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GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 547 AIRFOIL (goe547-il)
Reynolds number: 100,000
Max Cl/Cd: 60.36 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe547-il-100000.txt
Download as CSV file: xf-goe547-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 547 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4331   0.09820   0.09374  -0.0278   1.0000   0.1221
  -7.500  -0.4692   0.09770   0.09338  -0.0264   1.0000   0.1230
  -7.250  -0.5041   0.09515   0.09091  -0.0329   1.0000   0.1238
  -7.000  -0.4747   0.09196   0.08773  -0.0218   1.0000   0.1267
  -6.750  -0.4749   0.09003   0.08583  -0.0193   1.0000   0.1300
  -6.500  -0.4878   0.08770   0.08355  -0.0203   1.0000   0.1353
  -6.250  -0.5042   0.08319   0.07906  -0.0263   1.0000   0.1394
  -6.000  -0.4958   0.08219   0.07811  -0.0193   1.0000   0.1435
  -5.750  -0.5015   0.07720   0.07303  -0.0283   0.9996   0.1536
  -5.500  -0.4780   0.07550   0.07138  -0.0245   0.9957   0.1593
  -5.250  -0.4518   0.07083   0.06661  -0.0316   0.9889   0.1719
  -5.000  -0.4178   0.06641   0.06185  -0.0439   0.9809   0.1968
  -4.750  -0.3997   0.06328   0.05885  -0.0416   0.9760   0.2011
  -4.500  -0.3397   0.04452   0.03803  -0.0645   0.9718   0.1237
  -4.250  -0.3212   0.04450   0.03868  -0.0635   0.9649   0.1427
  -4.000  -0.2764   0.03453   0.02653  -0.0679   0.9621   0.0960
  -3.750  -0.2409   0.03247   0.02410  -0.0700   0.9578   0.0969
  -3.500  -0.2142   0.03103   0.02245  -0.0704   0.9512   0.0987
  -3.250  -0.1768   0.02967   0.02070  -0.0722   0.9467   0.0988
  -3.000  -0.1478   0.02867   0.01949  -0.0726   0.9404   0.1002
  -2.750  -0.1146   0.02780   0.01847  -0.0737   0.9348   0.1028
  -2.500  -0.0746   0.02722   0.01768  -0.0759   0.9312   0.1082
  -2.250  -0.0538   0.02651   0.01705  -0.0750   0.9233   0.1142
  -2.000  -0.0175   0.02600   0.01651  -0.0766   0.9186   0.1231
  -1.750   0.0079   0.02553   0.01616  -0.0763   0.9123   0.1365
  -1.500   0.0364   0.02497   0.01592  -0.0767   0.9064   0.1805
  -1.250   0.0719   0.02385   0.01604  -0.0784   0.9027   0.4417
  -1.000   0.0893   0.02382   0.01636  -0.0767   0.8950   0.5547
  -0.750   0.1503   0.02278   0.01645  -0.0825   0.8926   1.0000
  -0.500   0.1910   0.02308   0.01641  -0.0853   0.8883   1.0000
  -0.250   0.2099   0.02352   0.01665  -0.0842   0.8800   1.0000
   0.000   0.2446   0.02384   0.01676  -0.0858   0.8748   1.0000
   0.250   0.2718   0.02426   0.01702  -0.0862   0.8685   1.0000
   0.500   0.2977   0.02465   0.01728  -0.0862   0.8615   1.0000
   0.750   0.3387   0.02488   0.01737  -0.0887   0.8577   1.0000
   1.000   0.3506   0.02551   0.01792  -0.0865   0.8485   1.0000
   1.250   0.3881   0.02574   0.01806  -0.0884   0.8439   1.0000
   1.500   0.4052   0.02635   0.01860  -0.0870   0.8356   1.0000
   1.750   0.4390   0.02659   0.01878  -0.0882   0.8300   1.0000
   2.000   0.4640   0.02705   0.01921  -0.0880   0.8230   1.0000
   2.250   0.4930   0.02733   0.01946  -0.0883   0.8157   1.0000
   2.500   0.5238   0.02749   0.01960  -0.0887   0.8077   1.0000
   2.750   0.5679   0.02702   0.01913  -0.0907   0.7997   1.0000
   3.000   0.5964   0.02695   0.01906  -0.0904   0.7888   1.0000
   3.250   0.6504   0.02603   0.01817  -0.0937   0.7841   1.0000
   3.500   0.6689   0.02642   0.01860  -0.0921   0.7734   1.0000
