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GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 421 AIRFOIL (goe421-il)
Reynolds number: 100,000
Max Cl/Cd: 31.4 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe421-il-100000.txt
Download as CSV file: xf-goe421-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 421 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0151   0.12549   0.12060  -0.0975   0.8781   0.1534
  -9.000  -0.0481   0.12621   0.12139  -0.0961   0.8700   0.1574
  -8.750  -0.0926   0.12665   0.12193  -0.0959   0.8622   0.1586
  -8.500  -0.0267   0.11967   0.11483  -0.0968   0.8617   0.1615
  -8.250  -0.0028   0.11658   0.11170  -0.0991   0.8597   0.1671
  -8.000  -0.0354   0.11776   0.11297  -0.0920   0.8491   0.1686
  -7.750  -0.0846   0.11827   0.11356  -0.0934   0.8435   0.1730
  -7.500  -0.1276   0.11999   0.11539  -0.0849   0.8339   0.1730
  -7.250  -0.1173   0.11581   0.11121  -0.0848   0.8302   0.1747
  -7.000  -0.0668   0.11115   0.10646  -0.0870   0.8285   0.1781
  -6.750  -0.0511   0.10821   0.10348  -0.0888   0.8262   0.1827
  -6.500  -0.1044   0.11064   0.10606  -0.0781   0.8157   0.1815
  -6.250  -0.1183   0.10892   0.10435  -0.0777   0.8115   0.1859
  -6.000  -0.2217   0.08775   0.08302  -0.0970   0.8038   0.1309
  -5.750  -0.2207   0.08667   0.08195  -0.0948   0.7993   0.1317
  -5.500  -0.1875   0.09335   0.08869  -0.0897   0.7949   0.1576
  -5.250  -0.1584   0.09112   0.08645  -0.0894   0.7925   0.1613
  -5.000  -0.1841   0.09221   0.08762  -0.0828   0.7851   0.1626
  -4.750  -0.1004   0.05381   0.04648  -0.1318   0.7859   0.1343
  -4.500  -0.0794   0.05380   0.04637  -0.1317   0.7812   0.1390
  -4.250  -0.0383   0.05238   0.04455  -0.1348   0.7778   0.1461
  -4.000   0.0082   0.05206   0.04417  -0.1375   0.7752   0.1546
  -3.750   0.0000   0.05283   0.04468  -0.1339   0.7669   0.1585
  -3.500   0.0270   0.05326   0.04530  -0.1340   0.7621   0.1649
  -3.250   0.0718   0.05281   0.04468  -0.1365   0.7590   0.1777
  -3.000   0.0734   0.05395   0.04582  -0.1338   0.7511   0.1842
  -2.750   0.0999   0.05410   0.04592  -0.1340   0.7455   0.1964
  -2.500   0.1442   0.05373   0.04548  -0.1362   0.7420   0.2160
  -2.250   0.1499   0.05459   0.04625  -0.1341   0.7331   0.2281
  -2.000   0.1841   0.05438   0.04603  -0.1349   0.7271   0.2474
  -1.750   0.2352   0.05354   0.04520  -0.1375   0.7238   0.2702
  -1.500   0.2352   0.05469   0.04625  -0.1345   0.7118   0.2804
  -1.250   0.2795   0.05400   0.04554  -0.1362   0.7079   0.2986
  -1.000   0.2875   0.05495   0.04655  -0.1341   0.6982   0.3070
  -0.750   0.3207   0.05478   0.04625  -0.1348   0.6927   0.3217
  -0.500   0.3649   0.05401   0.04545  -0.1364   0.6899   0.3361
  -0.250   0.3645   0.05551   0.04692  -0.1338   0.6783   0.3416
   0.000   0.4027   0.05492   0.04631  -0.1348   0.6744   0.3530
   0.250   0.4481   0.05391   0.04520  -0.1367   0.6721   0.3648
   0.500   0.4441   0.05573   0.04704  -0.1337   0.6593   0.3696
   0.750   0.4864   0.05481   0.04599  -0.1352   0.6563   0.3801
   1.000   0.5323   0.05355   0.04468  -0.1369   0.6544   0.3889
   1.250   0.5292   0.05538   0.04648  -0.1341   0.6407   0.3926
   1.500   0.5730   0.05411   0.04516  -0.1355   0.6384   0.4016
   1.750   0.6190   0.05269   0.04367  -0.1372   0.6369   0.4124
   2.000   0.6146   0.05470   0.04570  -0.1342   0.6225   0.4167
   2.250   0.6578   0.05334   0.04435  -0.1355   0.6207   0.4286
   2.500   0.7033   0.05175   0.04277  -0.1370   0.6195   0.4446
   2.750   0.6983   0.05388   0.04494  -0.1339   0.6047   0.4538
   3.000   0.7044   0.05524   0.04639  -0.1319   0.5928   0.4672
   3.250   0.7413   0.05408   0.04532  -0.1324   0.5891   0.4980
   3.500   0.7844   0.05217   0.04374  -0.1334   0.5875   0.5692
   3.750   0.8188   0.04939   0.04168  -0.1321   0.5862   1.0000
   4.000   0.8642   0.04765   0.03969  -0.1333   0.5854   1.0000
   4.250   0.9113   0.04576   0.03762  -0.1346   0.5848   1.0000
   4.500   0.9612   0.04378   0.03548  -0.1364   0.5842   1.0000
   4.750   0.8953   0.05127   0.04309  -0.1283   0.5548   1.0000
   5.000   0.9371   0.04963   0.04133  -0.1290   0.5535   1.0000
   5.250   0.9505   0.05068   0.04233  -0.1277   0.5453   1.0000
   5.500   1.0062   0.04789   0.03941  -0.1295   0.5468   1.0000
   5.750   1.0650   0.04508   0.03647  -0.1320   0.5478   1.0000
   6.000   1.1317   0.04201   0.03326  -0.1356   0.5487   1.0000
   6.250   1.0772   0.04822   0.03958  -0.1280   0.5290   1.0000
   6.500   1.1419   0.04500   0.03624  -0.1311   0.5301   1.0000
   6.750   1.2214   0.04121   0.03230  -0.1361   0.5316   1.0000
   7.000   1.1418   0.04938   0.04064  -0.1262   0.5119   1.0000
   7.250   1.2113   0.04587   0.03701  -0.1297   0.5132   1.0000
   7.500   1.3028   0.04149   0.03245  -0.1362   0.5150   1.0000
   7.750   1.1937   0.05219   0.04340  -0.1239   0.4963   1.0000
   8.000   1.2613   0.04878   0.03990  -0.1271   0.4971   1.0000
   8.250   1.3493   0.04449   0.03546  -0.1330   0.4984   1.0000
   8.500   1.2231   0.05760   0.04885  -0.1204   0.4812   1.0000
   8.750   1.2836   0.05457   0.04575  -0.1228   0.4816   1.0000
   9.000   0.7394   0.13884   0.13113  -0.1178   0.5156   1.0000
   9.250   0.6927   0.14033   0.13269  -0.1154   0.5078   1.0000
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