.1323   0.0848   1.0000
   7.250   1.4085   0.01327   0.00667  -0.1316   0.0713   1.0000
   7.500   1.4317   0.01373   0.00706  -0.1309   0.0608   1.0000
   7.750   1.4548   0.01416   0.00748  -0.1302   0.0539   1.0000
   8.000   1.4780   0.01456   0.00787  -0.1296   0.0473   1.0000
   8.250   1.4997   0.01512   0.00837  -0.1287   0.0359   1.0000
   8.500   1.5183   0.01600   0.00909  -0.1273   0.0203   1.0000
   8.750   1.5389   0.01663   0.00973  -0.1262   0.0166   1.0000
   9.000   1.5584   0.01735   0.01048  -0.1248   0.0144   1.0000
   9.250   1.5783   0.01798   0.01118  -0.1236   0.0134   1.0000
   9.500   1.5981   0.01857   0.01183  -0.1224   0.0127   1.0000
   9.750   1.6169   0.01923   0.01254  -0.1210   0.0119   1.0000
  10.000   1.6337   0.02003   0.01341  -0.1194   0.0111   1.0000
  10.250   1.6439   0.02136   0.01486  -0.1166   0.0102   1.0000
  10.500   1.6615   0.02192   0.01547  -0.1151   0.0100   1.0000
  10.750   1.6764   0.02261   0.01624  -0.1132   0.0096   1.0000
  11.000   1.6873   0.02341   0.01711  -0.1105   0.0092   1.0000
  11.250   1.6971   0.02429   0.01806  -0.1078   0.0089   1.0000
  11.500   1.7062   0.02526   0.01912  -0.1052   0.0086   1.0000
  11.750   1.7145   0.02633   0.02026  -0.1026   0.0083   1.0000
  12.000   1.7204   0.02761   0.02163  -0.0998   0.0080   1.0000
  12.250   1.7212   0.02936   0.02348  -0.0967   0.0077   1.0000
  12.500   1.7146   0.03183   0.02610  -0.0930   0.0075   1.0000
  12.750   1.7114   0.03416   0.02857  -0.0901   0.0073   1.0000
  13.000   1.7176   0.03575   0.03026  -0.0883   0.0072   1.0000
  13.250   1.7215   0.03759   0.03221  -0.0865   0.0071   1.0000
  13.500   1.7243   0.03963   0.03435  -0.0848   0.0070   1.0000
  13.750   1.7255   0.04191   0.03675  -0.0832   0.0069   1.0000
  14.000   1.7261   0.04430   0.03926  -0.0818   0.0067   1.0000
  14.250   1.7253   0.04694   0.04201  -0.0806   0.0066   1.0000
  14.500   1.7248   0.04964   0.04482  -0.0796   0.0064   1.0000
  14.750   1.7223   0.05264   0.04793  -0.0787   0.0063   1.0000
  15.000   1.7190   0.05581   0.05121  -0.0780   0.0062   1.0000
  15.250   1.7145   0.05929   0.05481  -0.0775   0.0060   1.0000
  15.500   1.7085   0.06312   0.05876  -0.0774   0.0059   1.0000
  15.750   1.7011   0.06730   0.06306  -0.0775   0.0059   1.0000
  16.000   1.6916   0.07201   0.06790  -0.0781   0.0058   1.0000
  16.250   1.6814   0.07710   0.07311  -0.0791   0.0057   1.0000
  16.500   1.6698   0.08261   0.07875  -0.0805   0.0057   1.0000
  16.750   1.6574   0.08848   0.08475  -0.0823   0.0056   1.0000
  17.000   1.6434   0.09483   0.09123  -0.0845   0.0056   1.0000
  17.250   1.6288   0.10142   0.09795  -0.0869   0.0055   1.0000
  17.500   1.6136   0.10819   0.10485  -0.0896   0.0055   1.0000
  17.750   1.5981   0.11510   0.11189  -0.0925   0.0055   1.0000
  18.000   1.5825   0.12214   0.11905  -0.0956   0.0054   1.0000
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