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GOE 527 AIRFOIL (goe527-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 527 AIRFOIL (goe527-il)
Reynolds number: 100,000
Max Cl/Cd: 36.4 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe527-il-100000.txt
Download as CSV file: xf-goe527-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 527 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1010   0.09953   0.09491  -0.0819   0.9431   0.1375
  -9.000  -0.0584   0.09541   0.09074  -0.0841   0.9400   0.1425
  -8.750  -0.0823   0.09285   0.08821  -0.0962   0.9256   0.1513
  -8.500  -0.0327   0.08708   0.08239  -0.0965   0.9244   0.1542
  -8.250   0.0076   0.08320   0.07846  -0.1000   0.9213   0.1600
  -8.000  -0.0682   0.08163   0.07691  -0.1109   0.8928   0.1682
  -7.750   0.0342   0.07630   0.07154  -0.1075   0.9009   0.1738
  -7.500   0.0128   0.07401   0.06923  -0.1130   0.8847   0.1842
  -7.250   0.0248   0.07080   0.06603  -0.1118   0.8730   0.1883
  -7.000   0.0623   0.06794   0.06310  -0.1131   0.8677   0.1965
  -6.750   0.0236   0.06552   0.06066  -0.1150   0.8506   0.2054
  -6.500   0.0496   0.06370   0.05885  -0.1123   0.8417   0.2096
  -6.250  -0.0549   0.04648   0.04029  -0.1196   0.8227   0.1223
  -6.000  -0.0361   0.04339   0.03701  -0.1193   0.8152   0.1179
  -5.750  -0.0243   0.04054   0.03381  -0.1181   0.8073   0.1167
  -5.500  -0.0137   0.03831   0.03120  -0.1162   0.7980   0.1168
  -5.250   0.0121   0.03559   0.02798  -0.1163   0.7933   0.1175
  -5.000   0.0180   0.03457   0.02668  -0.1131   0.7822   0.1181
  -4.750   0.0446   0.03284   0.02439  -0.1127   0.7768   0.1205
  -4.500   0.0623   0.03156   0.02304  -0.1113   0.7689   0.1242
  -4.250   0.0848   0.03075   0.02215  -0.1103   0.7613   0.1289
  -4.000   0.1174   0.02948   0.02046  -0.1105   0.7569   0.1348
  -3.750   0.1297   0.02903   0.02004  -0.1083   0.7480   0.1400
  -3.500   0.1566   0.02838   0.01924  -0.1078   0.7419   0.1486
  -3.250   0.1912   0.02728   0.01809  -0.1085   0.7379   0.1590
  -3.000   0.2010   0.02757   0.01829  -0.1057   0.7286   0.1670
  -2.750   0.2285   0.02697   0.01776  -0.1055   0.7232   0.1785
  -2.500   0.2627   0.02625   0.01701  -0.1061   0.7195   0.1927
  -2.250   0.2706   0.02679   0.01752  -0.1030   0.7104   0.2023
  -2.000   0.2976   0.02635   0.01718  -0.1027   0.7050   0.2171
  -1.750   0.3311   0.02573   0.01660  -0.1031   0.7014   0.2367
  -1.500   0.3373   0.02631   0.01733  -0.1000   0.6933   0.2515
  -1.250   0.3590   0.02608   0.01728  -0.0988   0.6875   0.2834
  -1.000   0.3872   0.02491   0.01689  -0.0984   0.6838   0.4238
  -0.750   0.3991   0.02438   0.01742  -0.0948   0.6786   0.6812
  -0.500   0.5575   0.02383   0.01710  -0.1175   0.6732   1.0000
  -0.250   0.5753   0.02405   0.01713  -0.1159   0.6679   1.0000
   0.000   0.6042   0.02401   0.01684  -0.1158   0.6642   1.0000
   0.250   0.5932   0.02544   0.01827  -0.1102   0.6559   1.0000
   0.500   0.6114   0.02580   0.01850  -0.1086   0.6504   1.0000
   0.750   0.6448   0.02565   0.01815  -0.1090   0.6468   1.0000
   1.000   0.6353   0.02718   0.01968  -0.1037   0.6387   1.0000
