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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 500,000
Max Cl/Cd: 99.17 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe176-il-500000.txt
Download as CSV file: xf-goe176-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3149   0.08941   0.08735  -0.0328   1.0000   0.0205
  -8.000  -0.3266   0.08554   0.08355  -0.0313   1.0000   0.0210
  -7.750  -0.3307   0.08364   0.08170  -0.0296   0.9998   0.0212
  -7.500  -0.3065   0.08002   0.07807  -0.0348   0.9961   0.0216
  -7.250  -0.2799   0.07581   0.07385  -0.0415   0.9913   0.0223
  -7.000  -0.2523   0.07074   0.06878  -0.0500   0.9851   0.0233
  -6.750  -0.2257   0.06440   0.06243  -0.0602   0.9730   0.0248
  -6.500  -0.1753   0.04279   0.04040  -0.0950   0.9455   0.0266
  -6.250  -0.1372   0.02418   0.02063  -0.1134   0.9340   0.0192
  -6.000  -0.0912   0.01954   0.01533  -0.1196   0.9237   0.0187
  -5.750  -0.0445   0.01750   0.01283  -0.1240   0.9094   0.0197
  -5.500  -0.0057   0.01587   0.01077  -0.1265   0.8900   0.0202
  -5.250   0.0249   0.01452   0.00907  -0.1271   0.8699   0.0207
  -5.000   0.0525   0.01300   0.00737  -0.1273   0.8511   0.0218
  -4.750   0.0800   0.01242   0.00666  -0.1271   0.8334   0.0229
  -4.500   0.1075   0.01199   0.00610  -0.1269   0.8173   0.0244
  -4.250   0.1352   0.01174   0.00571  -0.1266   0.8016   0.0262
  -4.000   0.1627   0.01089   0.00471  -0.1264   0.7863   0.0281
  -3.750   0.1903   0.01045   0.00417  -0.1262   0.7705   0.0305
  -3.500   0.2179   0.01019   0.00379  -0.1260   0.7538   0.0335
  -3.250   0.2455   0.00979   0.00324  -0.1257   0.7355   0.0379
  -3.000   0.2732   0.00953   0.00286  -0.1255   0.7169   0.0433
  -2.750   0.3010   0.00925   0.00248  -0.1253   0.6991   0.0553
  -2.500   0.3284   0.00872   0.00232  -0.1254   0.6821   0.1750
  -2.250   0.3558   0.00881   0.00236  -0.1251   0.6652   0.2017
  -2.000   0.3832   0.00891   0.00235  -0.1247   0.6478   0.2148
  -1.750   0.4106   0.00904   0.00234  -0.1244   0.6318   0.2251
  -1.500   0.4380   0.00909   0.00234  -0.1242   0.6162   0.2347
  -1.250   0.4654   0.00917   0.00232  -0.1239   0.6006   0.2423
  -1.000   0.4928   0.00923   0.00232  -0.1237   0.5859   0.2497
  -0.750   0.5202   0.00932   0.00231  -0.1234   0.5707   0.2575
  -0.500   0.5474   0.00937   0.00232  -0.1231   0.5545   0.2641
  -0.250   0.5746   0.00946   0.00230  -0.1229   0.5354   0.2692
   0.000   0.6012   0.00956   0.00229  -0.1225   0.5117   0.2746
   0.250   0.6279   0.00968   0.00231  -0.1222   0.4834   0.2812
   0.500   0.6540   0.00986   0.00233  -0.1218   0.4421   0.2885
   0.750   0.6785   0.01021   0.00242  -0.1212   0.3835   0.2963
   1.000   0.7042   0.01048   0.00253  -0.1207   0.3599   0.3036
   1.250   0.7307   0.01065   0.00265  -0.1205   0.3486   0.3125
   1.500   0.7577   0.01076   0.00276  -0.1203   0.3408   0.3238
   1.750   0.7844   0.01090   0.00289  -0.1200   0.3338   0.3389
   2.250   0.8388   0.01097   0.00319  -0.1198   0.3237   0.4171
   2.500   0.8652   0.01063   0.00343  -0.1199   0.3184   0.6529
   2.750   0.8853   0.01014   0.00352  -0.1178   0.3141   1.0000
   3.000   0.9125   0.01030   0.00364  -0.1176   0.3081   1.0000
