Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 481A AIRFOIL (goe481a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.75 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe481a-il-1000000.txt
Download as CSV file: xf-goe481a-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 481A 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7486   0.03644   0.03330  -0.1468   0.9627   0.0429
 -13.250  -0.7508   0.03430   0.03104  -0.1463   0.9602   0.0431
 -13.000  -0.7433   0.03245   0.02906  -0.1461   0.9588   0.0432
 -12.750  -0.7528   0.03143   0.02798  -0.1408   0.9521   0.0433
 -12.500  -0.7398   0.03025   0.02672  -0.1397   0.9496   0.0435
 -12.250  -0.7217   0.02903   0.02541  -0.1395   0.9482   0.0437
 -12.000  -0.7000   0.02785   0.02414  -0.1397   0.9470   0.0440
 -11.750  -0.6749   0.02659   0.02278  -0.1404   0.9461   0.0442
 -11.500  -0.6462   0.02543   0.02151  -0.1417   0.9454   0.0446
 -11.250  -0.6502   0.02467   0.02067  -0.1360   0.9376   0.0447
 -11.000  -0.6254   0.02364   0.01955  -0.1362   0.9358   0.0450
 -10.750  -0.5987   0.02266   0.01847  -0.1366   0.9346   0.0453
 -10.500  -0.5707   0.02173   0.01745  -0.1371   0.9337   0.0456
 -10.250  -0.5417   0.02081   0.01643  -0.1378   0.9329   0.0459
 -10.000  -0.5112   0.01999   0.01551  -0.1387   0.9323   0.0462
  -9.750  -0.5041   0.01953   0.01498  -0.1346   0.9261   0.0464
  -9.500  -0.4808   0.01904   0.01441  -0.1338   0.9236   0.0467
  -9.250  -0.4547   0.01842   0.01371  -0.1335   0.9222   0.0468
  -9.000  -0.4318   0.01719   0.01237  -0.1331   0.9210   0.0473
  -8.750  -0.4043   0.01636   0.01151  -0.1332   0.9201   0.0478
  -8.500  -0.3744   0.01577   0.01089  -0.1336   0.9193   0.0481
  -8.250  -0.3426   0.01523   0.01033  -0.1344   0.9186   0.0485
  -8.000  -0.3104   0.01470   0.00978  -0.1353   0.9179   0.0489
  -7.750  -0.2974   0.01443   0.00946  -0.1321   0.9130   0.0492
  -7.500  -0.2755   0.01405   0.00905  -0.1307   0.9093   0.0496
  -7.250  -0.2450   0.01359   0.00855  -0.1311   0.9074   0.0500
  -7.000  -0.2128   0.01311   0.00803  -0.1319   0.9056   0.0504
  -6.750  -0.1798   0.01265   0.00752  -0.1328   0.9040   0.0509
  -6.500  -0.1415   0.01224   0.00706  -0.1348   0.9026   0.0514
  -6.250  -0.1264   0.01204   0.00683  -0.1319   0.8964   0.0516
  -6.000  -0.1008   0.01180   0.00655  -0.1311   0.8916   0.0519
  -5.750  -0.0681   0.01109   0.00580  -0.1321   0.8884   0.0528
  -5.500  -0.0243   0.01061   0.00531  -0.1354   0.8857   0.0536
  -5.250  -0.0209   0.01052   0.00521  -0.1299   0.8756   0.0538
  -5.000   0.0198   0.01016   0.00481  -0.1324   0.8701   0.0544
  -4.750   0.0349   0.01004   0.00466  -0.1294   0.8591   0.0551
  -4.500   0.0671   0.00979   0.00435  -0.1300   0.8489   0.0557
  -4.250   0.0916   0.00962   0.00413  -0.1290   0.8355   0.0563
  -4.000   0.1137   0.00950   0.00394  -0.1275   0.8190   0.0568
  -3.750   0.1361   0.00944   0.00376  -0.1260   0.7973   0.0573
