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GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il)
Reynolds number: 200,000
Max Cl/Cd: 72.43 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe255-il-200000.txt
Download as CSV file: xf-goe255-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 255 (MVA CA.6) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.6152   0.06878   0.06454  -0.0916   1.0000   0.0313
 -13.500  -0.6583   0.06318   0.05873  -0.0934   1.0000   0.0309
 -13.250  -0.6916   0.06032   0.05579  -0.0924   1.0000   0.0307
 -13.000  -0.7052   0.05566   0.05091  -0.0972   0.9957   0.0306
 -12.750  -0.7036   0.05005   0.04498  -0.1046   0.9883   0.0307
 -12.500  -0.6924   0.04546   0.04013  -0.1100   0.9826   0.0310
 -12.250  -0.6758   0.04221   0.03671  -0.1133   0.9742   0.0314
 -12.000  -0.6503   0.03936   0.03371  -0.1172   0.9699   0.0320
 -11.750  -0.6288   0.03699   0.03116  -0.1194   0.9606   0.0327
 -11.500  -0.6004   0.03475   0.02872  -0.1224   0.9560   0.0338
 -11.250  -0.5823   0.03303   0.02680  -0.1228   0.9449   0.0349
 -11.000  -0.5630   0.03151   0.02502  -0.1231   0.9354   0.0360
 -10.750  -0.5412   0.02955   0.02306  -0.1234   0.9279   0.0373
 -10.500  -0.5234   0.02833   0.02182  -0.1227   0.9176   0.0386
 -10.250  -0.5017   0.02705   0.02044  -0.1225   0.9108   0.0401
 -10.000  -0.4850   0.02599   0.01926  -0.1213   0.9002   0.0417
  -9.750  -0.4661   0.02467   0.01787  -0.1205   0.8930   0.0437
  -9.500  -0.4481   0.02369   0.01689  -0.1196   0.8840   0.0464
  -9.250  -0.4265   0.02282   0.01587  -0.1190   0.8770   0.0500
  -9.000  -0.4086   0.02169   0.01477  -0.1181   0.8687   0.0543
  -8.750  -0.3880   0.02067   0.01368  -0.1174   0.8617   0.0610
  -8.500  -0.3684   0.01966   0.01268  -0.1166   0.8536   0.0728
  -8.250  -0.3474   0.01857   0.01160  -0.1161   0.8471   0.0946
  -8.000  -0.3253   0.01788   0.01096  -0.1156   0.8390   0.1166
  -7.750  -0.2995   0.01737   0.01041  -0.1155   0.8331   0.1368
  -7.500  -0.2750   0.01705   0.01010  -0.1153   0.8252   0.1558
  -7.250  -0.2483   0.01675   0.00972  -0.1152   0.8187   0.1753
  -7.000  -0.2224   0.01652   0.00940  -0.1151   0.8116   0.1942
  -6.750  -0.1970   0.01619   0.00909  -0.1149   0.8045   0.2139
  -6.500  -0.1707   0.01592   0.00882  -0.1148   0.7984   0.2359
  -6.250  -0.1454   0.01570   0.00861  -0.1146   0.7906   0.2567
  -6.000  -0.1181   0.01549   0.00838  -0.1145   0.7844   0.2755
  -5.750  -0.0921   0.01540   0.00834  -0.1143   0.7768   0.2937
  -5.500  -0.0645   0.01539   0.00829  -0.1142   0.7698   0.3128
  -5.250  -0.0367   0.01546   0.00830  -0.1141   0.7630   0.3317
  -5.000  -0.0094   0.01556   0.00833  -0.1139   0.7552   0.3498
  -4.750   0.0197   0.01569   0.00833  -0.1140   0.7495   0.3665
  -4.500   0.0460   0.01579   0.00842  -0.1137   0.7413   0.3805
  -4.250   0.0744   0.01588   0.00841  -0.1137   0.7351   0.3947
  -4.000   0.1018   0.01599   0.00846  -0.1136   0.7284   0.4087
  -3.750   0.1293   0.01607   0.00845  -0.1135   0.7215   0.4223
  -3.500   0.1583   0.01608   0.00840  -0.1136   0.7164   0.4334
  -3.250   0.1848   0.01607   0.00838  -0.1135   0.7092   0.4424
  -3.000   0.2132   0.01605   0.00827  -0.1135   0.7032   0.4516
  -2.750   0.2421   0.01600   0.00814  -0.1137   0.6980   0.4599
  -2.500   0.2687   0.01599   0.00813  -0.1136   0.6908   0.4682
  -2.250   0.2977   0.01591   0.00795  -0.1138   0.6855   0.4754
  -2.000   0.3260   0.01589   0.00790  -0.1139   0.6805   0.4824
  -1.750   0.3533   0.01592   0.00786  -0.1140   0.6744   0.4899
  -1.500   0.3820   0.01582   0.00777  -0.1141   0.6697   0.4962
  -1.250   0.4118   0.01582   0.00767  -0.1145   0.6660   0.5032
  -1.000   0.4381   0.01585   0.00773  -0.1145   0.6604   0.5094
  -0.750   0.4661   0.01583   0.00772  -0.1146   0.6559   0.5159
  -0.500   0.4957   0.01584   0.00764  -0.1150   0.6523   0.5233
  -0.250   0.5242   0.01584   0.00767  -0.1152   0.6488   0.5312
   0.000   0.5506   0.01595   0.00780  -0.1152   0.6441   0.5410
   0.250   0.5782   0.01594   0.00786  -0.1153   0.6402   0.5494
   0.500   0.6076   0.01596   0.00782  -0.1157   0.6368   0.5581
