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GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.1 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe117-il-1000000.txt
Download as CSV file: xf-goe117-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 117 (MVA MK.4) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3527   0.10616   0.10453  -0.0367   1.0000   0.0110
 -10.000  -0.3600   0.10094   0.09935  -0.0377   1.0000   0.0114
  -9.000  -0.4940   0.02200   0.01925  -0.1047   0.9632   0.0085
  -8.750  -0.4593   0.02093   0.01803  -0.1074   0.9574   0.0089
  -8.500  -0.4295   0.01865   0.01541  -0.1097   0.9468   0.0093
  -8.250  -0.3987   0.01720   0.01371  -0.1114   0.9350   0.0098
  -8.000  -0.3712   0.01595   0.01218  -0.1122   0.9216   0.0104
  -7.750  -0.3444   0.01539   0.01145  -0.1123   0.9095   0.0108
  -7.500  -0.3240   0.01353   0.00921  -0.1116   0.8979   0.0117
  -7.250  -0.2980   0.01326   0.00886  -0.1115   0.8885   0.0124
  -7.000  -0.2719   0.01304   0.00857  -0.1112   0.8801   0.0130
  -6.750  -0.2461   0.01270   0.00811  -0.1109   0.8721   0.0138
  -6.500  -0.2204   0.01230   0.00759  -0.1106   0.8640   0.0146
  -6.250  -0.1940   0.01211   0.00730  -0.1103   0.8563   0.0152
  -6.000  -0.1707   0.01106   0.00609  -0.1097   0.8480   0.0167
  -5.750  -0.1437   0.01106   0.00606  -0.1096   0.8401   0.0177
  -5.500  -0.1169   0.01100   0.00595  -0.1094   0.8319   0.0190
  -5.250  -0.0902   0.01082   0.00570  -0.1091   0.8238   0.0203
  -4.750  -0.0396   0.00970   0.00435  -0.1083   0.8058   0.0232
  -4.500  -0.0133   0.00949   0.00410  -0.1080   0.7958   0.0249
  -4.250   0.0129   0.00928   0.00382  -0.1077   0.7842   0.0265
  -4.000   0.0390   0.00905   0.00351  -0.1073   0.7701   0.0278
  -3.750   0.0650   0.00886   0.00322  -0.1069   0.7525   0.0289
  -3.500   0.0909   0.00885   0.00310  -0.1064   0.7297   0.0297
  -3.250   0.1151   0.00845   0.00251  -0.1057   0.7001   0.0312
  -3.000   0.1396   0.00823   0.00209  -0.1050   0.6704   0.0332
  -2.750   0.1649   0.00814   0.00187  -0.1044   0.6480   0.0352
  -2.500   0.1909   0.00807   0.00169  -0.1040   0.6318   0.0364
  -2.250   0.2173   0.00801   0.00154  -0.1037   0.6193   0.0376
  -2.000   0.2440   0.00795   0.00140  -0.1035   0.6095   0.0390
  -1.750   0.2707   0.00791   0.00129  -0.1032   0.6012   0.0407
  -1.500   0.2976   0.00776   0.00117  -0.1030   0.5941   0.0576
  -1.250   0.3231   0.00749   0.00113  -0.1028   0.5875   0.1488
  -1.000   0.3504   0.00744   0.00110  -0.1027   0.5817   0.1634
  -0.750   0.3773   0.00741   0.00109  -0.1025   0.5762   0.1782
  -0.500   0.4042   0.00737   0.00109  -0.1024   0.5714   0.1973
  -0.250   0.4313   0.00729   0.00112  -0.1023   0.5666   0.2359
   0.000   0.4583   0.00729   0.00115  -0.1021   0.5618   0.2617
   0.250   0.4853   0.00731   0.00119  -0.1020   0.5571   0.2780
   0.500   0.5127   0.00730   0.00121  -0.1019   0.5520   0.2942
   0.750   0.5396   0.00731   0.00125  -0.1018   0.5472   0.3118
   1.000   0.5666   0.00732   0.00129  -0.1017   0.5431   0.3280
   1.250   0.5940   0.00730   0.00133  -0.1016   0.5395   0.3423
   1.500   0.6209   0.00727   0.00137  -0.1015   0.5357   0.3676
   1.750   0.6467   0.00713   0.00147  -0.1012   0.5321   0.4634