   3.750   0.7192   0.02565   0.01790  -0.0950   0.7695   1.0000
   4.000   0.7375   0.02603   0.01833  -0.0933   0.7590   1.0000
   4.250   0.7952   0.02485   0.01727  -0.0972   0.7547   1.0000
   4.500   0.8191   0.02484   0.01733  -0.0960   0.7438   1.0000
   4.750   0.8801   0.02325   0.01588  -0.0999   0.7385   1.0000
   5.000   0.9064   0.02298   0.01570  -0.0988   0.7262   1.0000
   5.250   0.9393   0.02243   0.01526  -0.0986   0.7144   1.0000
   5.500   0.9782   0.02164   0.01461  -0.0993   0.7027   1.0000
   5.750   1.0168   0.02093   0.01401  -0.1000   0.6901   1.0000
   6.000   1.0459   0.02043   0.01361  -0.0991   0.6730   1.0000
   6.250   1.0770   0.01981   0.01306  -0.0983   0.6525   1.0000
   6.500   1.1034   0.01934   0.01266  -0.0968   0.6281   1.0000
   6.750   1.1268   0.01906   0.01240  -0.0949   0.6007   1.0000
   7.000   1.1439   0.01904   0.01242  -0.0921   0.5705   1.0000
   7.250   1.1558   0.01915   0.01254  -0.0884   0.5341   1.0000
   7.500   1.1649   0.01937   0.01268  -0.0843   0.4895   1.0000
   7.750   1.1706   0.01985   0.01289  -0.0798   0.4371   1.0000
   8.000   1.1714   0.02066   0.01337  -0.0747   0.3850   1.0000
   8.250   1.1698   0.02173   0.01409  -0.0696   0.3375   1.0000
   8.500   1.1678   0.02295   0.01502  -0.0648   0.2927   1.0000
   8.750   1.1659   0.02427   0.01611  -0.0604   0.2493   1.0000
   9.000   1.1641   0.02574   0.01734  -0.0563   0.2060   1.0000
   9.250   1.1607   0.02747   0.01877  -0.0522   0.1608   1.0000
   9.500   1.1547   0.02969   0.02063  -0.0482   0.1265   1.0000
   9.750   1.1488   0.03231   0.02298  -0.0442   0.1005   1.0000
  10.000   1.1517   0.03437   0.02497  -0.0414   0.0824   1.0000
  10.250   1.1590   0.03619   0.02675  -0.0391   0.0721   1.0000
  10.500   1.1722   0.03814   0.02854  -0.0375   0.0657   1.0000
  10.750   1.1938   0.03986   0.03039  -0.0364   0.0606   1.0000
  11.000   1.2265   0.04229   0.03266  -0.0369   0.0550   1.0000
  11.250   1.2468   0.04426   0.03495  -0.0359   0.0522   1.0000
  11.500   1.2751   0.04691   0.03785  -0.0358   0.0501   1.0000
  11.750   1.2969   0.04985   0.04105  -0.0352   0.0487   1.0000
  12.000   1.3100   0.05287   0.04435  -0.0339   0.0478   1.0000
  12.250   1.3175   0.05584   0.04755  -0.0322   0.0468   1.0000
  12.500   1.3259   0.05964   0.05155  -0.0310   0.0457   1.0000
  13.000   1.3115   0.06792   0.06041  -0.0263   0.0448   1.0000
  13.250   1.2956   0.07123   0.06402  -0.0236   0.0447   1.0000
  13.500   1.2795   0.07514   0.06820  -0.0216   0.0447   1.0000
  13.750   1.2663   0.07957   0.07290  -0.0203   0.0450   1.0000
  14.000   1.2465   0.08341   0.07700  -0.0191   0.0451   1.0000
  14.250   1.2245   0.08721   0.08107  -0.0186   0.0455   1.0000
  14.500   1.1937   0.09246   0.08664  -0.0193   0.0462   1.0000
  14.750   1.1168   0.10471   0.09943  -0.0253   0.0487   1.0000
  15.000   1.0667   0.11754   0.11251  -0.0329   0.0517   1.0000
  15.250   1.0349   0.12886   0.12393  -0.0399   0.0533   1.0000
  15.500   1.0175   0.13820   0.13328  -0.0450   0.0545   1.0000
  15.750   1.0127   0.14500   0.14007  -0.0476   0.0553   1.0000
  16.000   0.7643   0.17819   0.17384  -0.0653   0.1187   1.0000
  16.250   0.7632   0.18304   0.17868  -0.0674   0.1180   1.0000
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