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GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il)
Reynolds number: 200,000
Max Cl/Cd: 83.14 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe118-il-200000.txt
Download as CSV file: xf-goe118-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2667   0.09880   0.09565  -0.0388   1.0000   0.0270
  -8.000  -0.2696   0.09687   0.09381  -0.0378   1.0000   0.0277
  -7.750  -0.2854   0.09639   0.09344  -0.0340   1.0000   0.0279
  -7.500  -0.2712   0.09281   0.08989  -0.0384   0.9948   0.0291
  -7.250  -0.2482   0.08832   0.08539  -0.0453   0.9862   0.0306
  -7.000  -0.2205   0.08349   0.08055  -0.0544   0.9764   0.0326
  -6.750  -0.1790   0.07836   0.07538  -0.0716   0.9644   0.0345
  -6.500  -0.1401   0.07320   0.07015  -0.0836   0.9553   0.0349
  -6.250  -0.1328   0.06782   0.06480  -0.0825   0.9452   0.0367
  -6.000  -0.1114   0.06466   0.06160  -0.0847   0.9338   0.0392
  -5.750  -0.0853   0.06079   0.05765  -0.0906   0.9207   0.0429
  -5.500  -0.0451   0.05434   0.05100  -0.1045   0.9066   0.0477
  -5.250  -0.0337   0.05263   0.04930  -0.1017   0.8948   0.0505
  -5.000   0.0070   0.04733   0.04368  -0.1122   0.8827   0.0592
  -4.750   0.0198   0.04562   0.04196  -0.1098   0.8720   0.0623
  -4.500   0.0561   0.04128   0.03728  -0.1163   0.8616   0.0720
  -4.250   0.0746   0.03940   0.03539  -0.1154   0.8506   0.0770
  -4.000   0.1048   0.03610   0.03184  -0.1185   0.8407   0.0875
  -3.750   0.1337   0.03319   0.02868  -0.1202   0.8320   0.0918
  -3.500   0.1817   0.01934   0.01299  -0.1253   0.8253   0.0388
  -3.250   0.2113   0.01792   0.01102  -0.1248   0.8169   0.0351
  -3.000   0.2394   0.01605   0.00875  -0.1246   0.8083   0.0342
  -2.750   0.2673   0.01485   0.00729  -0.1243   0.7993   0.0343
  -2.500   0.2952   0.01391   0.00614  -0.1240   0.7916   0.0355
  -2.250   0.3227   0.01313   0.00521  -0.1239   0.7826   0.0434
  -2.000   0.3507   0.01270   0.00474  -0.1236   0.7743   0.0536
  -1.750   0.3788   0.01274   0.00480  -0.1233   0.7666   0.1061
  -1.500   0.4065   0.01320   0.00510  -0.1233   0.7576   0.1364
  -1.250   0.4338   0.01322   0.00499  -0.1232   0.7500   0.1480
  -1.000   0.4609   0.01328   0.00496  -0.1232   0.7414   0.1649
  -0.750   0.4879   0.01310   0.00479  -0.1231   0.7332   0.1739
  -0.500   0.5153   0.01298   0.00455  -0.1230   0.7256   0.1780
  -0.250   0.5422   0.01279   0.00440  -0.1229   0.7166   0.1839
   0.000   0.5696   0.01269   0.00425  -0.1228   0.7093   0.1937
   0.250   0.5968   0.01253   0.00417  -0.1228   0.7011   0.2134
   0.500   0.6207   0.01068   0.00419  -0.1221   0.6943   1.0000
   0.750   0.6483   0.01081   0.00413  -0.1219   0.6867   1.0000
   1.000   0.6755   0.01096   0.00417  -0.1219   0.6795   1.0000
   1.250   0.7029   0.01110   0.00419  -0.1218   0.6724   1.0000
   1.500   0.7301   0.01125   0.00428  -0.1218   0.6651   1.0000
   1.750   0.7574   0.01139   0.00434  -0.1217   0.6583   1.0000
   2.000   0.7844   0.01155   0.00447  -0.1217   0.6508   1.0000
   2.250   0.8117   0.01169   0.00458  -0.1216   0.6442   1.0000
   2.500   0.8384   0.01184   0.00474  -0.1215   0.6360   1.0000
   2.750   0.8658   0.01199   0.00481  -0.1214   0.6292   1.0000
   3.000   0.8921   0.01212   0.00500  -0.1212   0.6201   1.0000
   3.250   0.9188   0.01226   0.00515  -0.1210   0.6118   1.0000
   3.500   0.9437   0.01219   0.00510  -0.1203   0.5948   1.0000
   3.750   0.9682   0.01213   0.00495  -0.1194   0.5749   1.0000
   4.000   0.9911   0.01209   0.00487  -0.1183   0.5451   1.0000
   4.250   1.0135   0.01219   0.00488  -0.1172   0.5088   1.0000
   4.500   1.0311   0.01269   0.00501  -0.1152   0.4274   1.0000
   4.750   1.0315   0.01520   0.00613  -0.1113   0.1979   1.0000
   5.000   1.0367   0.01763   0.00780  -0.1082   0.0406   1.0000
   5.250   1.0577   0.01833   0.00869  -0.1069   0.0358   1.0000
   5.500   1.0768   0.01918   0.00975  -0.1054   0.0329   1.0000
   5.750   1.0903   0.02045   0.01123  -0.1033   0.0289   1.0000
   6.000   1.0994   0.02195   0.01290  -0.1005   0.0278   1.0000
   6.250   1.1051   0.02360   0.01465  -0.0973   0.0273   1.0000
   6.500   1.1101   0.02518   0.01629  -0.0938   0.0272   1.0000
   6.750   1.1176   0.02663   0.01779  -0.0908   0.0274   1.0000
   7.000   1.1301   0.02790   0.01916  -0.0884   0.0281   1.0000
   7.250   1.1474   0.02909   0.02045  -0.0863   0.0299   1.0000
   7.500   1.1694   0.03119   0.02251  -0.0852   0.0285   1.0000
   9.500   1.3920   0.05553   0.04866  -0.0805   0.0358   1.0000
   9.750   1.3927   0.05708   0.05061  -0.0768   0.0333   1.0000
  10.000   1.3945   0.05998   0.05379  -0.0740   0.0313   1.0000
  10.250   1.3947   0.06334   0.05735  -0.0715   0.0297   1.0000
  10.500   1.4096   0.07094   0.06486  -0.0724   0.0274   1.0000
  10.750   1.3889   0.08171   0.07595  -0.0701   0.0264   1.0000
  11.000   1.3743   0.08387   0.07840  -0.0662   0.0264   1.0000
  11.250   1.3550   0.08569   0.08045  -0.0619   0.0263   1.0000
  11.500   1.3334   0.08764   0.08261  -0.0579   0.0262   1.0000
  11.750   1.3123   0.09017   0.08533  -0.0551   0.0261   1.0000
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