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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.1 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe176-il-1000000.txt
Download as CSV file: xf-goe176-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3289   0.09068   0.08918  -0.0301   1.0000   0.0124
  -8.500  -0.3242   0.08803   0.08655  -0.0309   0.9997   0.0125
  -8.250  -0.3604   0.02698   0.02461  -0.1058   0.9839   0.0093
  -8.000  -0.3318   0.02238   0.01957  -0.1109   0.9758   0.0095
  -7.750  -0.3047   0.02075   0.01776  -0.1122   0.9638   0.0098
  -7.500  -0.2713   0.01913   0.01594  -0.1145   0.9468   0.0101
  -7.250  -0.2178   0.01685   0.01332  -0.1214   0.9333   0.0106
  -7.000  -0.1690   0.01498   0.01104  -0.1267   0.9054   0.0111
  -6.750  -0.1399   0.01394   0.00966  -0.1273   0.8760   0.0114
  -6.500  -0.1130   0.01323   0.00871  -0.1272   0.8551   0.0117
  -6.250  -0.0860   0.01275   0.00805  -0.1270   0.8373   0.0120
  -6.000  -0.0597   0.01132   0.00637  -0.1270   0.8214   0.0128
  -5.750  -0.0324   0.01106   0.00603  -0.1269   0.8059   0.0135
  -5.500  -0.0050   0.01081   0.00567  -0.1267   0.7906   0.0142
  -5.250   0.0225   0.01046   0.00519  -0.1265   0.7740   0.0150
  -5.000   0.0501   0.01020   0.00481  -0.1263   0.7571   0.0156
  -4.750   0.0777   0.00958   0.00402  -0.1262   0.7400   0.0166
  -4.500   0.1053   0.00933   0.00367  -0.1261   0.7214   0.0177
  -4.250   0.1331   0.00917   0.00341  -0.1259   0.7022   0.0190
  -4.000   0.1608   0.00910   0.00323  -0.1257   0.6819   0.0203
  -3.500   0.2165   0.00867   0.00256  -0.1254   0.6411   0.0248
  -3.250   0.2443   0.00864   0.00242  -0.1252   0.6211   0.0266
  -3.000   0.2724   0.00841   0.00208  -0.1251   0.6041   0.0316
  -2.750   0.3004   0.00836   0.00194  -0.1250   0.5886   0.0349
  -2.500   0.3286   0.00820   0.00172  -0.1249   0.5746   0.0446
  -2.250   0.3566   0.00773   0.00152  -0.1251   0.5600   0.1411
  -2.000   0.3844   0.00771   0.00153  -0.1251   0.5441   0.1810
  -1.750   0.4123   0.00778   0.00154  -0.1249   0.5292   0.1954
  -1.500   0.4403   0.00783   0.00155  -0.1248   0.5153   0.2065
  -1.250   0.4681   0.00790   0.00156  -0.1246   0.4993   0.2147
  -1.000   0.4956   0.00802   0.00157  -0.1244   0.4729   0.2209
  -0.750   0.5208   0.00841   0.00162  -0.1239   0.3981   0.2253
  -0.500   0.5459   0.00880   0.00176  -0.1234   0.3444   0.2328
  -0.250   0.5732   0.00895   0.00183  -0.1232   0.3314   0.2376
   0.000   0.6010   0.00903   0.00187  -0.1231   0.3244   0.2432
   0.250   0.6287   0.00912   0.00193  -0.1229   0.3180   0.2480
   0.500   0.6567   0.00918   0.00198  -0.1229   0.3139   0.2527
   0.750   0.6846   0.00924   0.00203  -0.1228   0.3101   0.2582
   1.000   0.7122   0.00933   0.00211  -0.1226   0.3049   0.2654
   1.250   0.7399   0.00941   0.00217  -0.1225   0.2998   0.2725
   1.500   0.7679   0.00944   0.00223  -0.1225   0.2961   0.2807
   1.750   0.7957   0.00951   0.00230  -0.1224   0.2923   0.2894
   2.000   0.8232   0.00959   0.00239  -0.1223   0.2883   0.3007
   2.250   0.8509   0.00965   0.00248  -0.1222   0.2850   0.3157
   2.500   0.8789   0.00965   0.00255  -0.1222   0.2806   0.3382
   2.750   0.9065   0.00967   0.00265  -0.1222   0.2753   0.3825
   3.000   0.9341   0.00964   0.00281  -0.1222   0.2701   0.4745
