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GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il)
Reynolds number: 50,000
Max Cl/Cd: 29.19 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe147-il-50000.txt
Download as CSV file: xf-goe147-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 147 (MVA H.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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3773   0.12134   0.11498   0.0081   1.0000   0.1435
  -9.500  -0.3833   0.11966   0.11335   0.0064   1.0000   0.1461
  -9.250  -0.3945   0.11872   0.11249   0.0040   1.0000   0.1471
  -9.000  -0.3696   0.11114   0.10491   0.0057   1.0000   0.1508
  -8.750  -0.3639   0.10757   0.10137   0.0053   1.0000   0.1556
  -8.500  -0.3688   0.10539   0.09925   0.0036   1.0000   0.1597
  -8.250  -0.3813   0.10422   0.09818   0.0008   1.0000   0.1611
  -8.000  -0.3552   0.09716   0.09110   0.0033   1.0000   0.1687
  -7.750  -0.3600   0.09481   0.08883   0.0015   1.0000   0.1738
  -7.500  -0.3745   0.09354   0.08770  -0.0017   1.0000   0.1753
  -7.250  -0.3478   0.08667   0.08077   0.0012   1.0000   0.1833
  -7.000  -0.3560   0.08448   0.07870  -0.0011   1.0000   0.1886
  -6.750  -0.3522   0.08022   0.07450  -0.0019   1.0000   0.1918
  -6.500  -0.3426   0.07612   0.07044  -0.0016   1.0000   0.1992
  -6.250  -0.3461   0.07299   0.06741  -0.0072   1.0000   0.2047
  -6.000  -0.3995   0.08214   0.07604  -0.0101   1.0000   0.2041
  -5.750  -0.3868   0.07694   0.07092  -0.0053   1.0000   0.2099
  -5.500  -0.3721   0.07335   0.06734  -0.0097   1.0000   0.2206
  -5.250  -0.3562   0.06977   0.06376  -0.0124   1.0000   0.2342
  -5.000  -0.3420   0.06605   0.06008  -0.0121   1.0000   0.2509
  -4.750  -0.3242   0.06294   0.05694  -0.0156   1.0000   0.2763
  -4.500  -0.3105   0.05905   0.05312  -0.0138   1.0000   0.2946
  -4.250  -0.2945   0.05564   0.04971  -0.0143   1.0000   0.3227
  -3.750  -0.1844   0.04270   0.03538  -0.0400   1.0000   0.1908
  -3.500  -0.1540   0.03823   0.03062  -0.0420   1.0000   0.1838
  -3.250  -0.1248   0.03494   0.02697  -0.0435   1.0000   0.1996
  -3.000  -0.0977   0.03190   0.02365  -0.0442   1.0000   0.2244
  -2.750  -0.0719   0.02950   0.02095  -0.0444   1.0000   0.2577
  -2.500  -0.0496   0.02793   0.01924  -0.0440   1.0000   0.2917
  -2.250  -0.0242   0.02661   0.01764  -0.0442   1.0000   0.3048
  -2.000  -0.0021   0.02545   0.01641  -0.0439   1.0000   0.3138
  -1.750   0.0212   0.02466   0.01538  -0.0440   1.0000   0.3151
  -1.500   0.0426   0.02415   0.01466  -0.0440   1.0000   0.3165
  -1.250   0.0624   0.02383   0.01419  -0.0441   1.0000   0.3212
  -1.000   0.0818   0.02367   0.01396  -0.0444   1.0000   0.3254
  -0.750   0.1023   0.02370   0.01387  -0.0451   1.0000   0.3278
  -0.500   0.1508   0.02359   0.01349  -0.0504   0.9867   0.3324
  -0.250   0.2232   0.02299   0.01275  -0.0590   0.9600   0.3427
   0.000   0.2934   0.02224   0.01201  -0.0665   0.9335   0.3646
