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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 200,000
Max Cl/Cd: 73.73 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe176-il-200000.txt
Download as CSV file: xf-goe176-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 176 (ALBATROS 7020) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3071   0.10011   0.09682  -0.0338   1.0000   0.0447
  -8.250  -0.3136   0.09782   0.09461  -0.0344   1.0000   0.0449
  -8.000  -0.3209   0.09562   0.09250  -0.0339   1.0000   0.0450
  -7.750  -0.3179   0.09061   0.08753  -0.0316   1.0000   0.0462
  -7.500  -0.3121   0.08858   0.08555  -0.0292   1.0000   0.0473
  -7.250  -0.3155   0.08698   0.08402  -0.0268   1.0000   0.0483
  -7.000  -0.3249   0.08560   0.08275  -0.0243   1.0000   0.0492
  -6.750  -0.3210   0.08309   0.08028  -0.0258   0.9976   0.0510
  -6.500  -0.2695   0.07136   0.06849  -0.0558   0.9860   0.0574
  -6.250  -0.2533   0.07068   0.06783  -0.0491   0.9826   0.0601
  -6.000  -0.1349   0.04829   0.04557  -0.0638   0.9485   0.0746
  -5.750  -0.1818   0.05992   0.05697  -0.0686   0.9640   0.0726
  -5.500  -0.0795   0.03768   0.03485  -0.0791   0.9323   0.0881
  -5.250  -0.0679   0.02718   0.02230  -0.1104   0.9480   0.0435
  -5.000  -0.0296   0.02260   0.01707  -0.1140   0.9397   0.0406
  -4.750   0.0134   0.02024   0.01420  -0.1172   0.9343   0.0422
  -4.500   0.0530   0.01839   0.01195  -0.1194   0.9250   0.0434
  -4.250   0.0957   0.01679   0.01003  -0.1219   0.9163   0.0445
  -4.000   0.1370   0.01486   0.00797  -0.1245   0.9058   0.0479
  -3.750   0.1755   0.01387   0.00692  -0.1264   0.8922   0.0534
  -3.500   0.2113   0.01306   0.00597  -0.1276   0.8771   0.0586
  -3.250   0.2441   0.01244   0.00526  -0.1283   0.8610   0.0711
  -3.000   0.2745   0.01163   0.00483  -0.1287   0.8446   0.1625
  -2.750   0.3034   0.01212   0.00514  -0.1283   0.8277   0.2212
  -2.500   0.3310   0.01243   0.00528  -0.1278   0.8110   0.2421
  -2.250   0.3583   0.01258   0.00530  -0.1273   0.7948   0.2567
  -2.000   0.3854   0.01269   0.00529  -0.1268   0.7788   0.2704
  -1.750   0.4123   0.01270   0.00524  -0.1263   0.7633   0.2828
  -1.500   0.4391   0.01268   0.00516  -0.1259   0.7477   0.2953
  -1.250   0.4660   0.01260   0.00497  -0.1254   0.7315   0.3042
  -1.000   0.4930   0.01254   0.00481  -0.1249   0.7163   0.3123
  -0.750   0.5201   0.01245   0.00463  -0.1245   0.7018   0.3197
  -0.500   0.5472   0.01240   0.00451  -0.1241   0.6877   0.3279
  -0.250   0.5741   0.01233   0.00440  -0.1237   0.6737   0.3368
   0.000   0.6011   0.01232   0.00431  -0.1233   0.6595   0.3470
   0.250   0.6278   0.01227   0.00425  -0.1229   0.6449   0.3570
   0.500   0.6544   0.01223   0.00419  -0.1225   0.6296   0.3672
   0.750   0.6809   0.01221   0.00416  -0.1220   0.6134   0.3797
   1.000   0.7071   0.01221   0.00417  -0.1215   0.5955   0.3959
   1.250   0.7330   0.01221   0.00419  -0.1210   0.5756   0.4180
   1.500   0.7582   0.01221   0.00422  -0.1203   0.5533   0.4557
   1.750   0.7784   0.01153   0.00429  -0.1186   0.5288   0.7266
   2.000   0.8013   0.01140   0.00422  -0.1170   0.5011   1.0000
   2.250   0.8263   0.01168   0.00429  -0.1163   0.4727   1.0000
   2.500   0.8514   0.01196   0.00437  -0.1157   0.4472   1.0000