   3.250   0.9556   0.00870   0.00297  -0.1209   0.2661   1.0000
   3.500   0.9829   0.00885   0.00305  -0.1207   0.2589   1.0000
   3.750   1.0103   0.00898   0.00316  -0.1206   0.2512   1.0000
   4.000   1.0371   0.00917   0.00327  -0.1204   0.2379   1.0000
   4.250   1.0559   0.01022   0.00380  -0.1190   0.1489   1.0000
   4.500   1.0790   0.01080   0.00420  -0.1182   0.1187   1.0000
   4.750   1.1042   0.01114   0.00446  -0.1178   0.1065   1.0000
   5.000   1.1294   0.01147   0.00471  -0.1173   0.0951   1.0000
   5.250   1.1520   0.01208   0.00513  -0.1165   0.0618   1.0000
   5.500   1.1770   0.01241   0.00543  -0.1160   0.0571   1.0000
   5.750   1.2026   0.01267   0.00570  -0.1156   0.0548   1.0000
   6.000   1.2280   0.01294   0.00597  -0.1152   0.0529   1.0000
   6.250   1.2533   0.01320   0.00626  -0.1147   0.0522   1.0000
   6.500   1.2784   0.01347   0.00657  -0.1143   0.0511   1.0000
   6.750   1.3030   0.01378   0.00691  -0.1138   0.0498   1.0000
   7.000   1.3271   0.01413   0.00728  -0.1132   0.0478   1.0000
   7.250   1.3506   0.01453   0.00769  -0.1125   0.0455   1.0000
   7.500   1.3735   0.01497   0.00818  -0.1117   0.0428   1.0000
   7.750   1.3993   0.01509   0.00829  -0.1115   0.0417   1.0000
   8.000   1.4236   0.01534   0.00851  -0.1110   0.0363   1.0000
   8.250   1.4421   0.01615   0.00913  -0.1095   0.0153   1.0000
   8.500   1.4625   0.01675   0.00978  -0.1083   0.0126   1.0000
   8.750   1.4837   0.01724   0.01033  -0.1073   0.0117   1.0000
   9.000   1.5039   0.01779   0.01094  -0.1061   0.0109   1.0000
   9.250   1.5225   0.01844   0.01164  -0.1047   0.0102   1.0000
   9.500   1.5378   0.01931   0.01260  -0.1027   0.0093   1.0000
   9.750   1.5536   0.02007   0.01344  -0.1009   0.0088   1.0000
  10.000   1.5701   0.02072   0.01415  -0.0992   0.0085   1.0000
  10.250   1.5833   0.02143   0.01492  -0.0969   0.0082   1.0000
  10.500   1.5939   0.02222   0.01578  -0.0943   0.0078   1.0000
  10.750   1.6034   0.02310   0.01673  -0.0916   0.0075   1.0000
  11.000   1.6113   0.02411   0.01781  -0.0889   0.0072   1.0000
  11.250   1.6169   0.02530   0.01909  -0.0861   0.0070   1.0000
  11.500   1.6177   0.02691   0.02080  -0.0830   0.0068   1.0000
  11.750   1.6112   0.02925   0.02328  -0.0798   0.0066   1.0000
  12.000   1.6013   0.03222   0.02639  -0.0771   0.0064   1.0000
  12.250   1.6083   0.03389   0.02815  -0.0760   0.0063   1.0000
  12.500   1.6141   0.03577   0.03011  -0.0750   0.0062   1.0000
  12.750   1.6164   0.03811   0.03255  -0.0741   0.0060   1.0000
  13.000   1.6175   0.04069   0.03522  -0.0735   0.0059   1.0000
  13.250   1.6158   0.04373   0.03836  -0.0730   0.0057   1.0000
  13.500   1.6128   0.04705   0.04178  -0.0728   0.0056   1.0000
  13.750   1.6073   0.05079   0.04563  -0.0728   0.0055   1.0000
  14.000   1.6008   0.05477   0.04973  -0.0730   0.0054   1.0000
  14.250   1.5931   0.05904   0.05411  -0.0734   0.0053   1.0000
  14.500   1.5837   0.06361   0.05879  -0.0740   0.0053   1.0000
  14.750   1.5731   0.06846   0.06375  -0.0748   0.0052   1.0000
  15.000   1.5629   0.07337   0.06877  -0.0757   0.0051   1.0000
  15.250   1.5511   0.07857   0.07407  -0.0768   0.0051   1.0000
  15.500   1.5400   0.08380   0.07941  -0.0780   0.0050   1.0000
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