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GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 342 AIRFOIL (goe342-il)
Reynolds number: 100,000
Max Cl/Cd: 71.42 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe342-il-100000-n5.txt
Download as CSV file: xf-goe342-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2787   0.10742   0.10261  -0.0295   1.0000   0.0293
  -8.000  -0.2837   0.10606   0.10134  -0.0277   1.0000   0.0298
  -7.750  -0.2926   0.10515   0.10051  -0.0251   1.0000   0.0302
  -7.500  -0.2910   0.10339   0.09880  -0.0256   0.9968   0.0309
  -7.250  -0.2687   0.10060   0.09601  -0.0331   0.9880   0.0318
  -7.000  -0.2358   0.09849   0.09386  -0.0464   0.9781   0.0324
  -6.750  -0.2024   0.09545   0.09076  -0.0577   0.9700   0.0326
  -6.500  -0.1974   0.08873   0.08410  -0.0531   0.9683   0.0334
  -6.250  -0.1824   0.08454   0.07991  -0.0537   0.9631   0.0342
  -6.000  -0.1594   0.08075   0.07610  -0.0578   0.9584   0.0354
  -5.750  -0.1359   0.07732   0.07264  -0.0625   0.9520   0.0369
  -5.500  -0.1054   0.07371   0.06897  -0.0692   0.9470   0.0396
  -5.250  -0.0450   0.07122   0.06627  -0.0875   0.9383   0.0431
  -5.000  -0.0128   0.06660   0.06159  -0.0936   0.9344   0.0436
  -4.750  -0.0044   0.06282   0.05786  -0.0914   0.9288   0.0447
  -4.500   0.0184   0.05967   0.05467  -0.0937   0.9239   0.0466
  -4.250   0.0842   0.05673   0.05140  -0.1086   0.9206   0.0542
  -4.000   0.1050   0.05299   0.04766  -0.1104   0.9145   0.0553
  -3.750   0.1263   0.05007   0.04474  -0.1113   0.9099   0.0576
  -3.500   0.1934   0.04764   0.04186  -0.1237   0.9071   0.0657
  -3.250   0.2055   0.04424   0.03861  -0.1226   0.9028   0.0681
  -3.000   0.2468   0.04216   0.03628  -0.1280   0.8979   0.0786
  -2.750   0.2720   0.03969   0.03382  -0.1293   0.8940   0.0828
  -2.500   0.3175   0.03725   0.03113  -0.1348   0.8911   0.0925
  -2.000   0.3815   0.03342   0.02705  -0.1391   0.8792   0.1094
  -1.750   0.4240   0.03181   0.02515  -0.1429   0.8751   0.1328
  -1.250   0.5074   0.02667   0.01899  -0.1471   0.8630   0.0651
  -1.000   0.5397   0.02486   0.01710  -0.1484   0.8576   0.0610
  -0.750   0.5746   0.02362   0.01527  -0.1489   0.8504   0.0546
  -0.500   0.6082   0.02226   0.01372  -0.1498   0.8450   0.0537
  -0.250   0.6364   0.02128   0.01253  -0.1498   0.8349   0.0555
   0.000   0.6669   0.02032   0.01140  -0.1498   0.8257   0.0562
   0.250   0.6963   0.01967   0.01051  -0.1495   0.8165   0.0549
   0.500   0.7245   0.01915   0.00986  -0.1492   0.8088   0.0544
   0.750   0.7529   0.01855   0.00919  -0.1490   0.8015   0.0542
   1.000   0.7806   0.01809   0.00867  -0.1487   0.7940   0.0542
   1.250   0.8084   0.01768   0.00824  -0.1484   0.7861   0.0544
   1.500   0.8355   0.01728   0.00789  -0.1480   0.7777   0.0549
   1.750   0.8634   0.01691   0.00750  -0.1476   0.7691   0.0563
   2.000   0.8896   0.01675   0.00735  -0.1471   0.7584   0.0608
   2.250   0.9168   0.01661   0.00718  -0.1466   0.7479   0.0647
   2.500   0.9446   0.01646   0.00698  -0.1461   0.7372   0.0670
   2.750   0.9706   0.01642   0.00698  -0.1455   0.7241   0.0712
   3.000   0.9967   0.01640   0.00700  -0.1448   0.7098   0.0795
   3.250   1.0183   0.01507   0.00718  -0.1435   0.6941   1.0000
   3.500   1.0436   0.01517   0.00718  -0.1426   0.6747   1.0000
   3.750   1.0673   0.01531   0.00727  -0.1414   0.6477   1.0000
