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GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
Reynolds number: 50,000
Max Cl/Cd: 39.96 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe174-il-50000-n5.txt
Download as CSV file: xf-goe174-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 174 (ALBATROS 5020) AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2826   0.10174   0.09549  -0.0264   1.0000   0.0994
  -7.250  -0.2918   0.10120   0.09512  -0.0280   1.0000   0.1017
  -7.000  -0.2983   0.10078   0.09485  -0.0317   1.0000   0.1026
  -6.750  -0.2938   0.09624   0.09041  -0.0286   1.0000   0.1041
  -6.500  -0.2894   0.09280   0.08702  -0.0255   1.0000   0.1068
  -6.250  -0.2900   0.09063   0.08494  -0.0242   1.0000   0.1099
  -6.000  -0.2929   0.08895   0.08336  -0.0243   1.0000   0.1142
  -5.750  -0.2937   0.08884   0.08327  -0.0318   1.0000   0.1180
  -5.500  -0.2928   0.08461   0.07918  -0.0263   0.9992   0.1207
  -5.000  -0.2298   0.07599   0.07046  -0.0385   0.9798   0.1386
  -4.500  -0.1501   0.06801   0.06217  -0.0573   0.9563   0.1628
  -4.250  -0.1188   0.06419   0.05829  -0.0615   0.9454   0.1777
  -4.000  -0.0434   0.05424   0.04756  -0.0782   0.9372   0.0861
  -3.750  -0.0083   0.05009   0.04330  -0.0821   0.9271   0.0801
  -3.500   0.0365   0.04590   0.03876  -0.0883   0.9171   0.0788
  -3.250   0.0885   0.04134   0.03368  -0.0954   0.9099   0.0761
  -3.000   0.1382   0.03726   0.02863  -0.1007   0.8998   0.0720
  -2.750   0.1823   0.03430   0.02523  -0.1046   0.8917   0.0726
  -2.500   0.2193   0.03233   0.02310  -0.1070   0.8805   0.0757
  -2.250   0.2580   0.03031   0.02058  -0.1091   0.8684   0.0761
  -2.000   0.2966   0.02854   0.01834  -0.1107   0.8561   0.0763
  -1.750   0.3338   0.02710   0.01650  -0.1119   0.8430   0.0771
  -1.500   0.3685   0.02596   0.01503  -0.1125   0.8289   0.0786
  -1.250   0.4009   0.02513   0.01387  -0.1126   0.8141   0.0830
  -1.000   0.4330   0.02445   0.01284  -0.1125   0.7993   0.0868
  -0.750   0.4633   0.02376   0.01200  -0.1123   0.7847   0.0897
  -0.500   0.4923   0.02326   0.01135  -0.1120   0.7699   0.0938
  -0.250   0.5204   0.02289   0.01082  -0.1115   0.7550   0.0997
   0.000   0.5482   0.02253   0.01042  -0.1110   0.7402   0.1094
   0.250   0.5759   0.02214   0.01021  -0.1107   0.7256   0.1433
   0.750   0.6269   0.02014   0.00981  -0.1089   0.6970   1.0000
   1.000   0.6542   0.02032   0.00965  -0.1083   0.6826   1.0000
   1.250   0.6814   0.02053   0.00958  -0.1077   0.6684   1.0000
   1.500   0.7084   0.02077   0.00956  -0.1072   0.6543   1.0000
   1.750   0.7352   0.02104   0.00961  -0.1066   0.6401   1.0000
   2.000   0.7618   0.02134   0.00971  -0.1061   0.6261   1.0000
   2.250   0.7883   0.02167   0.00987  -0.1056   0.6123   1.0000
   2.500   0.8146   0.02203   0.01009  -0.1051   0.5986   1.0000
   2.750   0.8407   0.02241   0.01033  -0.1046   0.5851   1.0000
   3.000   0.8668   0.02279   0.01058  -0.1041   0.5722   1.0000
   3.250   0.8915   0.02325   0.01100  -0.1035   0.5584   1.0000
   3.500   0.9160   0.02371   0.01143  -0.1029   0.5452   1.0000
   3.750   0.9406   0.02419   0.01188  -0.1023   0.5327   1.0000
   4.000   0.9654   0.02465   0.01233  -0.1018   0.5212   1.0000
   4.250   0.9911   0.02507   0.01269  -0.1013   0.5111   1.0000
   4.500   1.0146   0.02564   0.01330  -0.1006   0.4995   1.0000
   4.750   1.0387   0.02620   0.01391  -0.1001   0.4892   1.0000
   5.000   1.0645   0.02664   0.01431  -0.0996   0.4809   1.0000
   5.250   1.0872   0.02733   0.01511  -0.0990   0.4709   1.0000
   5.500   1.1117   0.02791   0.01572  -0.0984   0.4627   1.0000
   5.750   1.1352   0.02855   0.01648  -0.0979   0.4541   1.0000
   6.000   1.1587   0.02925   0.01726  -0.0973   0.4464   1.0000
   6.250   1.1823   0.02993   0.01804  -0.0967   0.4388   1.0000
   6.500   1.2050   0.03071   0.01897  -0.0961   0.4314   1.0000
   6.750   1.2279   0.03146   0.01985  -0.0954   0.4240   1.0000
   7.000   1.2500   0.03227   0.02080  -0.0947   0.4167   1.0000
   7.250   1.2718   0.03304   0.02172  -0.0939   0.4088   1.0000
   7.500   1.2920   0.03387   0.02275  -0.0929   0.4002   1.0000
   7.750   1.3150   0.03441   0.02338  -0.0921   0.3917   1.0000
   8.000   1.3315   0.03542   0.02463  -0.0907   0.3821   1.0000
   8.250   1.3550   0.03595   0.02524  -0.0899   0.3742   1.0000
   8.500   1.3699   0.03708   0.02670  -0.0884   0.3651   1.0000
   8.750   1.3898   0.03788   0.02767  -0.0873   0.3572   1.0000
   9.000   1.4063   0.03883   0.02886  -0.0859   0.3483   1.0000
   9.250   1.4207   0.03990   0.03018  -0.0843   0.3395   1.0000
   9.500   1.4411   0.04048   0.03091  -0.0831   0.3309   1.0000
   9.750   1.4483   0.04196   0.03278  -0.0809   0.3217   1.0000
  10.000   1.4617   0.04265   0.03366  -0.0789   0.3112   1.0000
  10.250   1.4694   0.04319   0.03436  -0.0762   0.2977   1.0000
  10.500   1.4688   0.04404   0.03537  -0.0728   0.2831   1.0000
  10.750   1.4618   0.04527   0.03677  -0.0689   0.2697   1.0000
  11.000   1.4488   0.04751   0.03926  -0.0656   0.2576   1.0000
  11.250   1.4366   0.05009   0.04204  -0.0631   0.2451   1.0000
  11.500   1.4238   0.05319   0.04534  -0.0616   0.2317   1.0000
  11.750   1.4102   0.05693   0.04929  -0.0609   0.2178   1.0000
  12.000   1.3955   0.06134   0.05388  -0.0610   0.2038   1.0000
  12.250   1.3792   0.06641   0.05912  -0.0617   0.1893   1.0000
  12.500   1.3627   0.07179   0.06461  -0.0628   0.1729   1.0000
  12.750   1.3477   0.07696   0.06976  -0.0638   0.1530   1.0000
  13.000   1.3320   0.08223   0.07488  -0.0648   0.1330   1.0000
  13.250   1.3142   0.08810   0.08063  -0.0662   0.1170   1.0000
  13.500   1.2964   0.09434   0.08686  -0.0679   0.1025   1.0000
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