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GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 269 AIRFOIL (goe269-il)
Reynolds number: 50,000
Max Cl/Cd: 36.12 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe269-il-50000.txt
Download as CSV file: xf-goe269-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 269 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3513   0.10990   0.10293  -0.0129   1.0000   0.1155
  -8.000  -0.3494   0.10808   0.10118  -0.0145   1.0000   0.1194
  -7.750  -0.3533   0.10836   0.10158  -0.0192   1.0000   0.1215
  -7.500  -0.3419   0.10275   0.09602  -0.0177   1.0000   0.1242
  -7.250  -0.3311   0.09888   0.09216  -0.0170   1.0000   0.1293
  -7.000  -0.3256   0.09686   0.09021  -0.0199   1.0000   0.1344
  -6.750  -0.3194   0.09710   0.09054  -0.0293   1.0000   0.1370
  -6.500  -0.3102   0.09068   0.08416  -0.0229   1.0000   0.1405
  -6.250  -0.3016   0.08775   0.08129  -0.0232   1.0000   0.1460
  -6.000  -0.2898   0.08802   0.08159  -0.0335   1.0000   0.1517
  -5.750  -0.2867   0.08249   0.07617  -0.0267   1.0000   0.1553
  -5.500  -0.2785   0.08025   0.07398  -0.0279   1.0000   0.1638
  -5.250  -0.2711   0.07752   0.07131  -0.0291   1.0000   0.1691
  -5.000  -0.2643   0.07515   0.06897  -0.0287   1.0000   0.1778
  -4.750  -0.2562   0.07259   0.06646  -0.0300   1.0000   0.1840
  -4.500  -0.2401   0.07118   0.06498  -0.0347   1.0000   0.1960
  -4.250  -0.2408   0.06778   0.06172  -0.0300   1.0000   0.2007
  -4.000  -0.2281   0.06561   0.05952  -0.0322   1.0000   0.2127
  -3.500  -0.2061   0.06107   0.05500  -0.0334   1.0000   0.2423
  -3.250  -0.1983   0.05873   0.05270  -0.0321   1.0000   0.2608
  -3.000  -0.1867   0.05660   0.05058  -0.0323   1.0000   0.2896
  -2.750  -0.1740   0.05500   0.04898  -0.0324   1.0000   0.3323
  -2.500  -0.1697   0.05244   0.04655  -0.0292   1.0000   0.3667
  -2.250  -0.1648   0.05069   0.04488  -0.0259   1.0000   0.4259
  -2.000  -0.1653   0.04814   0.04250  -0.0204   1.0000   0.4749
  -1.750  -0.1639   0.04581   0.04028  -0.0150   1.0000   0.5262
  -1.500  -0.1553   0.04367   0.03822  -0.0120   1.0000   0.5816
  -1.250  -0.1483   0.04136   0.03600  -0.0081   1.0000   0.6231
  -1.000  -0.1355   0.03919   0.03390  -0.0061   1.0000   0.6638
  -0.750  -0.1114   0.03724   0.03197  -0.0074   1.0000   0.6942
  -0.500   0.1356   0.03725   0.03022  -0.0690   0.9822   0.4306
  -0.250   0.2422   0.03670   0.02814  -0.0858   0.9675   0.2699
   0.000   0.3076   0.03534   0.02621  -0.0928   0.9547   0.2282
   0.250   0.3677   0.03430   0.02473  -0.0986   0.9412   0.2146
   0.500   0.4211   0.03344   0.02356  -0.1033   0.9264   0.2159
   0.750   0.4731   0.03272   0.02252  -0.1074   0.9112   0.2158
   1.000   0.5245   0.03204   0.02158  -0.1111   0.8960   0.2294
   1.250   0.5746   0.03138   0.02078  -0.1143   0.8808   0.2420
   1.500   0.6197   0.03069   0.02015  -0.1167   0.8652   0.2641
   1.750   0.6612   0.03015   0.01976  -0.1183   0.8493   0.2912
   2.000   0.6940   0.02977   0.01986  -0.1189   0.8315   0.3542