   1.250   0.6497   0.02775   0.02016  -0.1015   0.6327   1.0000
   1.500   0.6877   0.02742   0.01966  -0.1025   0.6292   1.0000
   1.750   0.6792   0.02900   0.02124  -0.0974   0.6211   1.0000
   2.000   0.6936   0.02957   0.02174  -0.0953   0.6145   1.0000
   2.250   0.7420   0.02871   0.02069  -0.0975   0.6112   1.0000
   2.500   0.7266   0.03055   0.02256  -0.0916   0.6015   1.0000
   2.750   0.7608   0.03017   0.02208  -0.0919   0.5961   1.0000
   3.000   0.8135   0.02908   0.02081  -0.0947   0.5927   1.0000
   3.250   0.7888   0.03135   0.02316  -0.0876   0.5824   1.0000
   3.500   0.8272   0.03087   0.02258  -0.0885   0.5778   1.0000
   3.750   0.8778   0.02996   0.02152  -0.0911   0.5747   1.0000
   4.000   0.8437   0.03268   0.02435  -0.0830   0.5636   1.0000
   4.250   0.8878   0.03197   0.02356  -0.0847   0.5597   1.0000
   4.500   0.9397   0.03103   0.02249  -0.0874   0.5567   1.0000
   4.750   0.8940   0.03427   0.02586  -0.0780   0.5448   1.0000
   5.000   0.9479   0.03310   0.02460  -0.0808   0.5414   1.0000
   5.250   1.0083   0.03176   0.02312  -0.0846   0.5384   1.0000
   5.500   0.9548   0.03514   0.02665  -0.0742   0.5261   1.0000
   5.750   1.0194   0.03355   0.02497  -0.0783   0.5229   1.0000
   6.000   1.0847   0.03213   0.02340  -0.0829   0.5199   1.0000
   6.250   1.0231   0.03563   0.02709  -0.0712   0.5075   1.0000
   6.500   1.0923   0.03398   0.02535  -0.0762   0.5042   1.0000
   6.750   1.0238   0.03806   0.02955  -0.0644   0.4917   1.0000
   7.000   1.0929   0.03605   0.02748  -0.0686   0.4885   1.0000
   7.250   1.1780   0.03388   0.02518  -0.0757   0.4852   1.0000
   7.500   1.0994   0.03804   0.02950  -0.0624   0.4727   1.0000
   7.750   1.1841   0.03546   0.02682  -0.0686   0.4693   1.0000
   8.000   1.1098   0.04012   0.03163  -0.0573   0.4570   1.0000
   8.250   1.1789   0.03783   0.02927  -0.0609   0.4535   1.0000
   8.500   1.2789   0.03513   0.02642  -0.0696   0.4500   1.0000
   8.750   1.1674   0.04122   0.03276  -0.0541   0.4374   1.0000
   9.000   1.2674   0.03738   0.02879  -0.0607   0.4345   1.0000
   9.250   1.1450   0.04611   0.03774  -0.0480   0.4203   1.0000
   9.500   1.2605   0.03997   0.03147  -0.0538   0.4190   1.0000
   9.750   1.0618   0.05843   0.05017  -0.0425   0.3969   1.0000
  10.000   1.1265   0.05389   0.04561  -0.0424   0.3963   1.0000
  10.250   1.2120   0.04807   0.03975  -0.0438   0.3950   1.0000
  10.500   1.1192   0.05930   0.05109  -0.0400   0.3807   1.0000
  10.750   1.1937   0.05362   0.04538  -0.0401   0.3793   1.0000
  11.000   1.1101   0.06528   0.05713  -0.0381   0.3650   1.0000
  11.250   1.1752   0.06017   0.05203  -0.0375   0.3643   1.0000
  11.500   1.2575   0.05421   0.04604  -0.0380   0.3638   1.0000
  11.750   1.1472   0.06904   0.06100  -0.0362   0.3498   1.0000
  12.000   1.2134   0.06384   0.05580  -0.0355   0.3495   1.0000
  12.250   1.3079   0.05650   0.04843  -0.0360   0.3490   1.0000
  13.000   1.3908   0.05572   0.04772  -0.0349   0.3343   1.0000
  13.250   0.9245   0.12317   0.11550  -0.0451   0.2874   1.0000
  13.500   0.8771   0.13447   0.12685  -0.0489   0.2757   1.0000
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