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GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
Reynolds number: 200,000
Max Cl/Cd: 84.29 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe332-il-200000-n5.txt
Download as CSV file: xf-goe332-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 332 (PFALZ 61) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1451   0.10352   0.09986  -0.0663   0.9613   0.0372
  -9.250  -0.1420   0.09996   0.09631  -0.0735   0.9446   0.0389
  -9.000  -0.1306   0.09579   0.09212  -0.0796   0.9304   0.0390
  -8.750  -0.1143   0.09121   0.08751  -0.0844   0.9183   0.0392
  -8.500  -0.0904   0.08752   0.08377  -0.0850   0.9097   0.0398
  -8.250  -0.0688   0.08424   0.08044  -0.0876   0.8977   0.0405
  -8.000  -0.0497   0.08122   0.07735  -0.0906   0.8833   0.0417
  -7.750  -0.0352   0.07821   0.07427  -0.0938   0.8673   0.0438
  -7.500  -0.0288   0.07418   0.07014  -0.1040   0.8482   0.0463
  -7.250  -0.0125   0.06980   0.06565  -0.1118   0.8351   0.0465
  -7.000   0.0055   0.06551   0.06121  -0.1178   0.8243   0.0466
  -6.750   0.0183   0.06193   0.05759  -0.1192   0.8143   0.0469
  -6.500   0.0324   0.05947   0.05507  -0.1191   0.8055   0.0473
  -6.250   0.0481   0.05740   0.05296  -0.1194   0.7961   0.0480
  -5.750   0.0938   0.04526   0.04035  -0.1324   0.7795   0.0387
  -5.500   0.1147   0.04260   0.03755  -0.1342   0.7722   0.0382
  -5.250   0.1374   0.03925   0.03403  -0.1365   0.7641   0.0377
  -5.000   0.1622   0.03546   0.02994  -0.1390   0.7574   0.0373
  -4.750   0.1877   0.03039   0.02444  -0.1416   0.7501   0.0379
  -4.500   0.2128   0.02651   0.02008  -0.1429   0.7435   0.0377
  -4.250   0.2384   0.02368   0.01678  -0.1436   0.7370   0.0376
  -4.000   0.2646   0.02165   0.01430  -0.1439   0.7300   0.0378
  -3.500   0.3184   0.01911   0.01106  -0.1440   0.7171   0.0383
  -3.250   0.3457   0.01831   0.00996  -0.1439   0.7108   0.0388
  -3.000   0.3727   0.01753   0.00900  -0.1439   0.7047   0.0397
  -2.750   0.3996   0.01695   0.00836  -0.1438   0.6980   0.0406
  -2.500   0.4270   0.01645   0.00772  -0.1437   0.6923   0.0413
  -2.250   0.4540   0.01598   0.00716  -0.1436   0.6857   0.0418
  -2.000   0.4812   0.01557   0.00666  -0.1434   0.6795   0.0425
  -1.750   0.5085   0.01522   0.00622  -0.1432   0.6738   0.0433
  -1.500   0.5354   0.01491   0.00587  -0.1430   0.6669   0.0442
  -1.250   0.5627   0.01466   0.00553  -0.1428   0.6608   0.0452
  -1.000   0.5896   0.01447   0.00529  -0.1426   0.6541   0.0464
  -0.750   0.6165   0.01422   0.00504  -0.1424   0.6474   0.0488
  -0.500   0.6437   0.01409   0.00486  -0.1423   0.6416   0.0514
  -0.250   0.6706   0.01397   0.00473  -0.1421   0.6350   0.0538
   0.000   0.6979   0.01386   0.00458  -0.1419   0.6292   0.0574
   0.250   0.7251   0.01377   0.00450  -0.1418   0.6237   0.0649
   0.500   0.7519   0.01365   0.00456  -0.1417   0.6174   0.1033
   0.750   0.7789   0.01364   0.00459  -0.1415   0.6117   0.1423
   1.000   0.8057   0.01364   0.00463  -0.1414   0.6058   0.1673
   1.250   0.8323   0.01359   0.00467  -0.1412   0.5995   0.1986
   1.750   0.8806   0.01211   0.00490  -0.1396   0.5876   1.0000
   2.000   0.9069   0.01226   0.00494  -0.1393   0.5811   1.0000
   2.250   0.9333   0.01241   0.00499  -0.1390   0.5753   1.0000
   2.500   0.9591   0.01255   0.00510  -0.1387   0.5681   1.0000
   2.750   0.9851   0.01271   0.00517  -0.1383   0.5616   1.0000