   4.000   1.0911   0.01545   0.00733  -0.1402   0.6109   1.0000
   4.250   1.1148   0.01561   0.00724  -0.1389   0.5635   1.0000
   4.500   1.1370   0.01601   0.00728  -0.1374   0.5179   1.0000
   4.750   1.1585   0.01658   0.00757  -0.1360   0.4817   1.0000
   5.000   1.1802   0.01719   0.00801  -0.1349   0.4537   1.0000
   5.250   1.2025   0.01777   0.00847  -0.1338   0.4329   1.0000
   5.500   1.2253   0.01832   0.00896  -0.1329   0.4169   1.0000
   6.000   1.2696   0.01949   0.01005  -0.1310   0.3820   1.0000
   6.250   1.2909   0.02008   0.01061  -0.1299   0.3633   1.0000
   6.500   1.3120   0.02068   0.01120  -0.1288   0.3454   1.0000
   6.750   1.3333   0.02126   0.01182  -0.1277   0.3299   1.0000
   7.000   1.3545   0.02183   0.01249  -0.1267   0.3151   1.0000
   7.250   1.3749   0.02241   0.01316  -0.1255   0.2978   1.0000
   7.500   1.3941   0.02303   0.01384  -0.1241   0.2768   1.0000
   7.750   1.4129   0.02364   0.01456  -0.1227   0.2483   1.0000
   8.000   1.4292   0.02445   0.01536  -0.1210   0.2060   1.0000
   8.250   1.4403   0.02576   0.01636  -0.1187   0.1622   1.0000
   8.500   1.4507   0.02725   0.01766  -0.1163   0.1384   1.0000
   8.750   1.4609   0.02871   0.01906  -0.1140   0.1223   1.0000
   9.000   1.4709   0.03010   0.02047  -0.1117   0.1084   1.0000
   9.250   1.4796   0.03143   0.02184  -0.1091   0.0968   1.0000
   9.500   1.4883   0.03268   0.02319  -0.1066   0.0857   1.0000
   9.750   1.4984   0.03386   0.02450  -0.1044   0.0750   1.0000
  10.000   1.5067   0.03520   0.02593  -0.1021   0.0645   1.0000
  10.250   1.5118   0.03682   0.02765  -0.0995   0.0553   1.0000
  10.500   1.5129   0.03882   0.02967  -0.0967   0.0473   1.0000
  10.750   1.5149   0.04083   0.03180  -0.0942   0.0400   1.0000
  11.000   1.5153   0.04306   0.03414  -0.0917   0.0350   1.0000
  11.250   1.5153   0.04538   0.03658  -0.0895   0.0317   1.0000
  11.500   1.5123   0.04809   0.03940  -0.0873   0.0297   1.0000
  11.750   1.5111   0.05075   0.04228  -0.0854   0.0279   1.0000
  12.000   1.5097   0.05351   0.04521  -0.0837   0.0262   1.0000
  12.250   1.5075   0.05642   0.04826  -0.0823   0.0247   1.0000
  12.500   1.5025   0.05974   0.05168  -0.0811   0.0235   1.0000
  12.750   1.4983   0.06312   0.05523  -0.0800   0.0225   1.0000
  13.000   1.4948   0.06652   0.05885  -0.0790   0.0217   1.0000
  13.250   1.4903   0.07014   0.06268  -0.0781   0.0210   1.0000
  13.500   1.4852   0.07395   0.06670  -0.0775   0.0205   1.0000
  13.750   1.4793   0.07795   0.07091  -0.0771   0.0200   1.0000
  14.000   1.4727   0.08220   0.07536  -0.0771   0.0196   1.0000
  14.250   1.4653   0.08670   0.08007  -0.0774   0.0192   1.0000
  14.500   1.4568   0.09155   0.08516  -0.0781   0.0189   1.0000
  14.750   1.4477   0.09670   0.09050  -0.0794   0.0186   1.0000
  15.000   1.4379   0.10219   0.09618  -0.0811   0.0183   1.0000
  15.250   1.4275   0.10800   0.10219  -0.0833   0.0180   1.0000
  15.500   1.4164   0.11417   0.10855  -0.0860   0.0178   1.0000
  15.750   1.4047   0.12074   0.11531  -0.0892   0.0176   1.0000
  16.000   1.3923   0.12775   0.12252  -0.0930   0.0174   1.0000
  16.250   1.3790   0.13536   0.13032  -0.0973   0.0174   1.0000
  16.500   1.3641   0.14382   0.13900  -0.1026   0.0174   1.0000
  16.750   1.3440   0.15437   0.14981  -0.1096   0.0177   1.0000
  17.000   1.2901   0.17843   0.17424  -0.1259   0.0194   1.0000
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