   2.000   0.6912   0.00604   0.00165  -0.1052   0.5275   0.9977
   2.250   0.7194   0.00610   0.00169  -0.1054   0.5209   1.0000
   2.500   0.7449   0.00620   0.00176  -0.1049   0.5166   1.0000
   2.750   0.7711   0.00625   0.00182  -0.1045   0.5087   1.0000
   3.000   0.7964   0.00636   0.00189  -0.1040   0.5010   1.0000
   3.250   0.8226   0.00642   0.00195  -0.1037   0.4913   1.0000
   3.500   0.8481   0.00652   0.00202  -0.1033   0.4780   1.0000
   3.750   0.8731   0.00666   0.00211  -0.1027   0.4607   1.0000
   4.000   0.8974   0.00685   0.00221  -0.1021   0.4330   1.0000
   4.250   0.9165   0.00745   0.00246  -0.1005   0.3606   1.0000
   4.500   0.9228   0.00916   0.00330  -0.0970   0.1900   1.0000
   4.750   0.9329   0.01060   0.00414  -0.0941   0.0498   1.0000
   5.000   0.9556   0.01098   0.00447  -0.0932   0.0354   1.0000
   5.250   0.9782   0.01136   0.00482  -0.0923   0.0272   1.0000
   5.500   1.0012   0.01168   0.00513  -0.0915   0.0229   1.0000
   5.750   1.0226   0.01214   0.00563  -0.0903   0.0192   1.0000
   6.000   1.0454   0.01246   0.00598  -0.0895   0.0174   1.0000
   6.250   1.0674   0.01283   0.00635  -0.0885   0.0155   1.0000
   6.500   1.0840   0.01360   0.00721  -0.0865   0.0137   1.0000
   6.750   1.1052   0.01399   0.00762  -0.0854   0.0131   1.0000
   7.000   1.1250   0.01444   0.00813  -0.0841   0.0123   1.0000
   7.250   1.1439   0.01493   0.00866  -0.0826   0.0115   1.0000
   7.500   1.1612   0.01549   0.00926  -0.0809   0.0110   1.0000
   7.750   1.1765   0.01613   0.00994  -0.0789   0.0103   1.0000
   8.000   1.1779   0.01739   0.01130  -0.0743   0.0097   1.0000
   8.250   1.1869   0.01812   0.01211  -0.0712   0.0092   1.0000
   8.500   1.1982   0.01879   0.01284  -0.0685   0.0090   1.0000
   8.750   1.2092   0.01951   0.01361  -0.0659   0.0086   1.0000
   9.000   1.2184   0.02040   0.01458  -0.0632   0.0083   1.0000
   9.250   1.2280   0.02131   0.01555  -0.0607   0.0080   1.0000
   9.500   1.2372   0.02232   0.01664  -0.0583   0.0078   1.0000
   9.750   1.2465   0.02340   0.01778  -0.0560   0.0075   1.0000
  10.000   1.2580   0.02429   0.01872  -0.0542   0.0072   1.0000
  10.250   1.2669   0.02557   0.02008  -0.0521   0.0072   1.0000
  10.500   1.2766   0.02677   0.02133  -0.0503   0.0069   1.0000
  10.750   1.2838   0.02851   0.02316  -0.0483   0.0066   1.0000
  11.000   1.2958   0.03246   0.02742  -0.0464   0.0063   1.0000
  11.250   1.3047   0.03340   0.02847  -0.0447   0.0062   1.0000
  11.500   1.3142   0.03489   0.03011  -0.0431   0.0060   1.0000
  11.750   1.3226   0.03678   0.03215  -0.0416   0.0058   1.0000
  12.000   1.3283   0.03950   0.03511  -0.0398   0.0057   1.0000
  12.250   1.3301   0.04261   0.03847  -0.0379   0.0054   1.0000
  12.500   1.3301   0.04529   0.04133  -0.0363   0.0053   1.0000
  13.000   1.2661   0.06302   0.06005  -0.0313   0.0056   1.0000
  13.250   1.2394   0.06933   0.06659  -0.0309   0.0057   1.0000
  13.500   1.2141   0.07547   0.07292  -0.0315   0.0058   1.0000
  13.750   1.1932   0.08161   0.07923  -0.0328   0.0058   1.0000
  14.000   1.1659   0.08868   0.08646  -0.0353   0.0059   1.0000
  14.250   1.1428   0.09584   0.09376  -0.0384   0.0060   1.0000
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