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GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il)
Reynolds number: 500,000
Max Cl/Cd: 112.3 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe118-il-500000.txt
Download as CSV file: xf-goe118-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 118 (MVA MK.7) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2752   0.10388   0.10178  -0.0369   1.0000   0.0098
  -8.750  -0.2701   0.10093   0.09886  -0.0380   1.0000   0.0104
  -8.500  -0.2662   0.09814   0.09611  -0.0388   1.0000   0.0111
  -8.250  -0.2604   0.09537   0.09335  -0.0405   0.9982   0.0119
  -8.000  -0.2386   0.09171   0.08969  -0.0475   0.9870   0.0126
  -7.750  -0.2180   0.08783   0.08581  -0.0534   0.9713   0.0128
  -7.500  -0.2016   0.08390   0.08186  -0.0581   0.9492   0.0128
  -7.250  -0.1893   0.08031   0.07822  -0.0615   0.9242   0.0129
  -7.000  -0.1771   0.07676   0.07458  -0.0648   0.9008   0.0129
  -6.750  -0.1629   0.07306   0.07079  -0.0687   0.8796   0.0129
  -6.500  -0.1462   0.06918   0.06681  -0.0731   0.8615   0.0129
  -6.250  -0.1332   0.06219   0.05975  -0.0800   0.8456   0.0134
  -6.000  -0.1151   0.05747   0.05493  -0.0851   0.8313   0.0139
  -5.250  -0.0435   0.04665   0.04377  -0.0980   0.7951   0.0156
  -5.000  -0.0143   0.04255   0.03951  -0.1030   0.7852   0.0164
  -4.750   0.0170   0.03813   0.03490  -0.1078   0.7763   0.0175
  -4.500   0.0496   0.03341   0.02993  -0.1121   0.7677   0.0190
  -4.250   0.0839   0.03002   0.02628  -0.1142   0.7595   0.0220
  -4.000   0.1154   0.02577   0.02156  -0.1165   0.7523   0.0224
  -3.250   0.2028   0.01362   0.00766  -0.1197   0.7306   0.0178
  -3.000   0.2309   0.01297   0.00679  -0.1197   0.7236   0.0203
  -2.750   0.2596   0.01181   0.00540  -0.1197   0.7160   0.0195
  -2.500   0.2879   0.01098   0.00436  -0.1196   0.7092   0.0192
  -2.250   0.3163   0.01036   0.00359  -0.1196   0.7017   0.0201
  -2.000   0.3445   0.00998   0.00309  -0.1196   0.6946   0.0219
  -1.750   0.3728   0.00955   0.00252  -0.1196   0.6866   0.0265
  -1.500   0.4011   0.00928   0.00211  -0.1196   0.6787   0.0332
  -1.250   0.4289   0.00915   0.00211  -0.1196   0.6710   0.0937
  -1.000   0.4569   0.00925   0.00219  -0.1198   0.6632   0.1079
  -0.500   0.5126   0.00928   0.00214  -0.1200   0.6492   0.1224
   0.000   0.5684   0.00917   0.00198  -0.1202   0.6357   0.1327
   0.500   0.6241   0.00907   0.00187  -0.1205   0.6217   0.1460
   0.750   0.6517   0.00902   0.00183  -0.1205   0.6138   0.1627
   1.000   0.6790   0.00844   0.00193  -0.1210   0.6052   0.4261
   1.250   0.7025   0.00726   0.00199  -0.1202   0.5975   1.0000
   1.500   0.7300   0.00737   0.00201  -0.1202   0.5898   1.0000
   1.750   0.7577   0.00745   0.00206  -0.1202   0.5818   1.0000
   2.000   0.7850   0.00758   0.00211  -0.1202   0.5747   1.0000
   2.250   0.8126   0.00766   0.00220  -0.1203   0.5671   1.0000
   2.500   0.8399   0.00779   0.00229  -0.1203   0.5602   1.0000
   2.750   0.8667   0.00791   0.00236  -0.1203   0.5480   1.0000
   3.000   0.8934   0.00804   0.00245  -0.1202   0.5332   1.0000
   3.250   0.9197   0.00819   0.00254  -0.1200   0.5122   1.0000
   3.500   0.9452   0.00842   0.00269  -0.1197   0.4852   1.0000
   3.750   0.9694   0.00878   0.00287  -0.1193   0.4438   1.0000
   4.000   0.9817   0.01048   0.00360  -0.1172   0.2785   1.0000
   4.250   0.9867   0.01320   0.00520  -0.1140   0.0286   1.0000
   4.500   1.0111   0.01361   0.00572  -0.1135   0.0240   1.0000
   4.750   1.0342   0.01416   0.00639  -0.1127   0.0205   1.0000
   5.000   1.0540   0.01506   0.00743  -0.1114   0.0172   1.0000
   5.250   1.0688   0.01639   0.00891  -0.1093   0.0159   1.0000
   5.500   1.0888   0.01711   0.00971  -0.1080   0.0151   1.0000
   5.750   1.1042   0.01820   0.01089  -0.1060   0.0147   1.0000
   6.000   1.1162   0.01951   0.01228  -0.1035   0.0147   1.0000
   6.250   1.1315   0.02050   0.01333  -0.1015   0.0138   1.0000
   6.500   1.1459   0.02153   0.01441  -0.0995   0.0127   1.0000
   6.750   1.1574   0.02292   0.01589  -0.0969   0.0123   1.0000
   7.000   1.1711   0.02458   0.01760  -0.0944   0.0124   1.0000
   7.750   1.2833   0.03787   0.03098  -0.0975   0.0159   1.0000
   8.000   1.3021   0.03988   0.03321  -0.0960   0.0158   1.0000
   8.250   1.3162   0.03993   0.03349  -0.0936   0.0154   1.0000
   8.500   1.3319   0.03944   0.03319  -0.0913   0.0139   1.0000
   8.750   1.3482   0.04080   0.03477  -0.0894   0.0123   1.0000
   9.000   1.3617   0.04276   0.03689  -0.0878   0.0110   1.0000
   9.250   1.3747   0.04528   0.03953  -0.0863   0.0103   1.0000
   9.500   1.3887   0.04844   0.04279  -0.0852   0.0098   1.0000
   9.750   1.3969   0.05354   0.04805  -0.0837   0.0093   1.0000
  10.000   1.3814   0.06403   0.05901  -0.0798   0.0087   1.0000
  10.250   1.3763   0.06715   0.06239  -0.0763   0.0087   1.0000
  10.500   1.3684   0.07019   0.06565  -0.0727   0.0087   1.0000
  10.750   1.3561   0.07301   0.06869  -0.0689   0.0087   1.0000
  11.000   1.3396   0.07557   0.07143  -0.0647   0.0087   1.0000
  11.250   1.3214   0.07834   0.07436  -0.0611   0.0087   1.0000
  11.500   1.3026   0.08143   0.07761  -0.0585   0.0087   1.0000
  11.750   1.2838   0.08488   0.08123  -0.0566   0.0087   1.0000
  12.000   1.2645   0.08869   0.08520  -0.0556   0.0086   1.0000
  12.250   1.2452   0.09287   0.08952  -0.0552   0.0086   1.0000
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