   3.000   1.0107   0.01286   0.00529  -0.1379   0.5541   1.0000
   3.250   1.0362   0.01303   0.00541  -0.1374   0.5469   1.0000
   3.500   1.0616   0.01319   0.00554  -0.1370   0.5398   1.0000
   3.750   1.0866   0.01337   0.00569  -0.1365   0.5319   1.0000
   4.000   1.1114   0.01355   0.00584  -0.1360   0.5239   1.0000
   4.250   1.1359   0.01374   0.00600  -0.1354   0.5153   1.0000
   4.500   1.1603   0.01394   0.00619  -0.1348   0.5071   1.0000
   4.750   1.1843   0.01416   0.00638  -0.1341   0.4985   1.0000
   5.000   1.2080   0.01438   0.00660  -0.1334   0.4893   1.0000
   5.250   1.2310   0.01464   0.00680  -0.1326   0.4805   1.0000
   5.500   1.2542   0.01488   0.00707  -0.1318   0.4707   1.0000
   5.750   1.2762   0.01517   0.00732  -0.1309   0.4604   1.0000
   6.000   1.2969   0.01549   0.00758  -0.1296   0.4483   1.0000
   6.250   1.3169   0.01583   0.00789  -0.1283   0.4349   1.0000
   6.500   1.3368   0.01618   0.00822  -0.1270   0.4224   1.0000
   6.750   1.3567   0.01655   0.00857  -0.1257   0.4120   1.0000
   7.000   1.3763   0.01694   0.00896  -0.1244   0.4032   1.0000
   7.250   1.3965   0.01731   0.00936  -0.1232   0.3952   1.0000
   7.500   1.4148   0.01774   0.00977  -0.1217   0.3870   1.0000
   7.750   1.4326   0.01814   0.01021  -0.1201   0.3784   1.0000
   8.250   1.4651   0.01906   0.01118  -0.1164   0.3618   1.0000
   8.500   1.4807   0.01958   0.01171  -0.1145   0.3549   1.0000
   8.750   1.4976   0.02006   0.01226  -0.1129   0.3478   1.0000
   9.000   1.5112   0.02067   0.01289  -0.1108   0.3393   1.0000
   9.250   1.5248   0.02128   0.01355  -0.1088   0.3293   1.0000
   9.500   1.5354   0.02203   0.01430  -0.1064   0.3180   1.0000
   9.750   1.5439   0.02291   0.01516  -0.1038   0.3057   1.0000
  10.000   1.5538   0.02377   0.01606  -0.1016   0.2929   1.0000
  10.250   1.5629   0.02474   0.01707  -0.0994   0.2802   1.0000
  10.500   1.5702   0.02585   0.01820  -0.0971   0.2663   1.0000
  10.750   1.5761   0.02713   0.01948  -0.0948   0.2515   1.0000
  11.000   1.5802   0.02861   0.02094  -0.0926   0.2353   1.0000
  11.250   1.5834   0.03025   0.02257  -0.0905   0.2194   1.0000
  11.500   1.5844   0.03215   0.02446  -0.0883   0.2031   1.0000
  11.750   1.5838   0.03428   0.02655  -0.0863   0.1874   1.0000
  12.000   1.5819   0.03662   0.02886  -0.0844   0.1723   1.0000
  12.250   1.5782   0.03920   0.03142  -0.0825   0.1565   1.0000
  12.500   1.5742   0.04191   0.03410  -0.0808   0.1402   1.0000
  12.750   1.5680   0.04494   0.03710  -0.0792   0.1211   1.0000
  13.000   1.5574   0.04853   0.04059  -0.0777   0.1006   1.0000
  13.250   1.5465   0.05231   0.04431  -0.0764   0.0865   1.0000
  13.500   1.5383   0.05591   0.04791  -0.0754   0.0753   1.0000
  13.750   1.5294   0.05971   0.05173  -0.0746   0.0571   1.0000
  14.000   1.5100   0.06489   0.05676  -0.0738   0.0376   1.0000
  14.250   1.4988   0.06925   0.06115  -0.0734   0.0324   1.0000
  14.500   1.4914   0.07326   0.06525  -0.0731   0.0295   1.0000
  14.750   1.4837   0.07742   0.06950  -0.0731   0.0275   1.0000
  15.000   1.4766   0.08157   0.07375  -0.0731   0.0260   1.0000
  15.250   1.4718   0.08548   0.07780  -0.0733   0.0248   1.0000
  15.500   1.4657   0.08965   0.08210  -0.0736   0.0237   1.0000
  15.750   1.4585   0.09406   0.08663  -0.0741   0.0229   1.0000
  16.000   1.4499   0.09874   0.09142  -0.0748   0.0221   1.0000
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