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GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 507 AIRFOIL (goe507-il)
Reynolds number: 100,000
Max Cl/Cd: 55.45 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe507-il-100000.txt
Download as CSV file: xf-goe507-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 507 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4164   0.10796   0.10256  -0.0251   1.0000   0.1081
  -9.500  -0.4365   0.10665   0.10136  -0.0300   1.0000   0.1119
  -9.250  -0.4603   0.10515   0.10001  -0.0349   1.0000   0.1125
  -9.000  -0.4114   0.09840   0.09312  -0.0277   1.0000   0.1175
  -8.750  -0.4106   0.09575   0.09052  -0.0285   1.0000   0.1228
  -8.500  -0.4389   0.09444   0.08938  -0.0329   1.0000   0.1260
  -8.250  -0.4170   0.08969   0.08460  -0.0300   1.0000   0.1300
  -8.000  -0.4130   0.08726   0.08220  -0.0292   1.0000   0.1363
  -7.750  -0.4392   0.08564   0.08075  -0.0311   1.0000   0.1397
  -7.500  -0.4770   0.08393   0.07908  -0.0381   1.0000   0.1410
  -7.250  -0.4362   0.07936   0.07457  -0.0282   1.0000   0.1460
  -7.000  -0.4416   0.07710   0.07237  -0.0274   1.0000   0.1511
  -6.750  -0.4777   0.07502   0.07024  -0.0329   1.0000   0.1562
  -6.500  -0.4637   0.07165   0.06700  -0.0270   1.0000   0.1587
  -6.250  -0.4609   0.06966   0.06504  -0.0240   1.0000   0.1639
  -6.000  -0.4739   0.06649   0.06174  -0.0273   1.0000   0.1722
  -5.750  -0.4660   0.06427   0.05963  -0.0226   1.0000   0.1763
  -5.500  -0.4675   0.06125   0.05640  -0.0253   1.0000   0.1876
  -5.250  -0.4601   0.05861   0.05385  -0.0220   1.0000   0.1907
  -5.000  -0.4535   0.05575   0.05077  -0.0238   1.0000   0.2031
  -4.750  -0.4445   0.05327   0.04836  -0.0209   1.0000   0.2075
  -4.500  -0.4143   0.03793   0.03127  -0.0312   1.0000   0.1278
  -4.250  -0.3960   0.03495   0.02805  -0.0304   1.0000   0.1237
  -4.000  -0.3765   0.03215   0.02481  -0.0299   1.0000   0.1232
  -3.750  -0.3553   0.02959   0.02185  -0.0293   1.0000   0.1216
  -3.500  -0.3335   0.02764   0.01949  -0.0285   1.0000   0.1221
  -3.250  -0.3116   0.02618   0.01762  -0.0277   1.0000   0.1242
  -3.000  -0.2894   0.02486   0.01595  -0.0269   1.0000   0.1250
  -2.750  -0.2673   0.02381   0.01458  -0.0260   1.0000   0.1259
  -2.500  -0.2460   0.02288   0.01357  -0.0252   1.0000   0.1289
  -2.250  -0.2227   0.02236   0.01302  -0.0248   0.9993   0.1327
  -2.000  -0.1816   0.02183   0.01232  -0.0276   0.9933   0.1367
  -1.750  -0.1418   0.02138   0.01169  -0.0300   0.9865   0.1411
  -1.500  -0.1029   0.02100   0.01146  -0.0325   0.9798   0.1482
  -1.250  -0.0628   0.02077   0.01125  -0.0351   0.9724   0.1592
  -1.000  -0.0263   0.02050   0.01108  -0.0369   0.9644   0.1736
  -0.750   0.0150   0.02009   0.01094  -0.0396   0.9571   0.2099
  -0.500   0.0880   0.01719   0.01086  -0.0483   0.9571   1.0000
  -0.250   0.1250   0.01745   0.01082  -0.0502   0.9468   1.0000
   0.000   0.1702   0.01775   0.01090  -0.0537   0.9382   1.0000
   0.250   0.2112   0.01795   0.01095  -0.0563   0.9280   1.0000
   0.500   0.2489   0.01814   0.01103  -0.0583   0.9169   1.0000
