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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 1,000,000
Max Cl/Cd: 93.54 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe176-il-1000000-n5.txt
Download as CSV file: xf-goe176-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3471   0.14354   0.14182  -0.0199   1.0000   0.0050
 -12.250  -0.3422   0.14018   0.13847  -0.0208   1.0000   0.0048
 -12.000  -0.3375   0.13678   0.13508  -0.0216   1.0000   0.0047
 -11.750  -0.3330   0.13340   0.13171  -0.0225   1.0000   0.0046
 -11.500  -0.3282   0.13014   0.12847  -0.0233   1.0000   0.0048
  -9.500  -0.4102   0.02366   0.02096  -0.1248   0.9182   0.0043
  -9.250  -0.3782   0.02085   0.01766  -0.1290   0.8750   0.0044
  -9.000  -0.3530   0.01917   0.01566  -0.1303   0.8521   0.0045
  -8.500  -0.3015   0.01661   0.01259  -0.1317   0.8206   0.0048
  -8.250  -0.2752   0.01565   0.01139  -0.1320   0.8063   0.0049
  -8.000  -0.2486   0.01484   0.01037  -0.1322   0.7915   0.0051
  -7.750  -0.2219   0.01420   0.00955  -0.1323   0.7754   0.0053
  -7.500  -0.1950   0.01359   0.00875  -0.1324   0.7590   0.0055
  -7.250  -0.1679   0.01309   0.00807  -0.1324   0.7419   0.0056
  -7.000  -0.1407   0.01229   0.00705  -0.1325   0.7245   0.0059
  -6.750  -0.1133   0.01177   0.00637  -0.1326   0.7062   0.0061
  -6.500  -0.0857   0.01143   0.00589  -0.1326   0.6886   0.0064
  -6.250  -0.0581   0.01115   0.00547  -0.1325   0.6704   0.0067
  -6.000  -0.0304   0.01086   0.00504  -0.1325   0.6518   0.0070
  -5.750  -0.0025   0.01060   0.00465  -0.1324   0.6329   0.0074
  -5.500   0.0254   0.01037   0.00428  -0.1324   0.6142   0.0078
  -5.250   0.0533   0.01019   0.00395  -0.1323   0.5959   0.0081
  -5.000   0.0813   0.00991   0.00354  -0.1323   0.5778   0.0090
  -4.750   0.1091   0.00979   0.00332  -0.1323   0.5605   0.0099
  -4.500   0.1373   0.00967   0.00310  -0.1322   0.5468   0.0108
  -4.250   0.1657   0.00954   0.00287  -0.1322   0.5363   0.0115
  -4.000   0.1941   0.00935   0.00261  -0.1322   0.5269   0.0132
  -3.750   0.2225   0.00923   0.00245  -0.1322   0.5178   0.0151
  -3.500   0.2510   0.00913   0.00230  -0.1322   0.5097   0.0175
  -3.250   0.2793   0.00904   0.00216  -0.1322   0.5004   0.0216
  -3.000   0.3076   0.00900   0.00206  -0.1321   0.4894   0.0239
  -2.750   0.3359   0.00891   0.00193  -0.1321   0.4777   0.0295
  -2.500   0.3641   0.00889   0.00183  -0.1321   0.4631   0.0331
  -2.250   0.3917   0.00891   0.00174  -0.1319   0.4358   0.0415
  -2.000   0.4158   0.00917   0.00176  -0.1314   0.3427   0.0943
  -1.500   0.4710   0.00914   0.00178  -0.1314   0.3152   0.1670
  -1.250   0.4989   0.00918   0.00181  -0.1313   0.3088   0.1826
  -1.000   0.5269   0.00925   0.00183  -0.1312   0.3018   0.1902
  -0.750   0.5549   0.00930   0.00186  -0.1311   0.2964   0.1968
  -0.500   0.5829   0.00937   0.00188  -0.1310   0.2924   0.2012
  -0.250   0.6108   0.00942   0.00193  -0.1310   0.2885   0.2114
   0.000   0.6390   0.00946   0.00196  -0.1309   0.2862   0.2161
   0.250   0.6671   0.00950   0.00199  -0.1309   0.2833   0.2195
   0.500   0.6950   0.00956   0.00203  -0.1308   0.2792   0.2238
   0.750   0.7226   0.00965   0.00209  -0.1307   0.2740   0.2282
   1.000   0.7505   0.00971   0.00213  -0.1306   0.2700   0.2328
   1.250   0.7781   0.00979   0.00219  -0.1305   0.2621   0.2381
   1.500   0.8057   0.00988   0.00226  -0.1304   0.2567   0.2438
   1.750   0.8333   0.00995   0.00233  -0.1303   0.2508   0.2498
   2.000   0.8606   0.01007   0.00242  -0.1302   0.2427   0.2562
   2.250   0.8875   0.01022   0.00252  -0.1300   0.2296   0.2620
   2.500   0.9067   0.01123   0.00306  -0.1286   0.1324   0.2690
