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GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 591 AIRFOIL (goe591-il)
Reynolds number: 1,000,000
Max Cl/Cd: 132.33 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe591-il-1000000.txt
Download as CSV file: xf-goe591-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 591 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3095   0.13383   0.13212  -0.0349   1.0000   0.0129
 -12.250  -0.3056   0.13091   0.12921  -0.0354   1.0000   0.0134
 -10.500  -0.5592   0.02725   0.02474  -0.1090   0.9754   0.0146
 -10.250  -0.5392   0.02263   0.01963  -0.1126   0.9721   0.0152
 -10.000  -0.5046   0.02218   0.01915  -0.1145   0.9704   0.0156
  -9.750  -0.4768   0.02239   0.01941  -0.1144   0.9638   0.0159
  -9.500  -0.4453   0.02195   0.01891  -0.1156   0.9592   0.0163
  -9.250  -0.4173   0.02116   0.01802  -0.1164   0.9526   0.0168
  -9.000  -0.3929   0.01998   0.01663  -0.1166   0.9435   0.0175
  -8.750  -0.3678   0.01943   0.01592  -0.1164   0.9330   0.0181
  -8.500  -0.3498   0.01753   0.01368  -0.1156   0.9199   0.0187
  -8.250  -0.3261   0.01687   0.01293  -0.1151   0.9071   0.0192
  -8.000  -0.3006   0.01667   0.01266  -0.1147   0.8934   0.0196
  -7.750  -0.2759   0.01639   0.01227  -0.1142   0.8794   0.0202
  -7.250  -0.2282   0.01544   0.01103  -0.1129   0.8544   0.0215
  -7.000  -0.2031   0.01519   0.01064  -0.1123   0.8440   0.0222
  -6.750  -0.1767   0.01528   0.01060  -0.1119   0.8345   0.0226
  -6.500  -0.1577   0.01333   0.00840  -0.1107   0.8250   0.0236
  -6.250  -0.1328   0.01291   0.00791  -0.1102   0.8170   0.0242
  -6.000  -0.1072   0.01261   0.00754  -0.1098   0.8088   0.0250
  -5.750  -0.0814   0.01231   0.00716  -0.1094   0.8012   0.0257
  -5.500  -0.0555   0.01199   0.00675  -0.1089   0.7935   0.0266
  -5.250  -0.0296   0.01164   0.00630  -0.1085   0.7865   0.0272
  -5.000  -0.0033   0.01136   0.00593  -0.1080   0.7787   0.0277
  -4.750   0.0235   0.01129   0.00577  -0.1077   0.7714   0.0280
  -4.500   0.0465   0.01008   0.00446  -0.1069   0.7640   0.0292
  -4.250   0.0721   0.00971   0.00403  -0.1064   0.7568   0.0300
  -4.000   0.0983   0.00941   0.00369  -0.1060   0.7488   0.0306
  -3.750   0.1243   0.00917   0.00339  -0.1055   0.7410   0.0314
  -3.500   0.1508   0.00895   0.00313  -0.1051   0.7327   0.0323
  -3.250   0.1771   0.00877   0.00289  -0.1047   0.7248   0.0331
  -3.000   0.2035   0.00858   0.00265  -0.1043   0.7159   0.0337
  -2.750   0.2300   0.00843   0.00244  -0.1039   0.7070   0.0342
  -2.500   0.2561   0.00829   0.00224  -0.1034   0.6975   0.0347
  -2.250   0.2823   0.00806   0.00195  -0.1030   0.6882   0.0363
  -2.000   0.3086   0.00793   0.00178  -0.1025   0.6785   0.0382
  -1.750   0.3349   0.00786   0.00166  -0.1021   0.6678   0.0402
  -1.500   0.3616   0.00779   0.00155  -0.1018   0.6572   0.0422
  -1.250   0.3878   0.00770   0.00147  -0.1013   0.6468   0.0508
  -1.000   0.4135   0.00762   0.00143  -0.1009   0.6355   0.0794
  -0.750   0.4400   0.00757   0.00139  -0.1005   0.6239   0.0943
  -0.500   0.4661   0.00753   0.00137  -0.1001   0.6122   0.1138
  -0.250   0.4917   0.00745   0.00137  -0.0997   0.6005   0.1580
   0.000   0.5173   0.00742   0.00139  -0.0992   0.5875   0.1980
   0.250   0.5426   0.00740   0.00140  -0.0987   0.5731   0.2326
   0.500   0.5671   0.00728   0.00143  -0.0981   0.5585   0.3100
   0.750   0.5898   0.00694   0.00150  -0.0972   0.5460   0.4855
   1.000   0.6029   0.00611   0.00161  -0.0942   0.5357   0.8251