   2.250   0.7210   0.02895   0.01996  -0.1175   0.8139   1.0000
   2.500   0.7521   0.02941   0.02007  -0.1170   0.7968   1.0000
   2.750   0.7821   0.02983   0.02026  -0.1164   0.7801   1.0000
   3.000   0.8107   0.03028   0.02058  -0.1158   0.7640   1.0000
   3.250   0.8382   0.03076   0.02098  -0.1150   0.7483   1.0000
   3.500   0.8647   0.03132   0.02148  -0.1141   0.7329   1.0000
   3.750   0.8904   0.03192   0.02209  -0.1132   0.7177   1.0000
   4.000   0.9154   0.03258   0.02274  -0.1122   0.7027   1.0000
   4.250   0.9400   0.03324   0.02342  -0.1111   0.6877   1.0000
   4.500   0.9646   0.03383   0.02407  -0.1098   0.6723   1.0000
   4.750   0.9897   0.03414   0.02440  -0.1081   0.6557   1.0000
   5.000   1.0161   0.03409   0.02437  -0.1061   0.6381   1.0000
   5.250   1.0436   0.03381   0.02409  -0.1038   0.6204   1.0000
   5.500   1.0707   0.03358   0.02389  -0.1017   0.6029   1.0000
   5.750   1.0910   0.03423   0.02465  -0.0999   0.5829   1.0000
   6.000   1.1144   0.03448   0.02498  -0.0981   0.5636   1.0000
   6.250   1.1403   0.03439   0.02498  -0.0961   0.5447   1.0000
   6.500   1.1672   0.03415   0.02474  -0.0941   0.5250   1.0000
   6.750   1.1885   0.03454   0.02526  -0.0921   0.5015   1.0000
   7.000   1.2146   0.03434   0.02504  -0.0899   0.4778   1.0000
   7.250   1.2403   0.03434   0.02501  -0.0879   0.4520   1.0000
   7.500   1.2616   0.03506   0.02575  -0.0859   0.4239   1.0000
   7.750   1.2825   0.03602   0.02670  -0.0840   0.3964   1.0000
   8.000   1.3055   0.03696   0.02756  -0.0823   0.3718   1.0000
   8.250   1.3239   0.03829   0.02904  -0.0806   0.3484   1.0000
   8.500   1.3476   0.03923   0.02987  -0.0792   0.3281   1.0000
   8.750   1.3626   0.04096   0.03187  -0.0774   0.3088   1.0000
   9.000   1.3799   0.04248   0.03354  -0.0758   0.2907   1.0000
   9.250   1.3990   0.04370   0.03481  -0.0741   0.2724   1.0000
   9.500   1.4188   0.04476   0.03585  -0.0724   0.2530   1.0000
   9.750   1.4287   0.04581   0.03704  -0.0699   0.2303   1.0000
  10.000   1.4388   0.04627   0.03737  -0.0673   0.2047   1.0000
  10.250   1.4488   0.04757   0.03844  -0.0649   0.1798   1.0000
  10.500   1.4528   0.05015   0.04106  -0.0621   0.1578   1.0000
  10.750   1.4613   0.05344   0.04420  -0.0599   0.1385   1.0000
  11.000   1.4667   0.05684   0.04769  -0.0577   0.1250   1.0000
  11.250   1.4559   0.06069   0.05212  -0.0544   0.1189   1.0000
  11.500   1.4662   0.06452   0.05592  -0.0530   0.1111   1.0000
  11.750   1.4479   0.06885   0.06077  -0.0499   0.1094   1.0000
  12.000   1.4256   0.07308   0.06536  -0.0468   0.1085   1.0000
  12.250   1.4004   0.07785   0.07044  -0.0449   0.1082   1.0000
  12.500   1.3726   0.08343   0.07629  -0.0446   0.1086   1.0000
  12.750   1.3430   0.08994   0.08303  -0.0457   0.1095   1.0000
  13.000   1.3130   0.09739   0.09063  -0.0482   0.1105   1.0000
  13.250   1.2842   0.10569   0.09904  -0.0518   0.1115   1.0000
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