   2.750   0.9324   0.01151   0.00328  -0.1283   0.1160   0.2775
   3.000   0.9585   0.01173   0.00348  -0.1280   0.1067   0.2872
   3.250   0.9850   0.01190   0.00365  -0.1277   0.0999   0.2978
   3.500   1.0097   0.01226   0.00391  -0.1272   0.0742   0.3107
   3.750   1.0346   0.01259   0.00420  -0.1267   0.0583   0.3283
   4.000   1.0609   0.01275   0.00442  -0.1265   0.0535   0.3567
   4.250   1.0874   0.01285   0.00465  -0.1263   0.0520   0.4120
   4.500   1.1138   0.01295   0.00490  -0.1261   0.0511   0.4767
   4.750   1.1407   0.01270   0.00522  -0.1263   0.0503   0.7510
   5.250   1.1861   0.01269   0.00566  -0.1241   0.0490   1.0000
   5.500   1.2114   0.01295   0.00592  -0.1237   0.0479   1.0000
   5.750   1.2363   0.01326   0.00623  -0.1232   0.0457   1.0000
   6.000   1.2610   0.01357   0.00655  -0.1227   0.0440   1.0000
   6.250   1.2860   0.01383   0.00682  -0.1223   0.0431   1.0000
   6.500   1.3111   0.01405   0.00705  -0.1219   0.0422   1.0000
   6.750   1.3359   0.01431   0.00731  -0.1214   0.0404   1.0000
   7.000   1.3598   0.01464   0.00762  -0.1209   0.0372   1.0000
   7.250   1.3838   0.01495   0.00793  -0.1203   0.0337   1.0000
   7.500   1.4037   0.01562   0.00847  -0.1191   0.0132   1.0000
   7.750   1.4254   0.01611   0.00900  -0.1181   0.0100   1.0000
   8.000   1.4476   0.01652   0.00945  -0.1172   0.0086   1.0000
   8.250   1.4690   0.01698   0.00993  -0.1163   0.0075   1.0000
   8.500   1.4895   0.01749   0.01047  -0.1152   0.0065   1.0000
   8.750   1.5104   0.01794   0.01097  -0.1141   0.0060   1.0000
   9.000   1.5303   0.01843   0.01150  -0.1129   0.0054   1.0000
   9.250   1.5488   0.01899   0.01208  -0.1116   0.0049   1.0000
   9.500   1.5662   0.01960   0.01274  -0.1100   0.0045   1.0000
   9.750   1.5832   0.02017   0.01336  -0.1084   0.0042   1.0000
  10.000   1.5974   0.02077   0.01401  -0.1062   0.0040   1.0000
  10.250   1.6104   0.02143   0.01472  -0.1040   0.0038   1.0000
  10.500   1.6226   0.02214   0.01550  -0.1016   0.0036   1.0000
  10.750   1.6334   0.02295   0.01636  -0.0992   0.0034   1.0000
  11.000   1.6420   0.02393   0.01741  -0.0967   0.0032   1.0000
  11.250   1.6487   0.02508   0.01864  -0.0940   0.0030   1.0000
  11.500   1.6574   0.02615   0.01979  -0.0918   0.0029   1.0000
  11.750   1.6652   0.02735   0.02107  -0.0898   0.0028   1.0000
  12.000   1.6720   0.02872   0.02252  -0.0879   0.0027   1.0000
  12.250   1.6785   0.03021   0.02409  -0.0862   0.0026   1.0000
  12.500   1.6838   0.03190   0.02585  -0.0847   0.0025   1.0000
  12.750   1.6880   0.03379   0.02783  -0.0833   0.0024   1.0000
  13.000   1.6918   0.03581   0.02995  -0.0821   0.0023   1.0000
  13.250   1.6932   0.03817   0.03241  -0.0811   0.0023   1.0000
  13.500   1.6937   0.04075   0.03508  -0.0802   0.0022   1.0000
  13.750   1.6923   0.04364   0.03807  -0.0796   0.0021   1.0000
  14.000   1.6892   0.04684   0.04137  -0.0791   0.0021   1.0000
  14.250   1.6830   0.05055   0.04518  -0.0789   0.0020   1.0000
  14.500   1.6754   0.05457   0.04933  -0.0789   0.0020   1.0000
  14.750   1.6637   0.05927   0.05415  -0.0792   0.0019   1.0000
  15.000   1.6494   0.06450   0.05952  -0.0798   0.0019   1.0000
  15.250   1.6377   0.06952   0.06466  -0.0806   0.0019   1.0000
  15.500   1.6265   0.07452   0.06977  -0.0814   0.0019   1.0000
  15.750   1.6134   0.07994   0.07532  -0.0825   0.0019   1.0000
  16.000   1.6004   0.08546   0.08095  -0.0837   0.0018   1.0000
  16.250   1.5849   0.09145   0.08707  -0.0852   0.0018   1.0000
  16.500   1.5706   0.09742   0.09316  -0.0868   0.0018   1.0000
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