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GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 529 AIRFOIL (goe529-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.3 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe529-il-1000000-n5.txt
Download as CSV file: xf-goe529-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 529 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3126   0.12685   0.12517  -0.0323   1.0000   0.0050
 -12.000  -0.3085   0.12363   0.12196  -0.0332   1.0000   0.0051
 -10.000  -0.4883   0.01896   0.01534  -0.1175   0.8323   0.0093
  -9.750  -0.4682   0.01732   0.01342  -0.1171   0.8189   0.0096
  -9.500  -0.4463   0.01610   0.01200  -0.1166   0.8063   0.0104
  -9.250  -0.4230   0.01524   0.01095  -0.1162   0.7932   0.0111
  -9.000  -0.3991   0.01454   0.01009  -0.1158   0.7792   0.0118
  -8.750  -0.3747   0.01394   0.00930  -0.1153   0.7640   0.0125
  -8.500  -0.3491   0.01365   0.00894  -0.1149   0.7474   0.0136
  -8.250  -0.3230   0.01348   0.00869  -0.1145   0.7303   0.0146
  -8.000  -0.2973   0.01323   0.00830  -0.1141   0.7124   0.0156
  -7.750  -0.2719   0.01288   0.00779  -0.1137   0.6951   0.0162
  -7.250  -0.2188   0.01274   0.00750  -0.1131   0.6661   0.0176
  -7.000  -0.1918   0.01274   0.00744  -0.1128   0.6546   0.0182
  -6.750  -0.1648   0.01270   0.00733  -0.1126   0.6448   0.0190
  -6.500  -0.1379   0.01261   0.00716  -0.1123   0.6357   0.0198
  -6.250  -0.1110   0.01239   0.00684  -0.1121   0.6288   0.0204
  -6.000  -0.0840   0.01222   0.00658  -0.1119   0.6227   0.0208
  -5.500  -0.0305   0.01154   0.00570  -0.1114   0.6144   0.0218
  -5.250  -0.0036   0.01122   0.00532  -0.1112   0.6104   0.0225
  -5.000   0.0237   0.01107   0.00513  -0.1111   0.6066   0.0231
  -4.750   0.0509   0.01091   0.00491  -0.1109   0.6030   0.0237
  -4.500   0.0784   0.01072   0.00468  -0.1108   0.5999   0.0243
  -4.250   0.1058   0.01045   0.00435  -0.1106   0.5963   0.0248
  -4.000   0.1331   0.01021   0.00403  -0.1104   0.5929   0.0254
  -3.750   0.1604   0.01003   0.00380  -0.1102   0.5896   0.0260
  -3.500   0.1877   0.00982   0.00352  -0.1100   0.5864   0.0264
  -3.250   0.2152   0.00958   0.00323  -0.1099   0.5832   0.0267
  -3.000   0.2427   0.00940   0.00300  -0.1097   0.5795   0.0270
  -2.750   0.2700   0.00922   0.00278  -0.1095   0.5759   0.0272
  -2.500   0.2973   0.00908   0.00258  -0.1093   0.5725   0.0274
  -2.250   0.3250   0.00892   0.00240  -0.1092   0.5692   0.0276
  -2.000   0.3526   0.00879   0.00224  -0.1091   0.5651   0.0278
  -1.750   0.3799   0.00864   0.00205  -0.1089   0.5606   0.0280
  -1.500   0.4070   0.00847   0.00182  -0.1086   0.5567   0.0292
  -1.250   0.4347   0.00834   0.00168  -0.1085   0.5527   0.0304
  -1.000   0.4622   0.00826   0.00157  -0.1084   0.5465   0.0313
  -0.750   0.4895   0.00821   0.00149  -0.1082   0.5392   0.0325
  -0.500   0.5169   0.00817   0.00143  -0.1080   0.5305   0.0336
  -0.250   0.5441   0.00815   0.00137  -0.1078   0.5203   0.0346
   0.000   0.5711   0.00816   0.00133  -0.1076   0.5083   0.0359
   0.500   0.6240   0.00825   0.00131  -0.1070   0.4737   0.0470
   0.750   0.6501   0.00829   0.00135  -0.1067   0.4581   0.0701
   1.000   0.6764   0.00836   0.00140  -0.1064   0.4446   0.0816
   1.250   0.7027   0.00844   0.00145  -0.1061   0.4319   0.0939
   1.500   0.7289   0.00849   0.00152  -0.1058   0.4208   0.1203
   1.750   0.7555   0.00854   0.00159  -0.1056   0.4125   0.1433
   2.000   0.7820   0.00858   0.00167  -0.1054   0.4060   0.1671
   2.250   0.8086   0.00860   0.00174  -0.1052   0.3992   0.2030
   2.500   0.8344   0.00855   0.00186  -0.1049   0.3928   0.2908
   3.000   0.8989   0.00741   0.00221  -0.1074   0.3793   1.0000
   3.250   0.9250   0.00752   0.00229  -0.1071   0.3736   1.0000