   0.750   0.6376   0.01593   0.00778  -0.1162   0.6339   0.5648
   1.000   0.6629   0.01604   0.00798  -0.1160   0.6295   0.5732
   1.250   0.6899   0.01606   0.00809  -0.1160   0.6255   0.5823
   1.750   0.7480   0.01605   0.00813  -0.1167   0.6193   0.6066
   2.000   0.7743   0.01609   0.00829  -0.1166   0.6154   0.6233
   2.250   0.7993   0.01610   0.00847  -0.1163   0.6108   0.6473
   2.500   0.8254   0.01600   0.00857  -0.1160   0.6071   0.6867
   2.750   0.8507   0.01575   0.00858  -0.1152   0.6038   0.7646
   3.000   0.8893   0.01548   0.00871  -0.1168   0.5992   0.9869
   3.250   0.9166   0.01565   0.00887  -0.1171   0.5945   1.0000
   3.500   0.9443   0.01577   0.00891  -0.1173   0.5905   1.0000
   3.750   0.9744   0.01587   0.00890  -0.1179   0.5871   1.0000
   4.000   0.9979   0.01612   0.00919  -0.1174   0.5826   1.0000
   4.250   1.0225   0.01631   0.00940  -0.1170   0.5778   1.0000
   4.500   1.0509   0.01641   0.00944  -0.1172   0.5734   1.0000
   4.750   1.0790   0.01656   0.00954  -0.1174   0.5690   1.0000
   5.000   1.1005   0.01678   0.00983  -0.1165   0.5629   1.0000
   5.250   1.1285   0.01683   0.00983  -0.1166   0.5570   1.0000
   5.500   1.1525   0.01700   0.01001  -0.1160   0.5506   1.0000
   5.750   1.1762   0.01712   0.01014  -0.1154   0.5432   1.0000
   6.000   1.2031   0.01723   0.01020  -0.1153   0.5364   1.0000
   6.250   1.2231   0.01741   0.01044  -0.1140   0.5280   1.0000
   6.500   1.2492   0.01753   0.01050  -0.1138   0.5203   1.0000
   6.750   1.2673   0.01771   0.01076  -0.1122   0.5108   1.0000
   7.000   1.2889   0.01790   0.01093  -0.1112   0.5018   1.0000
   7.250   1.3081   0.01806   0.01111  -0.1098   0.4917   1.0000
   7.500   1.3226   0.01832   0.01143  -0.1075   0.4802   1.0000
   7.750   1.3385   0.01855   0.01167  -0.1055   0.4688   1.0000
   8.000   1.3528   0.01879   0.01188  -0.1033   0.4568   1.0000
   8.250   1.3587   0.01914   0.01228  -0.0996   0.4433   1.0000
   8.500   1.3659   0.01959   0.01275  -0.0963   0.4292   1.0000
   8.750   1.3738   0.02013   0.01329  -0.0933   0.4150   1.0000
   9.000   1.3818   0.02078   0.01391  -0.0906   0.4011   1.0000
   9.250   1.3896   0.02154   0.01461  -0.0879   0.3879   1.0000
   9.500   1.3972   0.02241   0.01541  -0.0854   0.3761   1.0000
   9.750   1.4053   0.02337   0.01627  -0.0831   0.3655   1.0000
  10.000   1.4136   0.02441   0.01729  -0.0810   0.3550   1.0000
  10.250   1.4234   0.02545   0.01829  -0.0792   0.3461   1.0000
  10.500   1.4335   0.02652   0.01930  -0.0775   0.3374   1.0000
  10.750   1.4428   0.02766   0.02046  -0.0758   0.3289   1.0000
  11.000   1.4528   0.02880   0.02149  -0.0742   0.3196   1.0000
  11.250   1.4578   0.03022   0.02304  -0.0724   0.3110   1.0000
  11.500   1.4683   0.03138   0.02410  -0.0709   0.3029   1.0000
  11.750   1.4722   0.03296   0.02585  -0.0693   0.2953   1.0000
  12.000   1.4795   0.03435   0.02718  -0.0678   0.2872   1.0000
  12.250   1.4814   0.03619   0.02919  -0.0663   0.2791   1.0000
  12.500   1.4836   0.03803   0.03100  -0.0648   0.2703   1.0000
  12.750   1.4838   0.04021   0.03335  -0.0636   0.2601   1.0000
  13.000   1.4853   0.04235   0.03555  -0.0625   0.2507   1.0000
  13.250   1.4851   0.04471   0.03797  -0.0614   0.2407   1.0000
  13.500   1.4861   0.04711   0.04046  -0.0605   0.2288   1.0000
  13.750   1.4837   0.04990   0.04328  -0.0597   0.2143   1.0000
  14.000   1.4774   0.05317   0.04652  -0.0588   0.1976   1.0000
  14.250   1.4688   0.05675   0.05004  -0.0580   0.1820   1.0000
  14.500   1.4589   0.06057   0.05379  -0.0573   0.1683   1.0000
  14.750   1.4502   0.06436   0.05753  -0.0567   0.1563   1.0000
  15.000   1.4419   0.06817   0.06133  -0.0562   0.1438   1.0000
  15.250   1.4359   0.07179   0.06495  -0.0558   0.1315   1.0000
  15.500   1.4296   0.07554   0.06869  -0.0556   0.1178   1.0000
  15.750   1.4203   0.07972   0.07283  -0.0555   0.1014   1.0000
  16.000   1.4054   0.08466   0.07767  -0.0556   0.0840   1.0000
  16.250   1.3889   0.08986   0.08280  -0.0558   0.0688   1.0000
  16.500   1.3699   0.09553   0.08837  -0.0562   0.0441   1.0000
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