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GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 429 AIRFOIL (goe429-il)
Reynolds number: 200,000
Max Cl/Cd: 47.45 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe429-il-200000.txt
Download as CSV file: xf-goe429-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 429 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -1.0715   0.09481   0.09077   0.0150   1.0000   0.0323
 -14.500  -1.1002   0.08558   0.08136   0.0090   1.0000   0.0320
 -14.250  -1.1262   0.07730   0.07288   0.0035   1.0000   0.0319
 -14.000  -1.1492   0.07001   0.06535  -0.0013   1.0000   0.0319
 -13.750  -1.1692   0.06368   0.05877  -0.0051   1.0000   0.0319
 -13.500  -1.1859   0.05824   0.05306  -0.0081   1.0000   0.0320
 -13.250  -1.1999   0.05356   0.04811  -0.0102   1.0000   0.0322
 -13.000  -1.2111   0.04966   0.04391  -0.0114   1.0000   0.0324
 -12.750  -1.2143   0.04596   0.04007  -0.0113   1.0000   0.0330
 -12.500  -1.2109   0.04349   0.03753  -0.0108   1.0000   0.0336
 -12.250  -1.2068   0.04145   0.03540  -0.0098   1.0000   0.0344
 -12.000  -1.1998   0.03945   0.03326  -0.0089   1.0000   0.0352
 -11.750  -1.1906   0.03739   0.03100  -0.0080   1.0000   0.0364
 -11.500  -1.1793   0.03544   0.02879  -0.0072   1.0000   0.0378
 -11.250  -1.1664   0.03331   0.02648  -0.0063   1.0000   0.0394
 -11.000  -1.1492   0.03201   0.02522  -0.0058   1.0000   0.0413
 -10.750  -1.1314   0.03069   0.02375  -0.0052   1.0000   0.0437
 -10.500  -1.1136   0.02900   0.02185  -0.0044   1.0000   0.0463
 -10.250  -1.0942   0.02774   0.02064  -0.0040   1.0000   0.0493
 -10.000  -1.0729   0.02679   0.01947  -0.0035   1.0000   0.0538
  -9.750  -1.0524   0.02559   0.01835  -0.0031   1.0000   0.0586
  -9.500  -1.0304   0.02455   0.01715  -0.0026   1.0000   0.0649
  -9.250  -1.0073   0.02383   0.01644  -0.0024   1.0000   0.0709
  -9.000  -0.9842   0.02286   0.01539  -0.0021   1.0000   0.0774
  -8.750  -0.9596   0.02230   0.01474  -0.0020   1.0000   0.0839
  -8.500  -0.9357   0.02129   0.01369  -0.0017   1.0000   0.0899
  -8.250  -0.9105   0.02065   0.01301  -0.0016   1.0000   0.0963
  -8.000  -0.8858   0.01971   0.01203  -0.0013   1.0000   0.1026
  -7.750  -0.8604   0.01904   0.01134  -0.0012   1.0000   0.1097
  -7.500  -0.8352   0.01815   0.01045  -0.0011   1.0000   0.1170
  -7.250  -0.8092   0.01748   0.00976  -0.0010   1.0000   0.1245
  -7.000  -0.7837   0.01661   0.00894  -0.0008   1.0000   0.1319
  -6.750  -0.7570   0.01600   0.00830  -0.0007   1.0000   0.1405
  -6.500  -0.7309   0.01527   0.00767  -0.0007   1.0000   0.1509
  -6.250  -0.7040   0.01465   0.00714  -0.0007   1.0000   0.1648
  -6.000  -0.6767   0.01408   0.00664  -0.0007   1.0000   0.1854
  -5.750  -0.6497   0.01344   0.00616  -0.0008   1.0000   0.2166
  -5.500  -0.6226   0.01285   0.00574  -0.0010   1.0000   0.2513
  -5.250  -0.5948   0.01241   0.00540  -0.0012   1.0000   0.2812
  -5.000  -0.5667   0.01205   0.00513  -0.0013   1.0000   0.3082
  -4.750  -0.5384   0.01172   0.00491  -0.0015   1.0000   0.3326
  -4.500  -0.5096   0.01145   0.00469  -0.0018   1.0000   0.3570
  -4.250  -0.4810   0.01117   0.00452  -0.0020   1.0000   0.3812
  -4.000  -0.4519   0.01094   0.00436  -0.0024   1.0000   0.4064
  -3.750  -0.4228   0.01070   0.00423  -0.0028   1.0000   0.4305
  -3.500  -0.3934   0.01050   0.00413  -0.0033   1.0000   0.4556
  -3.250  -0.3647   0.01032   0.00407  -0.0038   1.0000   0.4803
  -3.000  -0.3331   0.01020   0.00405  -0.0051   0.9913   0.5052
  -2.750  -0.2903   0.01011   0.00404  -0.0080   0.9679   0.5325
  -2.500  -0.2547   0.01008   0.00409  -0.0093   0.9444   0.5561
  -2.250  -0.2274   0.01014   0.00419  -0.0086   0.9219   0.5778
  -2.000  -0.2034   0.01023   0.00427  -0.0072   0.9006   0.5990
  -1.750  -0.1803   0.01031   0.00436  -0.0055   0.8809   0.6174
