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GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il)
Reynolds number: 50,000
Max Cl/Cd: 5.1 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe255-il-50000.txt
Download as CSV file: xf-goe255-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3320   0.13726   0.13152  -0.0237   1.0000   0.2708
 -10.000  -0.3619   0.13733   0.13172  -0.0220   1.0000   0.2736
  -9.750  -0.4382   0.12350   0.11802  -0.0315   1.0000   0.1782
  -9.500  -0.4277   0.12063   0.11516  -0.0290   1.0000   0.1749
  -9.250  -0.4654   0.11396   0.10861  -0.0308   1.0000   0.1602
  -9.000  -0.5951   0.09477   0.08968  -0.0403   1.0000   0.1329
  -8.750  -0.6198   0.09020   0.08516  -0.0404   1.0000   0.1318
  -8.500  -0.6485   0.08462   0.07960  -0.0411   1.0000   0.1302
  -8.250  -0.6829   0.07719   0.07202  -0.0431   1.0000   0.1277
  -8.000  -0.7022   0.06787   0.06222  -0.0484   0.9964   0.1268
  -7.750  -0.6964   0.06005   0.05360  -0.0541   0.9900   0.1305
  -7.500  -0.6696   0.05619   0.04938  -0.0579   0.9830   0.1380
  -7.250  -0.6480   0.05198   0.04438  -0.0609   0.9761   0.1483
  -7.000  -0.6130   0.05041   0.04279  -0.0637   0.9692   0.1653
  -6.750  -0.5893   0.04934   0.04179  -0.0642   0.9615   0.1846
  -6.500  -0.5557   0.04843   0.04082  -0.0665   0.9546   0.2141
  -6.250  -0.5346   0.04828   0.04071  -0.0662   0.9472   0.2400
  -5.750  -0.4858   0.04950   0.04205  -0.0658   0.9356   0.2903
  -5.500  -0.4653   0.05081   0.04351  -0.0641   0.9308   0.3092
  -5.250  -0.4333   0.05165   0.04425  -0.0649   0.9259   0.3348
  -5.000  -0.4189   0.05153   0.04397  -0.0638   0.9217   0.3542
  -4.750  -0.4022   0.05196   0.04438  -0.0623   0.9181   0.3724
  -4.500  -0.3832   0.05225   0.04461  -0.0614   0.9156   0.3911
  -4.250  -0.5178   0.04884   0.04148  -0.0381   1.0000   0.3583
  -4.000  -0.5004   0.04912   0.04170  -0.0370   1.0000   0.3783
  -3.750  -0.4815   0.04913   0.04157  -0.0365   1.0000   0.3992
  -3.500  -0.4609   0.04899   0.04122  -0.0367   1.0000   0.4217
  -3.250  -0.4434   0.04913   0.04132  -0.0357   1.0000   0.4404
  -3.000  -0.4260   0.04931   0.04148  -0.0347   1.0000   0.4597
  -2.750  -0.4083   0.04949   0.04162  -0.0337   1.0000   0.4800
  -2.500  -0.3894   0.04962   0.04168  -0.0332   1.0000   0.5015
  -2.250  -0.3679   0.04968   0.04156  -0.0335   1.0000   0.5246
  -2.000  -0.3493   0.04982   0.04166  -0.0329   1.0000   0.5437
  -1.750  -0.3302   0.05000   0.04180  -0.0324   1.0000   0.5633
  -1.500  -0.3111   0.05024   0.04196  -0.0320   1.0000   0.5831
  -1.250  -0.2914   0.05053   0.04219  -0.0318   1.0000   0.6030
  -1.000  -0.2712   0.05092   0.04249  -0.0318   1.0000   0.6230
  -0.750  -0.2507   0.05137   0.04286  -0.0319   1.0000   0.6421
  -0.500  -0.2303   0.05190   0.04331  -0.0321   1.0000   0.6608
  -0.250  -0.2102   0.05250   0.04383  -0.0322   1.0000   0.6790
   0.250  -0.1681   0.05400   0.04522  -0.0329   0.9991   0.7148
   0.500  -0.1307   0.05586   0.04704  -0.0362   0.9918   0.7369
   0.750  -0.0879   0.05827   0.04939  -0.0406   0.9823   0.7633
   1.000  -0.0603   0.05938   0.05055  -0.0421   0.9711   0.7881
   1.250  -0.0375   0.06031   0.05154  -0.0427   0.9603   0.8165
   1.500  -0.0160   0.06138   0.05274  -0.0427   0.9506   0.8512
   1.750   0.0125   0.06273   0.05429  -0.0444   0.9385   0.9147
   2.000   0.0434   0.06356   0.05505  -0.0490   0.9187   1.0000
   2.250   0.0868   0.06590   0.05712  -0.0561   0.9025   1.0000
   2.500   0.1264   0.06826   0.05920  -0.0617   0.8850   1.0000
   2.750   0.1636   0.07073   0.06142  -0.0662   0.8673   1.0000
   3.000   0.2016   0.07350   0.06397  -0.0702   0.8496   1.0000
   3.250   0.2281   0.07572   0.06603  -0.0722   0.8318   1.0000
   3.500   0.2437   0.07724   0.06744  -0.0724   0.8131   1.0000
   3.750   0.2719   0.07978   0.06985  -0.0744   0.7981   1.0000
   4.000   0.3014   0.08233   0.07227  -0.0764   0.7824   1.0000
   4.500   0.4152   0.08144   0.07096  -0.0789   0.6823   1.0000
   4.750   0.4171   0.08450   0.07402  -0.0788   0.6822   1.0000
   5.000   0.3600   0.09017   0.07985  -0.0770   0.7353   1.0000
   5.250   0.3691   0.09244   0.08208  -0.0768   0.7288   1.0000
   5.500   0.3938   0.09480   0.08439  -0.0780   0.7177   1.0000
   5.750   0.3984   0.09693   0.08650  -0.0773   0.7124   1.0000
   6.000   0.4114   0.09890   0.08844  -0.0774   0.7035   1.0000
   6.250   0.4430   0.10262   0.09211  -0.0797   0.6987   1.0000
   6.500   0.4341   0.10331   0.09281  -0.0774   0.6892   1.0000
   6.750   0.4725   0.10723   0.09669  -0.0802   0.6829   1.0000
   7.000   0.4586   0.10798   0.09746  -0.0777   0.6758   1.0000
   7.250   0.4855   0.11093   0.10040  -0.0792   0.6681   1.0000
   7.500   0.4858   0.11276   0.10224  -0.0782   0.6613   1.0000
   7.750   0.5091   0.11543   0.10491  -0.0793   0.6522   1.0000
   8.000   0.5112   0.11742   0.10691  -0.0786   0.6451   1.0000
   8.250   0.5392   0.12043   0.10994  -0.0800   0.6353   1.0000
   8.500   0.5353   0.12187   0.11140  -0.0787   0.6261   1.0000
   8.750   0.5760   0.12626   0.11580  -0.0813   0.6179   1.0000
   9.000   0.5643   0.12668   0.11627  -0.0794   0.6066   1.0000
   9.250   0.5784   0.12962   0.11923  -0.0799   0.5993   1.0000
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