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GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 484 AIRFOIL (goe484-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.73 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe484-il-1000000-n5.txt
Download as CSV file: xf-goe484-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 484 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3343   0.10186   0.10009  -0.0456   0.9944   0.0092
  -9.750  -0.3240   0.09843   0.09665  -0.0482   0.9926   0.0097
  -9.500  -0.3217   0.09212   0.09035  -0.0527   0.9901   0.0109
  -9.250  -0.3064   0.08932   0.08755  -0.0558   0.9881   0.0111
  -9.000  -0.2904   0.08632   0.08454  -0.0592   0.9863   0.0113
  -8.750  -0.2776   0.08372   0.08194  -0.0616   0.9825   0.0115
  -8.500  -0.2641   0.08052   0.07874  -0.0649   0.9790   0.0118
  -8.250  -0.2487   0.07718   0.07539  -0.0689   0.9761   0.0124
  -7.750  -0.2214   0.06625   0.06443  -0.0829   0.9627   0.0142
  -7.500  -0.1938   0.06317   0.06133  -0.0892   0.9588   0.0144
  -7.250  -0.1656   0.05984   0.05797  -0.0958   0.9546   0.0148
  -7.000  -0.1380   0.05608   0.05418  -0.1028   0.9471   0.0153
  -6.750  -0.1080   0.04301   0.04091  -0.1227   0.9309   0.0175
  -6.500  -0.0822   0.03792   0.03568  -0.1297   0.9199   0.0179
  -6.250  -0.0570   0.03505   0.03271  -0.1331   0.9104   0.0182
  -6.000  -0.0313   0.03236   0.02989  -0.1359   0.9014   0.0185
  -5.750  -0.0107   0.01765   0.01420  -0.1443   0.8882   0.0198
  -5.500   0.0138   0.01552   0.01169  -0.1447   0.8809   0.0204
  -5.250   0.0393   0.01415   0.01004  -0.1448   0.8745   0.0209
  -5.000   0.0652   0.01319   0.00887  -0.1448   0.8674   0.0213
  -4.500   0.1179   0.01197   0.00731  -0.1445   0.8539   0.0217
  -4.250   0.1444   0.01146   0.00666  -0.1443   0.8472   0.0218
  -4.000   0.1711   0.01105   0.00614  -0.1441   0.8414   0.0219
  -3.750   0.1979   0.01066   0.00564  -0.1439   0.8355   0.0220
  -3.500   0.2244   0.01008   0.00494  -0.1437   0.8302   0.0222
  -3.250   0.2509   0.00938   0.00413  -0.1435   0.8252   0.0223
  -3.000   0.2775   0.00885   0.00352  -0.1433   0.8194   0.0225
  -2.500   0.3311   0.00819   0.00278  -0.1429   0.8084   0.0232
  -2.250   0.3581   0.00794   0.00250  -0.1426   0.8026   0.0234
  -2.000   0.3850   0.00773   0.00224  -0.1423   0.7971   0.0236
  -1.750   0.4121   0.00753   0.00203  -0.1421   0.7907   0.0239
  -1.500   0.4389   0.00738   0.00185  -0.1418   0.7838   0.0243
  -1.250   0.4660   0.00723   0.00168  -0.1416   0.7760   0.0247
  -1.000   0.4926   0.00713   0.00154  -0.1412   0.7667   0.0252
  -0.750   0.5190   0.00705   0.00142  -0.1408   0.7537   0.0257
  -0.500   0.5446   0.00701   0.00132  -0.1402   0.7321   0.0262
  -0.250   0.5658   0.00721   0.00125  -0.1386   0.6708   0.0266
   0.250   0.6118   0.00759   0.00127  -0.1365   0.5930   0.0272
   0.500   0.6375   0.00765   0.00126  -0.1360   0.5762   0.0275
   0.750   0.6633   0.00771   0.00126  -0.1355   0.5603   0.0277
   1.000   0.6887   0.00781   0.00129  -0.1349   0.5409   0.0280
   1.250   0.7142   0.00788   0.00129  -0.1344   0.5226   0.0290
   1.500   0.7391   0.00802   0.00132  -0.1337   0.4947   0.0300
   1.750   0.7632   0.00823   0.00138  -0.1329   0.4575   0.0314
   2.000   0.7816   0.00893   0.00162  -0.1312   0.3501   0.0333
   2.500   0.8239   0.00991   0.00215  -0.1288   0.2165   0.1051
   3.000   0.8635   0.01125   0.00292  -0.1260   0.0469   0.1746
   3.250   0.8881   0.01109   0.00317  -0.1256   0.0424   0.3942
   3.750   0.9398   0.01041   0.00370  -0.1251   0.0367   1.0000
   4.000   0.9650   0.01061   0.00389  -0.1245   0.0358   1.0000
   4.250   0.9899   0.01082   0.00409  -0.1239   0.0349   1.0000
   4.500   1.0147   0.01104   0.00431  -0.1233   0.0338   1.0000
   4.750   1.0392   0.01128   0.00454  -0.1227   0.0326   1.0000