   3.250   0.9389   0.01053   0.00380  -0.1173   0.3032   1.0000
   3.500   0.9659   0.01069   0.00395  -0.1171   0.2993   1.0000
   3.750   0.9932   0.01082   0.00407  -0.1170   0.2952   1.0000
   4.000   1.0200   0.01099   0.00423  -0.1167   0.2905   1.0000
   4.250   1.0461   0.01123   0.00442  -0.1164   0.2857   1.0000
   4.500   1.0736   0.01132   0.00454  -0.1163   0.2807   1.0000
   4.750   1.1002   0.01148   0.00469  -0.1161   0.2747   1.0000
   5.000   1.1266   0.01166   0.00486  -0.1158   0.2691   1.0000
   5.250   1.1535   0.01179   0.00501  -0.1156   0.2625   1.0000
   5.500   1.1796   0.01199   0.00519  -0.1153   0.2553   1.0000
   5.750   1.2059   0.01216   0.00535  -0.1150   0.2443   1.0000
   6.000   1.2310   0.01245   0.00554  -0.1146   0.2204   1.0000
   6.250   1.2468   0.01368   0.00626  -0.1129   0.1433   1.0000
   6.500   1.2692   0.01422   0.00674  -0.1121   0.1278   1.0000
   6.750   1.2915   0.01477   0.00721  -0.1112   0.1132   1.0000
   7.000   1.3138   0.01529   0.00767  -0.1104   0.0986   1.0000
   7.250   1.3326   0.01613   0.00831  -0.1091   0.0663   1.0000
   7.500   1.3538   0.01671   0.00890  -0.1081   0.0605   1.0000
   7.750   1.3748   0.01729   0.00950  -0.1070   0.0568   1.0000
   8.000   1.3959   0.01783   0.01008  -0.1060   0.0530   1.0000
   8.250   1.4181   0.01823   0.01056  -0.1051   0.0512   1.0000
   8.500   1.4387   0.01875   0.01116  -0.1041   0.0476   1.0000
   8.750   1.4571   0.01945   0.01188  -0.1027   0.0426   1.0000
   9.000   1.4800   0.01971   0.01212  -0.1020   0.0343   1.0000
   9.250   1.4937   0.02070   0.01294  -0.0999   0.0179   1.0000
   9.500   1.5096   0.02147   0.01378  -0.0981   0.0158   1.0000
   9.750   1.5231   0.02230   0.01473  -0.0959   0.0149   1.0000
  10.000   1.5326   0.02323   0.01578  -0.0931   0.0141   1.0000
  10.250   1.5395   0.02436   0.01702  -0.0901   0.0133   1.0000
  10.500   1.5427   0.02576   0.01855  -0.0867   0.0126   1.0000
  10.750   1.5451   0.02729   0.02020  -0.0837   0.0121   1.0000
  11.000   1.5509   0.02865   0.02168  -0.0813   0.0118   1.0000
  11.250   1.5539   0.03034   0.02348  -0.0790   0.0115   1.0000
  11.500   1.5548   0.03236   0.02562  -0.0770   0.0112   1.0000
  11.750   1.5541   0.03471   0.02809  -0.0753   0.0110   1.0000
  12.000   1.5521   0.03736   0.03089  -0.0740   0.0107   1.0000
  12.250   1.5486   0.04038   0.03403  -0.0730   0.0105   1.0000
  12.500   1.5435   0.04374   0.03751  -0.0723   0.0103   1.0000
  12.750   1.5369   0.04747   0.04137  -0.0720   0.0102   1.0000
  13.000   1.5288   0.05151   0.04553  -0.0720   0.0100   1.0000
  13.250   1.5195   0.05587   0.05001  -0.0722   0.0099   1.0000
  13.500   1.5097   0.06037   0.05462  -0.0726   0.0098   1.0000
  13.750   1.4988   0.06508   0.05944  -0.0731   0.0097   1.0000
  14.000   1.4881   0.06985   0.06432  -0.0737   0.0096   1.0000
  14.250   1.4772   0.07467   0.06924  -0.0743   0.0095   1.0000
  14.500   1.4671   0.07942   0.07407  -0.0749   0.0094   1.0000
  14.750   1.4581   0.08393   0.07866  -0.0753   0.0093   1.0000
  15.000   1.4498   0.08796   0.08274  -0.0750   0.0091   1.0000
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