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GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 585 AIRFOIL (goe585-il)
Reynolds number: 50,000
Max Cl/Cd: 34.65 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe585-il-50000.txt
Download as CSV file: xf-goe585-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 585 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3985   0.10346   0.09647  -0.0186   1.0000   0.2076
  -8.000  -0.3856   0.09969   0.09270  -0.0173   1.0000   0.2180
  -7.750  -0.3900   0.09720   0.09033  -0.0171   1.0000   0.2242
  -7.500  -0.3948   0.09543   0.08866  -0.0161   1.0000   0.2350
  -7.250  -0.3836   0.09159   0.08483  -0.0146   1.0000   0.2453
  -7.000  -0.4117   0.09173   0.08519  -0.0156   1.0000   0.2516
  -6.750  -0.3970   0.08757   0.08106  -0.0127   1.0000   0.2650
  -6.500  -0.3904   0.08421   0.07776  -0.0110   1.0000   0.2752
  -6.250  -0.3965   0.08194   0.07560  -0.0104   1.0000   0.2860
  -5.750  -0.4042   0.07753   0.07137  -0.0086   1.0000   0.3142
  -5.500  -0.4013   0.07472   0.06863  -0.0062   1.0000   0.3301
  -5.250  -0.3942   0.07178   0.06576  -0.0025   1.0000   0.3499
  -5.000  -0.4031   0.07019   0.06426  -0.0012   1.0000   0.3746
  -4.750  -0.3975   0.06745   0.06157   0.0037   1.0000   0.4020
  -3.000  -0.2302   0.03677   0.02809  -0.0349   1.0000   0.1739
  -2.750  -0.2071   0.03426   0.02528  -0.0347   1.0000   0.1692
  -2.500  -0.1816   0.03191   0.02240  -0.0348   1.0000   0.1650
  -2.250  -0.1567   0.03010   0.02013  -0.0344   1.0000   0.1644
  -2.000  -0.1336   0.02881   0.01860  -0.0338   1.0000   0.1696
  -1.750  -0.1092   0.02769   0.01701  -0.0332   1.0000   0.1760
  -1.500  -0.0861   0.02653   0.01584  -0.0327   1.0000   0.1835
  -1.250  -0.0626   0.02557   0.01462  -0.0319   1.0000   0.1931
  -1.000  -0.0394   0.02480   0.01384  -0.0311   1.0000   0.2122
  -0.750  -0.0133   0.02408   0.01313  -0.0308   1.0000   0.2507
  -0.500   0.0122   0.02312   0.01259  -0.0305   1.0000   0.3332
  -0.250   0.0495   0.02002   0.01149  -0.0313   1.0000   1.0000
   0.000   0.0691   0.02048   0.01148  -0.0305   1.0000   1.0000
   0.250   0.0878   0.02098   0.01167  -0.0298   1.0000   1.0000
   0.500   0.1059   0.02153   0.01199  -0.0292   1.0000   1.0000
   0.750   0.1235   0.02213   0.01240  -0.0286   1.0000   1.0000
   1.000   0.1406   0.02280   0.01293  -0.0281   1.0000   1.0000
   1.250   0.1813   0.02391   0.01388  -0.0322   0.9889   1.0000
   1.500   0.2464   0.02519   0.01501  -0.0404   0.9643   1.0000
   1.750   0.3094   0.02612   0.01586  -0.0476   0.9387   1.0000
   2.000   0.3746   0.02671   0.01642  -0.0546   0.9121   1.0000
   2.250   0.4369   0.02687   0.01661  -0.0603   0.8840   1.0000
   2.500   0.4969   0.02664   0.01646  -0.0650   0.8545   1.0000
   2.750   0.5600   0.02595   0.01588  -0.0693   0.8249   1.0000
   3.000   0.6165   0.02502   0.01506  -0.0718   0.7945   1.0000
   3.250   0.6653   0.02409   0.01419  -0.0727   0.7624   1.0000
   3.500   0.7024   0.02358   0.01370  -0.0719   0.7264   1.0000
   3.750   0.7388   0.02318   0.01324  -0.0710   0.6912   1.0000
   4.000   0.7706   0.02314   0.01308  -0.0698   0.6574   1.0000
   4.250   0.7955   0.02350   0.01337  -0.0681   0.6242   1.0000
   4.500   0.8214   0.02392   0.01372  -0.0667   0.5950   1.0000
   4.750   0.8468   0.02444   0.01416  -0.0654   0.5687   1.0000
   5.000   0.8697   0.02520   0.01492  -0.0641   0.5443   1.0000
   5.250   0.8958   0.02589   0.01556  -0.0631   0.5237   1.0000
   5.500   0.9184   0.02683   0.01654  -0.0620   0.5039   1.0000
   5.750   0.9413   0.02786   0.01763  -0.0609   0.4862   1.0000
   6.000   0.9642   0.02896   0.01879  -0.0599   0.4697   1.0000
   6.250   0.9866   0.03013   0.02008  -0.0588   0.4542   1.0000
   6.500   1.0082   0.03143   0.02149  -0.0577   0.4396   1.0000
   6.750   1.0291   0.03275   0.02294  -0.0565   0.4245   1.0000
   7.000   1.0493   0.03408   0.02439  -0.0552   0.4090   1.0000
   7.250   1.0702   0.03523   0.02565  -0.0537   0.3917   1.0000
   7.500   1.0935   0.03615   0.02655  -0.0524   0.3730   1.0000
   7.750   1.1092   0.03752   0.02810  -0.0504   0.3545   1.0000
   8.000   1.1246   0.03886   0.02963  -0.0484   0.3349   1.0000
   8.250   1.1481   0.03964   0.03035  -0.0469   0.3129   1.0000
   8.500   1.1583   0.04131   0.03232  -0.0443   0.2914   1.0000
   8.750   1.1779   0.04208   0.03302  -0.0422   0.2654   1.0000
   9.000   1.1962   0.04278   0.03360  -0.0400   0.2381   1.0000
   9.250   1.2009   0.04442   0.03550  -0.0366   0.2145   1.0000
   9.500   1.2126   0.04522   0.03622  -0.0339   0.1901   1.0000
   9.750   1.2298   0.04564   0.03633  -0.0319   0.1662   1.0000
  10.000   1.2335   0.04788   0.03881  -0.0288   0.1507   1.0000
  10.250   1.2407   0.05008   0.04108  -0.0263   0.1374   1.0000
  10.500   1.2402   0.05300   0.04435  -0.0234   0.1284   1.0000
  10.750   1.2392   0.05662   0.04822  -0.0209   0.1227   1.0000
  11.000   1.2244   0.06075   0.05278  -0.0178   0.1198   1.0000
  11.250   1.2401   0.06290   0.05478  -0.0166   0.1118   1.0000
  11.500   1.2175   0.06712   0.05936  -0.0134   0.1113   1.0000
  11.750   1.1916   0.07152   0.06402  -0.0109   0.1113   1.0000
  12.000   1.1657   0.07656   0.06926  -0.0100   0.1117   1.0000
  12.250   1.1398   0.08236   0.07521  -0.0105   0.1122   1.0000
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