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GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il)
Reynolds number: 50,000
Max Cl/Cd: 42.36 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe155-il-50000-n5.txt
Download as CSV file: xf-goe155-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 155 (SSW D.1) 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  -0.2999   0.10021   0.09397  -0.0277   1.0000   0.0825
  -7.250  -0.3036   0.09870   0.09257  -0.0278   1.0000   0.0850
  -7.000  -0.3118   0.09809   0.09209  -0.0283   1.0000   0.0868
  -6.750  -0.3201   0.09788   0.09198  -0.0299   1.0000   0.0877
  -6.500  -0.3239   0.09637   0.09056  -0.0307   1.0000   0.0883
  -6.250  -0.3239   0.09200   0.08625  -0.0255   1.0000   0.0901
  -6.000  -0.3252   0.08965   0.08395  -0.0236   1.0000   0.0923
  -5.750  -0.3225   0.08736   0.08170  -0.0239   0.9991   0.0952
  -5.500  -0.2814   0.08406   0.07824  -0.0390   0.9893   0.1015
  -5.250  -0.2686   0.07925   0.07347  -0.0364   0.9849   0.1072
  -4.750  -0.2109   0.07174   0.06578  -0.0481   0.9707   0.1237
  -4.500  -0.1744   0.06775   0.06162  -0.0559   0.9646   0.1316
  -4.250  -0.1366   0.06478   0.05843  -0.0638   0.9568   0.1437
  -3.500  -0.0466   0.05456   0.04789  -0.0744   0.9388   0.1889
  -3.250   0.0285   0.04779   0.04011  -0.0869   0.9339   0.0888
  -3.000   0.0620   0.04497   0.03701  -0.0896   0.9270   0.0867
  -2.750   0.1030   0.04187   0.03363  -0.0937   0.9223   0.0831
  -2.500   0.1423   0.03893   0.03007  -0.0967   0.9146   0.0769
  -2.250   0.1841   0.03652   0.02720  -0.0998   0.9084   0.0746
  -2.000   0.2179   0.03462   0.02491  -0.1013   0.8996   0.0739
  -1.750   0.2586   0.03278   0.02256  -0.1038   0.8928   0.0765
  -1.500   0.2886   0.03151   0.02107  -0.1044   0.8831   0.0783
  -1.250   0.3282   0.02998   0.01910  -0.1062   0.8769   0.0780
  -1.000   0.3563   0.02905   0.01786  -0.1061   0.8670   0.0782
  -0.750   0.3894   0.02808   0.01663  -0.1067   0.8596   0.0791
  -0.500   0.4209   0.02738   0.01565  -0.1069   0.8508   0.0805
  -0.250   0.4521   0.02677   0.01481  -0.1071   0.8422   0.0826
   0.000   0.4847   0.02618   0.01401  -0.1074   0.8343   0.0867
   0.250   0.5117   0.02583   0.01368  -0.1071   0.8241   0.0941
   0.500   0.5426   0.02540   0.01318  -0.1072   0.8158   0.1031
   0.750   0.5707   0.02511   0.01288  -0.1069   0.8056   0.1145
   1.000   0.5979   0.02482   0.01273  -0.1065   0.7948   0.1454
   1.250   0.6279   0.02271   0.01234  -0.1065   0.7862   1.0000
   1.500   0.6546   0.02284   0.01218  -0.1057   0.7749   1.0000
   1.750   0.6800   0.02301   0.01217  -0.1048   0.7624   1.0000
   2.000   0.7058   0.02312   0.01212  -0.1039   0.7497   1.0000
   2.250   0.7318   0.02311   0.01200  -0.1028   0.7356   1.0000
   2.500   0.7574   0.02307   0.01184  -0.1016   0.7203   1.0000
   2.750   0.7827   0.02303   0.01171  -0.1003   0.7041   1.0000
   3.000   0.8077   0.02302   0.01165  -0.0991   0.6878   1.0000
   3.250   0.8325   0.02305   0.01164  -0.0979   0.6714   1.0000