   0.750   0.3037   0.01820   0.01101  -0.0633   0.9099   1.0000
   1.000   0.3390   0.01827   0.01103  -0.0646   0.8972   1.0000
   1.250   0.3791   0.01827   0.01101  -0.0667   0.8854   1.0000
   1.500   0.4398   0.01790   0.01065  -0.0722   0.8788   1.0000
   1.750   0.4764   0.01770   0.01045  -0.0731   0.8649   1.0000
   2.000   0.5127   0.01741   0.01018  -0.0738   0.8507   1.0000
   2.250   0.5467   0.01712   0.00992  -0.0739   0.8364   1.0000
   2.500   0.5783   0.01686   0.00970  -0.0735   0.8219   1.0000
   2.750   0.6082   0.01663   0.00950  -0.0729   0.8071   1.0000
   3.000   0.6372   0.01637   0.00929  -0.0720   0.7913   1.0000
   3.250   0.6665   0.01594   0.00887  -0.0707   0.7733   1.0000
   3.500   0.6922   0.01557   0.00850  -0.0689   0.7517   1.0000
   3.750   0.7173   0.01525   0.00817  -0.0670   0.7280   1.0000
   4.000   0.7411   0.01508   0.00802  -0.0652   0.7030   1.0000
   4.250   0.7657   0.01494   0.00785  -0.0635   0.6771   1.0000
   4.500   0.7888   0.01490   0.00777  -0.0617   0.6479   1.0000
   4.750   0.8102   0.01495   0.00778  -0.0596   0.6129   1.0000
   5.000   0.8320   0.01510   0.00784  -0.0577   0.5786   1.0000
   5.250   0.8528   0.01538   0.00796  -0.0557   0.5409   1.0000
   5.500   0.8717   0.01577   0.00822  -0.0536   0.4995   1.0000
   5.750   0.8894   0.01621   0.00857  -0.0513   0.4551   1.0000
   6.000   0.9045   0.01674   0.00893  -0.0487   0.3964   1.0000
   6.250   0.9120   0.01782   0.00943  -0.0450   0.2900   1.0000
   6.500   0.9156   0.01976   0.01050  -0.0412   0.1824   1.0000
   6.750   0.9279   0.02117   0.01155  -0.0387   0.1490   1.0000
   7.000   0.9429   0.02236   0.01264  -0.0366   0.1320   1.0000
   7.250   0.9587   0.02363   0.01379  -0.0346   0.1202   1.0000
   7.500   0.9760   0.02511   0.01509  -0.0330   0.1105   1.0000
   7.750   0.9973   0.02639   0.01644  -0.0318   0.1021   1.0000
   8.000   1.0218   0.02830   0.01825  -0.0313   0.0949   1.0000
   8.250   1.0460   0.02990   0.01997  -0.0306   0.0887   1.0000
   8.500   1.0743   0.03255   0.02252  -0.0309   0.0829   1.0000
   8.750   1.0968   0.03448   0.02478  -0.0297   0.0797   1.0000
   9.000   1.1183   0.03654   0.02705  -0.0287   0.0756   1.0000
   9.250   1.1405   0.03955   0.03008  -0.0284   0.0719   1.0000
   9.500   1.1564   0.04338   0.03427  -0.0270   0.0705   1.0000
   9.750   1.1657   0.04582   0.03721  -0.0244   0.0696   1.0000
  10.000   1.1713   0.04851   0.04038  -0.0216   0.0685   1.0000
  10.250   1.1730   0.05144   0.04376  -0.0187   0.0672   1.0000
  10.500   1.1716   0.05488   0.04759  -0.0158   0.0669   1.0000
  10.750   1.1660   0.05870   0.05178  -0.0129   0.0674   1.0000
  11.000   1.1563   0.06271   0.05612  -0.0100   0.0681   1.0000
  11.250   1.1448   0.06682   0.06046  -0.0073   0.0690   1.0000
  11.500   1.1359   0.07171   0.06550  -0.0054   0.0701   1.0000
  11.750   1.0460   0.07026   0.06451   0.0013   0.0712   1.0000
  12.000   1.0099   0.07321   0.06770   0.0032   0.0720   1.0000
  12.250   0.8727   0.08867   0.08374  -0.0048   0.0787   1.0000
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