   3.500   0.9508   0.00765   0.00239  -0.1067   0.3669   1.0000
   3.750   0.9765   0.00779   0.00249  -0.1063   0.3606   1.0000
   4.000   1.0023   0.00792   0.00260  -0.1060   0.3533   1.0000
   4.250   1.0277   0.00808   0.00272  -0.1056   0.3459   1.0000
   4.500   1.0528   0.00827   0.00286  -0.1051   0.3353   1.0000
   4.750   1.0775   0.00848   0.00301  -0.1046   0.3222   1.0000
   5.000   1.1019   0.00871   0.00318  -0.1040   0.3085   1.0000
   5.250   1.1264   0.00893   0.00335  -0.1035   0.2967   1.0000
   5.500   1.1487   0.00931   0.00361  -0.1026   0.2739   1.0000
   5.750   1.1699   0.00975   0.00391  -0.1016   0.2476   1.0000
   6.000   1.1918   0.01015   0.00420  -0.1007   0.2276   1.0000
   6.250   1.2118   0.01066   0.00455  -0.0995   0.2021   1.0000
   6.500   1.2309   0.01121   0.00496  -0.0981   0.1719   1.0000
   6.750   1.2432   0.01222   0.00565  -0.0957   0.1188   1.0000
   7.000   1.2640   0.01261   0.00600  -0.0947   0.1101   1.0000
   7.250   1.2857   0.01293   0.00631  -0.0937   0.1029   1.0000
   7.500   1.3052   0.01337   0.00671  -0.0925   0.0923   1.0000
   7.750   1.3172   0.01423   0.00736  -0.0900   0.0561   1.0000
   8.000   1.3329   0.01483   0.00790  -0.0881   0.0413   1.0000
   8.250   1.3396   0.01575   0.00868  -0.0847   0.0166   1.0000
   8.500   1.3539   0.01620   0.00916  -0.0825   0.0132   1.0000
   8.750   1.3690   0.01664   0.00963  -0.0805   0.0119   1.0000
   9.000   1.3828   0.01715   0.01017  -0.0784   0.0107   1.0000
   9.250   1.3958   0.01772   0.01077  -0.0762   0.0096   1.0000
   9.500   1.4099   0.01824   0.01134  -0.0743   0.0091   1.0000
   9.750   1.4233   0.01883   0.01196  -0.0724   0.0084   1.0000
  10.000   1.4356   0.01949   0.01266  -0.0704   0.0078   1.0000
  10.250   1.4467   0.02026   0.01347  -0.0685   0.0073   1.0000
  10.500   1.4558   0.02119   0.01445  -0.0663   0.0067   1.0000
  10.750   1.4670   0.02203   0.01534  -0.0646   0.0065   1.0000
  11.000   1.4776   0.02296   0.01632  -0.0629   0.0062   1.0000
  11.250   1.4869   0.02402   0.01744  -0.0613   0.0060   1.0000
  11.500   1.4959   0.02517   0.01864  -0.0597   0.0058   1.0000
  11.750   1.5039   0.02644   0.01996  -0.0582   0.0055   1.0000
  12.000   1.5108   0.02787   0.02146  -0.0568   0.0052   1.0000
  12.250   1.5161   0.02949   0.02313  -0.0554   0.0050   1.0000
  12.500   1.5200   0.03132   0.02504  -0.0542   0.0047   1.0000
  12.750   1.5255   0.03308   0.02687  -0.0531   0.0047   1.0000
  13.000   1.5316   0.03485   0.02871  -0.0523   0.0045   1.0000
  13.250   1.5353   0.03692   0.03085  -0.0515   0.0044   1.0000
  13.500   1.5385   0.03911   0.03312  -0.0508   0.0042   1.0000
  13.750   1.5417   0.04135   0.03544  -0.0502   0.0041   1.0000
  14.000   1.5421   0.04396   0.03813  -0.0497   0.0040   1.0000
  14.250   1.5430   0.04657   0.04083  -0.0493   0.0039   1.0000
  14.500   1.5447   0.04916   0.04349  -0.0490   0.0038   1.0000
  14.750   1.5436   0.05211   0.04653  -0.0488   0.0037   1.0000
  15.000   1.5422   0.05519   0.04968  -0.0487   0.0036   1.0000
  15.250   1.5396   0.05848   0.05307  -0.0488   0.0036   1.0000
  15.500   1.5379   0.06175   0.05640  -0.0490   0.0035   1.0000
  15.750   1.5344   0.06532   0.06006  -0.0493   0.0034   1.0000
  16.000   1.5253   0.06979   0.06464  -0.0499   0.0033   1.0000
  16.250   1.5199   0.07387   0.06881  -0.0506   0.0032   1.0000
  16.500   1.5120   0.07842   0.07346  -0.0515   0.0032   1.0000
  16.750   1.5060   0.08281   0.07795  -0.0525   0.0031   1.0000
  17.000   1.5025   0.08691   0.08214  -0.0535   0.0031   1.0000
  17.250   1.4984   0.09115   0.08648  -0.0547   0.0031   1.0000
  17.500   1.4891   0.09629   0.09173  -0.0563   0.0031   1.0000
  17.750   1.4847   0.10071   0.09625  -0.0577   0.0030   1.0000
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