   3.500   0.8573   0.02313   0.01168  -0.0968   0.6551   1.0000
   3.750   0.8821   0.02322   0.01179  -0.0958   0.6388   1.0000
   4.000   0.9063   0.02338   0.01195  -0.0947   0.6217   1.0000
   4.250   0.9299   0.02362   0.01222  -0.0937   0.6034   1.0000
   4.500   0.9540   0.02382   0.01245  -0.0927   0.5854   1.0000
   4.750   0.9785   0.02402   0.01269  -0.0917   0.5678   1.0000
   5.000   1.0031   0.02424   0.01292  -0.0907   0.5505   1.0000
   5.250   1.0273   0.02454   0.01322  -0.0898   0.5329   1.0000
   5.500   1.0508   0.02496   0.01372  -0.0888   0.5148   1.0000
   5.750   1.0745   0.02541   0.01421  -0.0879   0.4978   1.0000
   6.000   1.0983   0.02593   0.01479  -0.0871   0.4821   1.0000
   6.250   1.1221   0.02652   0.01546  -0.0863   0.4673   1.0000
   6.500   1.1457   0.02717   0.01625  -0.0855   0.4532   1.0000
   6.750   1.1695   0.02786   0.01706  -0.0848   0.4403   1.0000
   7.000   1.1933   0.02856   0.01789  -0.0841   0.4279   1.0000
   7.250   1.2135   0.02928   0.01877  -0.0829   0.4108   1.0000
   7.500   1.2312   0.02996   0.01960  -0.0813   0.3909   1.0000
   7.750   1.2480   0.03059   0.02041  -0.0796   0.3710   1.0000
   8.000   1.2598   0.03131   0.02130  -0.0774   0.3462   1.0000
   8.250   1.2655   0.03211   0.02212  -0.0745   0.3123   1.0000
   8.500   1.2690   0.03323   0.02323  -0.0715   0.2738   1.0000
   8.750   1.2680   0.03488   0.02470  -0.0684   0.2240   1.0000
   9.250   1.2446   0.04119   0.02983  -0.0620   0.0847   1.0000
   9.500   1.2369   0.04466   0.03322  -0.0599   0.0730   1.0000
   9.750   1.2337   0.04773   0.03645  -0.0583   0.0650   1.0000
  10.000   1.2271   0.05125   0.04014  -0.0570   0.0608   1.0000
  10.250   1.2219   0.05474   0.04379  -0.0560   0.0579   1.0000
  10.500   1.2178   0.05822   0.04748  -0.0552   0.0549   1.0000
  10.750   1.2125   0.06192   0.05134  -0.0548   0.0521   1.0000
  11.000   1.2061   0.06584   0.05537  -0.0545   0.0497   1.0000
  11.250   1.1993   0.06983   0.05940  -0.0542   0.0477   1.0000
  11.500   1.1996   0.07299   0.06279  -0.0536   0.0457   1.0000
  11.750   1.2020   0.07582   0.06581  -0.0525   0.0441   1.0000
  12.000   1.2071   0.07832   0.06846  -0.0511   0.0423   1.0000
  12.250   1.2132   0.08074   0.07101  -0.0498   0.0401   1.0000
  12.500   1.2307   0.08186   0.07205  -0.0467   0.0371   1.0000
  12.750   1.2399   0.08452   0.07511  -0.0455   0.0358   1.0000
  13.000   1.2499   0.08739   0.07832  -0.0442   0.0350   1.0000
  13.250   1.2529   0.09115   0.08240  -0.0438   0.0344   1.0000
  13.500   1.2496   0.09563   0.08718  -0.0442   0.0340   1.0000
  13.750   1.2422   0.10065   0.09249  -0.0453   0.0337   1.0000
  14.000   1.2318   0.10619   0.09829  -0.0472   0.0335   1.0000
  14.250   1.2196   0.11223   0.10459  -0.0497   0.0334   1.0000
  14.500   1.2062   0.11882   0.11142  -0.0530   0.0334   1.0000
  14.750   1.1917   0.12605   0.11886  -0.0570   0.0335   1.0000
  15.000   1.1767   0.13390   0.12689  -0.0617   0.0337   1.0000
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