   5.000   1.0635   0.01154   0.00479  -0.1220   0.0316   1.0000
   5.250   1.0873   0.01183   0.00508  -0.1212   0.0304   1.0000
   5.500   1.1105   0.01218   0.00545  -0.1203   0.0289   1.0000
   5.750   1.1336   0.01253   0.00583  -0.1194   0.0280   1.0000
   6.000   1.1576   0.01276   0.00606  -0.1187   0.0277   1.0000
   6.250   1.1814   0.01301   0.00632  -0.1179   0.0272   1.0000
   6.500   1.2049   0.01327   0.00661  -0.1171   0.0265   1.0000
   6.750   1.2282   0.01354   0.00689  -0.1163   0.0256   1.0000
   7.000   1.2512   0.01382   0.00719  -0.1155   0.0247   1.0000
   7.250   1.2741   0.01410   0.00746  -0.1146   0.0236   1.0000
   7.500   1.2964   0.01442   0.00779  -0.1137   0.0224   1.0000
   7.750   1.3170   0.01487   0.00825  -0.1124   0.0211   1.0000
   8.000   1.3396   0.01514   0.00854  -0.1115   0.0206   1.0000
   8.250   1.3617   0.01542   0.00884  -0.1106   0.0196   1.0000
   8.500   1.3834   0.01571   0.00915  -0.1095   0.0182   1.0000
   8.750   1.4045   0.01604   0.00947  -0.1084   0.0167   1.0000
   9.000   1.4245   0.01644   0.00988  -0.1071   0.0154   1.0000
   9.250   1.4437   0.01685   0.01031  -0.1057   0.0143   1.0000
   9.500   1.4615   0.01727   0.01073  -0.1040   0.0129   1.0000
   9.750   1.4779   0.01775   0.01122  -0.1020   0.0116   1.0000
  10.000   1.4940   0.01823   0.01176  -0.1001   0.0110   1.0000
  10.250   1.5094   0.01875   0.01232  -0.0980   0.0103   1.0000
  10.500   1.5243   0.01932   0.01293  -0.0959   0.0096   1.0000
  10.750   1.5382   0.01996   0.01360  -0.0937   0.0090   1.0000
  11.000   1.5515   0.02065   0.01434  -0.0915   0.0084   1.0000
  11.250   1.5653   0.02129   0.01507  -0.0894   0.0082   1.0000
  11.500   1.5786   0.02199   0.01583  -0.0873   0.0078   1.0000
  11.750   1.5910   0.02275   0.01665  -0.0851   0.0075   1.0000
  12.000   1.6029   0.02356   0.01753  -0.0830   0.0072   1.0000
  12.250   1.6139   0.02445   0.01848  -0.0808   0.0068   1.0000
  12.500   1.6241   0.02543   0.01951  -0.0786   0.0065   1.0000
  12.750   1.6319   0.02662   0.02079  -0.0762   0.0061   1.0000
  13.000   1.6426   0.02760   0.02185  -0.0743   0.0060   1.0000
  13.250   1.6520   0.02870   0.02304  -0.0723   0.0058   1.0000
  13.500   1.6604   0.02991   0.02434  -0.0703   0.0057   1.0000
  13.750   1.6684   0.03119   0.02571  -0.0684   0.0055   1.0000
  14.000   1.6752   0.03260   0.02721  -0.0665   0.0054   1.0000
  14.250   1.6817   0.03408   0.02879  -0.0647   0.0052   1.0000
  14.500   1.6874   0.03567   0.03047  -0.0630   0.0051   1.0000
  14.750   1.6919   0.03743   0.03234  -0.0613   0.0050   1.0000
  15.000   1.6955   0.03933   0.03433  -0.0598   0.0049   1.0000
  15.250   1.6984   0.04136   0.03647  -0.0583   0.0047   1.0000
  15.500   1.6994   0.04366   0.03887  -0.0570   0.0046   1.0000
  15.750   1.6989   0.04621   0.04153  -0.0559   0.0045   1.0000
  16.000   1.6965   0.04910   0.04454  -0.0549   0.0044   1.0000
  16.250   1.6914   0.05245   0.04803  -0.0542   0.0042   1.0000
  16.500   1.6878   0.05578   0.05148  -0.0539   0.0042   1.0000
  16.750   1.6848   0.05919   0.05503  -0.0539   0.0042   1.0000
  17.000   1.6793   0.06308   0.05906  -0.0542   0.0041   1.0000
  17.250   1.6745   0.06706   0.06317  -0.0548   0.0041   1.0000
  17.500   1.6671   0.07162   0.06787  -0.0558   0.0041   1.0000
  17.750   1.6577   0.07666   0.07306  -0.0572   0.0040   1.0000
  18.000   1.6479   0.08194   0.07848  -0.0589   0.0040   1.0000
  18.250   1.6352   0.08794   0.08465  -0.0612   0.0040   1.0000
  18.500   1.6205   0.09455   0.09141  -0.0640   0.0040   1.0000
  18.750   1.6041   0.10174   0.09875  -0.0674   0.0039   1.0000
  19.000   1.5846   0.10991   0.10709  -0.0716   0.0039   1.0000
  19.250   1.5627   0.11905   0.11640  -0.0767   0.0039   1.0000
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