   2.750   0.8768   0.01224   0.00449  -0.1152   0.4266   1.0000
   3.000   0.9022   0.01254   0.00466  -0.1147   0.4114   1.0000
   3.250   0.9278   0.01285   0.00486  -0.1142   0.4001   1.0000
   3.500   0.9531   0.01319   0.00507  -0.1137   0.3910   1.0000
   3.750   0.9787   0.01351   0.00531  -0.1133   0.3811   1.0000
   4.000   1.0040   0.01386   0.00559  -0.1128   0.3725   1.0000
   4.250   1.0295   0.01421   0.00588  -0.1124   0.3654   1.0000
   4.500   1.0550   0.01457   0.00619  -0.1120   0.3594   1.0000
   4.750   1.0806   0.01489   0.00651  -0.1116   0.3526   1.0000
   5.000   1.1055   0.01533   0.00687  -0.1111   0.3459   1.0000
   5.250   1.1310   0.01561   0.00721  -0.1107   0.3392   1.0000
   5.500   1.1561   0.01602   0.00757  -0.1103   0.3336   1.0000
   5.750   1.1815   0.01636   0.00797  -0.1099   0.3286   1.0000
   6.000   1.2067   0.01666   0.00834  -0.1094   0.3231   1.0000
   6.250   1.2315   0.01708   0.00873  -0.1090   0.3181   1.0000
   6.500   1.2564   0.01741   0.00914  -0.1085   0.3132   1.0000
   6.750   1.2810   0.01770   0.00955  -0.1079   0.3075   1.0000
   7.000   1.3049   0.01814   0.00996  -0.1073   0.3016   1.0000
   7.250   1.3284   0.01833   0.01033  -0.1066   0.2938   1.0000
   7.500   1.3507   0.01866   0.01069  -0.1057   0.2849   1.0000
   7.750   1.3730   0.01882   0.01098  -0.1048   0.2731   1.0000
   8.000   1.3961   0.01903   0.01133  -0.1040   0.2625   1.0000
   8.250   1.4186   0.01927   0.01167  -0.1032   0.2497   1.0000
   8.500   1.4406   0.01954   0.01202  -0.1023   0.2307   1.0000
   8.750   1.4598   0.02001   0.01243  -0.1010   0.1972   1.0000
   9.000   1.4700   0.02121   0.01330  -0.0986   0.1571   1.0000
   9.250   1.4807   0.02246   0.01442  -0.0963   0.1346   1.0000
   9.500   1.4933   0.02351   0.01544  -0.0943   0.1168   1.0000
   9.750   1.5052   0.02452   0.01643  -0.0921   0.0964   1.0000
  10.000   1.5057   0.02610   0.01780  -0.0884   0.0667   1.0000
  10.250   1.5065   0.02772   0.01942  -0.0849   0.0586   1.0000
  10.500   1.5059   0.02950   0.02129  -0.0815   0.0528   1.0000
  10.750   1.5107   0.03099   0.02297  -0.0791   0.0467   1.0000
  11.000   1.5115   0.03289   0.02501  -0.0766   0.0408   1.0000
  11.250   1.5171   0.03454   0.02675  -0.0747   0.0337   1.0000
  11.500   1.5220   0.03634   0.02865  -0.0732   0.0286   1.0000
  11.750   1.5227   0.03864   0.03100  -0.0717   0.0261   1.0000
  12.000   1.5219   0.04125   0.03372  -0.0705   0.0247   1.0000
  12.250   1.5189   0.04422   0.03682  -0.0696   0.0237   1.0000
  12.500   1.5138   0.04761   0.04037  -0.0690   0.0229   1.0000
  12.750   1.5061   0.05148   0.04437  -0.0688   0.0223   1.0000
  13.000   1.4961   0.05583   0.04887  -0.0689   0.0218   1.0000
  13.250   1.4836   0.06067   0.05386  -0.0694   0.0214   1.0000
  13.500   1.4699   0.06580   0.05915  -0.0702   0.0211   1.0000
  13.750   1.4570   0.07097   0.06444  -0.0710   0.0209   1.0000
  14.000   1.4457   0.07597   0.06960  -0.0719   0.0206   1.0000
  14.250   1.4350   0.08100   0.07476  -0.0729   0.0203   1.0000
  14.500   1.4254   0.08594   0.07982  -0.0739   0.0200   1.0000
  14.750   1.4169   0.09069   0.08469  -0.0749   0.0197   1.0000
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