   0.250   0.3525   0.02138   0.01130  -0.0714   0.9055   0.3926
   0.500   0.3964   0.02036   0.01076  -0.0732   0.8759   0.4484
   0.750   0.4316   0.01891   0.01030  -0.0719   0.8451   1.0000
   1.000   0.4601   0.01920   0.01015  -0.0701   0.8128   1.0000
   1.250   0.4845   0.01954   0.01020  -0.0677   0.7810   1.0000
   1.500   0.5073   0.01991   0.01031  -0.0651   0.7494   1.0000
   1.750   0.5298   0.02035   0.01056  -0.0628   0.7171   1.0000
   2.000   0.5530   0.02086   0.01087  -0.0608   0.6857   1.0000
   2.250   0.5766   0.02139   0.01121  -0.0590   0.6562   1.0000
   2.500   0.6006   0.02196   0.01157  -0.0572   0.6298   1.0000
   2.750   0.6250   0.02262   0.01212  -0.0560   0.6035   1.0000
   3.000   0.6497   0.02335   0.01275  -0.0549   0.5790   1.0000
   3.250   0.6744   0.02396   0.01320  -0.0536   0.5577   1.0000
   3.500   0.6989   0.02470   0.01391  -0.0527   0.5342   1.0000
   3.750   0.7236   0.02526   0.01435  -0.0514   0.5138   1.0000
   4.000   0.7482   0.02601   0.01510  -0.0506   0.4926   1.0000
   4.250   0.7730   0.02672   0.01578  -0.0497   0.4733   1.0000
   4.500   0.7981   0.02742   0.01643  -0.0488   0.4560   1.0000
   4.750   0.8232   0.02820   0.01721  -0.0480   0.4399   1.0000
   5.000   0.8481   0.02909   0.01812  -0.0473   0.4240   1.0000
   5.250   0.8728   0.03014   0.01925  -0.0468   0.4088   1.0000
   5.500   0.8978   0.03125   0.02040  -0.0462   0.3961   1.0000
   5.750   0.9215   0.03286   0.02227  -0.0461   0.3839   1.0000
   6.000   0.9441   0.03483   0.02451  -0.0462   0.3734   1.0000
   6.250   0.9684   0.03634   0.02609  -0.0457   0.3655   1.0000
   6.500   0.9885   0.03882   0.02893  -0.0460   0.3568   1.0000
   6.750   1.0104   0.04085   0.03113  -0.0459   0.3503   1.0000
   7.000   1.0259   0.04423   0.03497  -0.0466   0.3438   1.0000
   7.250   1.0455   0.04679   0.03775  -0.0467   0.3398   1.0000
   7.500   1.0608   0.05038   0.04161  -0.0473   0.3373   1.0000
   7.750   1.0593   0.05706   0.04874  -0.0500   0.3363   1.0000
   8.000   1.0542   0.06422   0.05619  -0.0531   0.3371   1.0000
   9.500   1.2280   0.05299   0.04574  -0.0359   0.2347   1.0000
   9.750   1.2591   0.04469   0.03715  -0.0308   0.1756   1.0000
  10.000   1.2654   0.04456   0.03668  -0.0280   0.1372   1.0000
  10.250   1.2690   0.04738   0.03955  -0.0262   0.1193   1.0000
  10.500   1.2726   0.05024   0.04247  -0.0246   0.1081   1.0000
  10.750   1.2783   0.05254   0.04466  -0.0231   0.0993   1.0000
  11.000   1.2707   0.05677   0.04935  -0.0221   0.0950   1.0000
  11.250   1.2637   0.06029   0.05305  -0.0209   0.0916   1.0000
  11.500   1.2694   0.06305   0.05575  -0.0196   0.0878   1.0000
  11.750   1.2515   0.06836   0.06139  -0.0204   0.0874   1.0000
  12.000   1.2305   0.07459   0.06788  -0.0227   0.0874   1.0000
  12.250   1.2073   0.08179   0.07529  -0.0264   0.0878   1.0000
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