  -3.500   0.1508   0.00936   0.00355  -0.1229   0.7675   0.0578
  -3.250   0.1606   0.00939   0.00342  -0.1188   0.7333   0.0586
  -2.750   0.1835   0.00954   0.00331  -0.1113   0.6775   0.0601
  -2.500   0.1985   0.00962   0.00330  -0.1083   0.6557   0.0609
  -2.250   0.2138   0.00969   0.00327  -0.1054   0.6363   0.0618
  -2.000   0.2302   0.00975   0.00325  -0.1028   0.6201   0.0627
  -1.750   0.2487   0.00980   0.00322  -0.1006   0.6057   0.0633
  -1.500   0.2678   0.00973   0.00312  -0.0985   0.5939   0.0649
  -1.000   0.3085   0.00973   0.00305  -0.0949   0.5728   0.0678
  -0.750   0.3283   0.00978   0.00303  -0.0930   0.5628   0.0693
  -0.500   0.3502   0.00974   0.00299  -0.0915   0.5545   0.0720
  -0.250   0.3703   0.00976   0.00298  -0.0897   0.5446   0.0751
   0.000   0.3913   0.00975   0.00297  -0.0881   0.5350   0.0799
   0.250   0.4118   0.00974   0.00299  -0.0864   0.5271   0.0898
   0.500   0.4320   0.00978   0.00307  -0.0846   0.5197   0.1066
   0.750   0.4549   0.00983   0.00315  -0.0834   0.5123   0.1176
   1.000   0.4760   0.00994   0.00323  -0.0818   0.5043   0.1235
   1.250   0.4987   0.01002   0.00331  -0.0805   0.4976   0.1283
   1.500   0.5217   0.01012   0.00339  -0.0794   0.4896   0.1316
   1.750   0.5420   0.01022   0.00345  -0.0777   0.4817   0.1351
   2.000   0.5657   0.01027   0.00352  -0.0766   0.4759   0.1386
   2.250   0.5879   0.01036   0.00359  -0.0753   0.4680   0.1413
   2.500   0.6090   0.01050   0.00368  -0.0738   0.4606   0.1437
   2.750   0.6322   0.01055   0.00374  -0.0727   0.4546   0.1455
   3.000   0.6528   0.01061   0.00379  -0.0711   0.4474   0.1489
   3.250   0.6731   0.01072   0.00388  -0.0695   0.4399   0.1514
   3.500   0.6954   0.01080   0.00396  -0.0682   0.4322   0.1544
   3.750   0.7155   0.01096   0.00407  -0.0666   0.4237   0.1571
   4.000   0.7380   0.01106   0.00417  -0.0654   0.4164   0.1589
   4.250   0.7584   0.01116   0.00424  -0.0639   0.4074   0.1633
   4.500   0.7796   0.01127   0.00436  -0.0625   0.4000   0.1668
   4.750   0.8010   0.01140   0.00447  -0.0612   0.3920   0.1705
   5.000   0.8203   0.01159   0.00461  -0.0595   0.3833   0.1723
   5.250   0.8421   0.01171   0.00473  -0.0582   0.3763   0.1743
   5.500   0.8622   0.01187   0.00488  -0.0567   0.3689   0.1798
   5.750   0.8835   0.01202   0.00504  -0.0555   0.3623   0.1846
   6.000   1.1021   0.01151   0.00630  -0.0984   0.3417   1.0000
   6.250   1.1213   0.01178   0.00650  -0.0967   0.3330   1.0000
   6.500   1.1414   0.01201   0.00670  -0.0952   0.3267   1.0000
   6.750   1.1625   0.01222   0.00688  -0.0939   0.3209   1.0000
   7.000   1.1824   0.01247   0.00710  -0.0924   0.3149   1.0000
   7.250   1.2025   0.01273   0.00733  -0.0910   0.3092   1.0000
   7.500   1.2232   0.01295   0.00754  -0.0897   0.3036   1.0000
   7.750   1.2420   0.01326   0.00781  -0.0881   0.2969   1.0000
   8.000   1.2614   0.01355   0.00807  -0.0866   0.2902   1.0000
   8.250   1.2809   0.01385   0.00834  -0.0852   0.2823   1.0000
