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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 100,000
Max Cl/Cd: 57.5 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe176-il-100000-n5.txt
Download as CSV file: xf-goe176-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2916   0.09361   0.08928  -0.0333   1.0000   0.0328
  -7.500  -0.2969   0.09150   0.08727  -0.0312   1.0000   0.0324
  -7.250  -0.3058   0.08971   0.08560  -0.0290   1.0000   0.0320
  -7.000  -0.2870   0.08494   0.08084  -0.0346   0.9930   0.0314
  -6.750  -0.2636   0.07968   0.07558  -0.0417   0.9826   0.0305
  -6.500  -0.2402   0.07410   0.06999  -0.0494   0.9701   0.0293
  -6.250  -0.2147   0.06773   0.06360  -0.0586   0.9564   0.0281
  -6.000  -0.1843   0.05970   0.05550  -0.0703   0.9429   0.0270
  -5.750  -0.1255   0.03751   0.03230  -0.1018   0.9312   0.0247
  -5.500  -0.0833   0.03200   0.02613  -0.1094   0.9228   0.0253
  -5.250  -0.0428   0.02905   0.02279  -0.1140   0.9140   0.0276
  -5.000  -0.0030   0.02615   0.01928  -0.1177   0.9041   0.0297
  -4.750   0.0392   0.02361   0.01616  -0.1209   0.8959   0.0312
  -4.500   0.0766   0.02201   0.01412  -0.1228   0.8843   0.0332
  -4.250   0.1123   0.02028   0.01228  -0.1247   0.8725   0.0375
  -4.000   0.1482   0.01915   0.01090  -0.1262   0.8607   0.0413
  -3.750   0.1836   0.01815   0.00967  -0.1275   0.8488   0.0476
  -3.500   0.2176   0.01730   0.00861  -0.1286   0.8354   0.0559
  -3.250   0.2498   0.01644   0.00770  -0.1294   0.8209   0.0746
  -3.000   0.2806   0.01582   0.00742  -0.1301   0.8066   0.1592
  -2.750   0.3105   0.01601   0.00742  -0.1300   0.7928   0.2046
  -2.500   0.3398   0.01622   0.00741  -0.1300   0.7791   0.2312
  -2.250   0.3682   0.01637   0.00744  -0.1298   0.7646   0.2514
  -2.000   0.3965   0.01639   0.00731  -0.1296   0.7497   0.2669
  -1.750   0.4248   0.01631   0.00703  -0.1294   0.7355   0.2770
  -1.500   0.4525   0.01617   0.00680  -0.1291   0.7212   0.2843
  -1.000   0.5074   0.01600   0.00638  -0.1284   0.6921   0.3013
  -0.750   0.5347   0.01594   0.00620  -0.1281   0.6774   0.3106
  -0.500   0.5617   0.01588   0.00606  -0.1277   0.6638   0.3196
  -0.250   0.5887   0.01584   0.00594  -0.1273   0.6508   0.3284
   0.000   0.6154   0.01582   0.00583  -0.1268   0.6374   0.3382
   0.250   0.6421   0.01580   0.00577  -0.1264   0.6235   0.3475
   0.500   0.6687   0.01581   0.00574  -0.1259   0.6091   0.3592
   0.750   0.6952   0.01584   0.00573  -0.1255   0.5945   0.3732
   1.000   0.7215   0.01587   0.00574  -0.1250   0.5796   0.3901
   1.250   0.7476   0.01592   0.00579  -0.1245   0.5645   0.4136
   1.500   0.7736   0.01594   0.00587  -0.1240   0.5492   0.4519
   1.750   0.7989   0.01581   0.00596  -0.1235   0.5339   0.5336
   2.250   0.8444   0.01544   0.00608  -0.1208   0.5025   1.0000
   2.500   0.8699   0.01572   0.00624  -0.1202   0.4859   1.0000
   2.750   0.8953   0.01601   0.00641  -0.1197   0.4694   1.0000
   3.000   0.9206   0.01631   0.00661  -0.1192   0.4533   1.0000
   3.250   0.9457   0.01663   0.00684  -0.1186   0.4377   1.0000
   3.500   0.9704   0.01696   0.00706  -0.1180   0.4222   1.0000
   3.750   0.9946   0.01732   0.00730  -0.1173   0.4071   1.0000
   4.000   1.0183   0.01771   0.00757  -0.1166   0.3924   1.0000
   4.250   1.0415   0.01814   0.00786  -0.1158   0.3786   1.0000
   4.500   1.0647   0.01861   0.00820  -0.1150   0.3662   1.0000
   4.750   1.0883   0.01905   0.00862  -0.1144   0.3556   1.0000
   5.000   1.1120   0.01951   0.00902  -0.1137   0.3482   1.0000
   5.250   1.1364   0.01992   0.00947  -0.1132   0.3422   1.0000
   5.500   1.1604   0.02038   0.00995  -0.1126   0.3371   1.0000
   5.750   1.1846   0.02083   0.01043  -0.1120   0.3323   1.0000
   6.000   1.2086   0.02125   0.01094  -0.1114   0.3266   1.0000
   6.250   1.2318   0.02176   0.01145  -0.1108   0.3210   1.0000
   6.500   1.2554   0.02221   0.01202  -0.1101   0.3155   1.0000
   6.750   1.2785   0.02266   0.01258  -0.1094   0.3097   1.0000
   7.000   1.3012   0.02319   0.01314  -0.1087   0.3044   1.0000
   7.250   1.3239   0.02362   0.01376  -0.1079   0.2986   1.0000
   7.500   1.3460   0.02410   0.01440  -0.1071   0.2927   1.0000
   7.750   1.3680   0.02463   0.01501  -0.1062   0.2882   1.0000
   8.000   1.3897   0.02508   0.01571  -0.1053   0.2821   1.0000
   8.250   1.4083   0.02556   0.01631  -0.1040   0.2715   1.0000
   8.500   1.4251   0.02597   0.01691  -0.1024   0.2524   1.0000
   8.750   1.4411   0.02647   0.01751  -0.1008   0.2224   1.0000
   9.250   1.4522   0.02896   0.01949  -0.0951   0.1495   1.0000
   9.500   1.4572   0.03036   0.02085  -0.0922   0.1325   1.0000
   9.750   1.4632   0.03176   0.02228  -0.0897   0.1179   1.0000
  10.000   1.4695   0.03318   0.02375  -0.0872   0.0966   1.0000
  10.500   1.4575   0.03809   0.02845  -0.0813   0.0585   1.0000
  10.750   1.4507   0.04086   0.03132  -0.0790   0.0535   1.0000
  11.000   1.4513   0.04315   0.03382  -0.0775   0.0483   1.0000
  11.500   1.4512   0.04825   0.03936  -0.0753   0.0353   1.0000
  11.750   1.4444   0.05175   0.04295  -0.0746   0.0239   1.0000
  12.000   1.4327   0.05602   0.04725  -0.0744   0.0221   1.0000
  12.250   1.4216   0.06051   0.05184  -0.0745   0.0209   1.0000
  12.500   1.4102   0.06527   0.05675  -0.0751   0.0201   1.0000
  13.000   1.3839   0.07588   0.06774  -0.0771   0.0193   1.0000
  13.250   1.3698   0.08161   0.07367  -0.0785   0.0190   1.0000
  13.500   1.3553   0.08761   0.07985  -0.0802   0.0188   1.0000
  13.750   1.3414   0.09368   0.08610  -0.0820   0.0186   1.0000
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