  -1.500  -0.1567   0.01037   0.00441  -0.0040   0.8622   0.6343
  -1.250  -0.1320   0.01041   0.00442  -0.0027   0.8447   0.6505
  -1.000  -0.1062   0.01044   0.00442  -0.0017   0.8284   0.6661
  -0.750  -0.0801   0.01046   0.00441  -0.0009   0.8126   0.6815
  -0.500  -0.0536   0.01046   0.00440  -0.0001   0.7967   0.6966
  -0.250  -0.0273   0.01045   0.00438   0.0007   0.7806   0.7113
   0.000  -0.0011   0.01043   0.00435   0.0016   0.7638   0.7258
   0.250   0.0250   0.01041   0.00432   0.0026   0.7464   0.7401
   0.500   0.0516   0.01036   0.00428   0.0033   0.7274   0.7543
   0.750   0.0781   0.01031   0.00425   0.0041   0.7081   0.7697
   1.000   0.1041   0.01026   0.00423   0.0051   0.6886   0.7877
   1.250   0.1299   0.01020   0.00419   0.0061   0.6684   0.8065
   1.500   0.1558   0.01013   0.00414   0.0070   0.6464   0.8242
   1.750   0.1816   0.01003   0.00408   0.0080   0.6196   0.8411
   2.000   0.2071   0.00996   0.00401   0.0090   0.5876   0.8580
   2.250   0.2317   0.00992   0.00393   0.0102   0.5473   0.8765
   2.500   0.2563   0.00997   0.00387   0.0114   0.4957   0.8986
   2.750   0.2833   0.01019   0.00388   0.0119   0.4396   0.9265
   3.000   0.3186   0.01055   0.00400   0.0104   0.3844   0.9605
   3.250   0.3585   0.01097   0.00418   0.0075   0.3365   1.0000
   3.500   0.3875   0.01137   0.00436   0.0067   0.3045   1.0000
   3.750   0.4166   0.01175   0.00457   0.0061   0.2803   1.0000
   4.000   0.4455   0.01213   0.00481   0.0056   0.2620   1.0000
   4.250   0.4743   0.01247   0.00507   0.0053   0.2472   1.0000
   4.500   0.5030   0.01279   0.00534   0.0050   0.2342   1.0000
   4.750   0.5315   0.01311   0.00562   0.0047   0.2226   1.0000
   5.000   0.5597   0.01345   0.00590   0.0045   0.2121   1.0000
   5.250   0.5882   0.01369   0.00617   0.0044   0.2016   1.0000
   5.500   0.6165   0.01392   0.00643   0.0042   0.1901   1.0000
   5.750   0.6449   0.01412   0.00664   0.0041   0.1747   1.0000
   6.000   0.6731   0.01437   0.00684   0.0039   0.1545   1.0000
   6.250   0.7008   0.01477   0.00715   0.0039   0.1241   1.0000
   6.500   0.7278   0.01544   0.00764   0.0038   0.0902   1.0000
   6.750   0.7541   0.01619   0.00826   0.0039   0.0772   1.0000
   7.000   0.7803   0.01693   0.00899   0.0039   0.0715   1.0000
   7.250   0.8059   0.01774   0.00980   0.0041   0.0676   1.0000
   7.500   0.8301   0.01880   0.01083   0.0043   0.0649   1.0000
   7.750   0.8551   0.01966   0.01175   0.0046   0.0634   1.0000
   8.000   0.8797   0.02058   0.01275   0.0049   0.0617   1.0000
   8.250   0.9038   0.02158   0.01379   0.0053   0.0599   1.0000
   8.500   0.9273   0.02269   0.01491   0.0056   0.0581   1.0000
   8.750   0.9504   0.02404   0.01625   0.0061   0.0568   1.0000
   9.000   0.9729   0.02587   0.01809   0.0066   0.0555   1.0000
   9.250   0.9959   0.02744   0.01980   0.0070   0.0546   1.0000
   9.500   1.0188   0.02868   0.02123   0.0075   0.0535   1.0000
   9.750   1.0407   0.03018   0.02293   0.0080   0.0524   1.0000
  10.000   1.0615   0.03192   0.02488   0.0085   0.0515   1.0000
  10.250   1.0810   0.03374   0.02690   0.0090   0.0505   1.0000
  10.500   1.0999   0.03560   0.02889   0.0095   0.0492   1.0000
  10.750   1.1172   0.03771   0.03113   0.0099   0.0481   1.0000
  11.000   1.1322   0.04051   0.03407   0.0104   0.0472   1.0000
  11.250   1.1421   0.04427   0.03809   0.0109   0.0467   1.0000
  11.500   1.1432   0.04915   0.04333   0.0114   0.0462   1.0000
  11.750   1.1402   0.05190   0.04644   0.0123   0.0459   1.0000
  12.000   1.1316   0.05495   0.04983   0.0131   0.0456   1.0000
  12.250   1.1143   0.05844   0.05358   0.0136   0.0455   1.0000
  12.500   1.0938   0.06303   0.05840   0.0121   0.0455   1.0000
  12.750   1.0709   0.06884   0.06443   0.0089   0.0457   1.0000
  13.000   1.0459   0.07594   0.07171   0.0046   0.0459   1.0000
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