   8.500   1.2992   0.01420   0.00865  -0.0836   0.2743   1.0000
   8.750   1.3181   0.01452   0.00895  -0.0821   0.2657   1.0000
   9.000   1.3348   0.01494   0.00932  -0.0803   0.2562   1.0000
   9.250   1.3511   0.01539   0.00971  -0.0784   0.2443   1.0000
   9.500   1.3673   0.01586   0.01012  -0.0766   0.2318   1.0000
   9.750   1.3812   0.01643   0.01062  -0.0745   0.2183   1.0000
  10.000   1.3935   0.01710   0.01120  -0.0722   0.2038   1.0000
  10.250   1.4060   0.01776   0.01180  -0.0699   0.1923   1.0000
  10.500   1.4193   0.01839   0.01239  -0.0678   0.1848   1.0000
  10.750   1.4331   0.01900   0.01298  -0.0659   0.1793   1.0000
  11.000   1.4475   0.01961   0.01358  -0.0641   0.1739   1.0000
  11.250   1.4605   0.02028   0.01424  -0.0621   0.1700   1.0000
  11.500   1.4734   0.02098   0.01494  -0.0602   0.1658   1.0000
  11.750   1.4894   0.02152   0.01550  -0.0587   0.1639   1.0000
  12.000   1.5036   0.02217   0.01618  -0.0570   0.1616   1.0000
  12.250   1.5170   0.02288   0.01690  -0.0553   0.1591   1.0000
  12.500   1.5289   0.02369   0.01772  -0.0535   0.1564   1.0000
  12.750   1.5379   0.02469   0.01872  -0.0514   0.1525   1.0000
  13.000   1.5541   0.02529   0.01937  -0.0502   0.1509   1.0000
  13.250   1.5674   0.02606   0.02017  -0.0487   0.1483   1.0000
  13.500   1.5787   0.02698   0.02110  -0.0470   0.1452   1.0000
  13.750   1.5883   0.02804   0.02218  -0.0453   0.1425   1.0000
  14.000   1.5965   0.02923   0.02338  -0.0435   0.1395   1.0000
  14.250   1.6110   0.03001   0.02422  -0.0424   0.1371   1.0000
  14.500   1.6225   0.03102   0.02526  -0.0410   0.1342   1.0000
  14.750   1.6301   0.03233   0.02658  -0.0395   0.1304   1.0000
  15.000   1.6374   0.03370   0.02797  -0.0380   0.1266   1.0000
  15.250   1.6467   0.03497   0.02926  -0.0367   0.1221   1.0000
  15.500   1.6497   0.03677   0.03104  -0.0351   0.1155   1.0000
  15.750   1.6523   0.03866   0.03292  -0.0336   0.1073   1.0000
  16.000   1.6516   0.04090   0.03515  -0.0322   0.0996   1.0000
  16.250   1.6482   0.04346   0.03770  -0.0307   0.0933   1.0000
  16.500   1.6432   0.04627   0.04051  -0.0294   0.0883   1.0000
  16.750   1.6419   0.04881   0.04311  -0.0285   0.0854   1.0000
  17.000   1.6400   0.05148   0.04582  -0.0276   0.0833   1.0000
  17.250   1.6354   0.05447   0.04885  -0.0269   0.0811   1.0000
  17.500   1.6302   0.05760   0.05204  -0.0263   0.0792   1.0000
  17.750   1.6290   0.06037   0.05488  -0.0259   0.0777   1.0000
  18.000   1.6272   0.06322   0.05780  -0.0255   0.0768   1.0000
  18.250   1.6239   0.06628   0.06092  -0.0253   0.0758   1.0000
  18.500   1.6173   0.06974   0.06444  -0.0251   0.0744   1.0000
  18.750   1.6088   0.07350   0.06826  -0.0251   0.0729   1.0000
  19.000   1.5997   0.07739   0.07222  -0.0252   0.0719   1.0000
  19.250   1.5966   0.08059   0.07550  -0.0253   0.0711   1.0000
<< Back to GOE 481A AIRFOIL (goe481a-il)

Polar data table (+)

Polar graphs


<< Back to GOE 481A AIRFOIL (goe481a-il)