   1.250   0.6577   0.00606   0.00177  -0.0999   0.5230   0.9780
   1.500   0.7154   0.00623   0.00184  -0.1065   0.5105   0.9967
   1.750   0.7534   0.00637   0.00189  -0.1088   0.4981   1.0000
   2.000   0.7764   0.00647   0.00194  -0.1078   0.4872   1.0000
   2.250   0.7991   0.00660   0.00200  -0.1067   0.4764   1.0000
   2.500   0.8216   0.00673   0.00207  -0.1056   0.4672   1.0000
   2.750   0.8452   0.00683   0.00214  -0.1047   0.4592   1.0000
   3.000   0.8681   0.00696   0.00222  -0.1037   0.4515   1.0000
   3.250   0.8919   0.00706   0.00230  -0.1028   0.4442   1.0000
   3.500   0.9149   0.00721   0.00240  -0.1018   0.4369   1.0000
   3.750   0.9389   0.00731   0.00249  -0.1011   0.4296   1.0000
   4.000   0.9618   0.00747   0.00260  -0.1001   0.4213   1.0000
   4.250   0.9858   0.00758   0.00269  -0.0993   0.4137   1.0000
   4.500   1.0088   0.00774   0.00282  -0.0984   0.4062   1.0000
   4.750   1.0329   0.00786   0.00293  -0.0976   0.3992   1.0000
   5.000   1.0558   0.00803   0.00306  -0.0967   0.3912   1.0000
   5.250   1.0798   0.00816   0.00319  -0.0960   0.3829   1.0000
   5.500   1.1026   0.00835   0.00333  -0.0950   0.3709   1.0000
   5.750   1.1249   0.00856   0.00349  -0.0940   0.3569   1.0000
   6.000   1.1472   0.00878   0.00366  -0.0930   0.3438   1.0000
   6.250   1.1692   0.00901   0.00385  -0.0920   0.3298   1.0000
   6.500   1.1906   0.00928   0.00405  -0.0909   0.3131   1.0000
   6.750   1.2108   0.00961   0.00428  -0.0895   0.2930   1.0000
   7.250   1.2494   0.01035   0.00485  -0.0866   0.2553   1.0000
   7.500   1.2681   0.01073   0.00515  -0.0851   0.2376   1.0000
   7.750   1.2864   0.01112   0.00547  -0.0835   0.2213   1.0000
   8.000   1.3031   0.01157   0.00583  -0.0816   0.2032   1.0000
   8.250   1.3176   0.01204   0.00620  -0.0793   0.1836   1.0000
   8.500   1.3248   0.01278   0.00673  -0.0758   0.1495   1.0000
   8.750   1.3321   0.01354   0.00733  -0.0724   0.1235   1.0000
   9.000   1.3401   0.01431   0.00796  -0.0691   0.1010   1.0000
   9.250   1.3377   0.01559   0.00896  -0.0645   0.0583   1.0000
   9.500   1.3323   0.01710   0.01026  -0.0595   0.0223   1.0000
   9.750   1.3420   0.01790   0.01105  -0.0570   0.0170   1.0000
  10.000   1.3541   0.01860   0.01179  -0.0549   0.0156   1.0000
  10.250   1.3639   0.01945   0.01269  -0.0527   0.0141   1.0000
  10.500   1.3752   0.02025   0.01354  -0.0507   0.0134   1.0000
  10.750   1.3871   0.02103   0.01439  -0.0489   0.0129   1.0000
  11.000   1.3972   0.02197   0.01538  -0.0470   0.0122   1.0000
  11.250   1.4062   0.02302   0.01649  -0.0452   0.0119   1.0000
  11.500   1.4137   0.02422   0.01775  -0.0433   0.0113   1.0000
  11.750   1.4166   0.02581   0.01942  -0.0412   0.0108   1.0000
  12.000   1.4191   0.02752   0.02123  -0.0392   0.0105   1.0000
  12.250   1.4283   0.02877   0.02255  -0.0380   0.0103   1.0000
  12.500   1.4349   0.03028   0.02413  -0.0366   0.0101   1.0000
  12.750   1.4417   0.03183   0.02574  -0.0355   0.0097   1.0000
  13.000   1.4452   0.03372   0.02771  -0.0343   0.0095   1.0000
  13.250   1.4496   0.03558   0.02964  -0.0333   0.0092   1.0000
  13.500   1.4513   0.03779   0.03193  -0.0323   0.0090   1.0000
  13.750   1.4532   0.04005   0.03425  -0.0315   0.0087   1.0000
  14.000   1.4510   0.04282   0.03710  -0.0308   0.0085   1.0000
  14.250   1.4467   0.04594   0.04032  -0.0303   0.0083   1.0000
  14.500   1.4360   0.04993   0.04442  -0.0299   0.0082   1.0000
  14.750   1.4227   0.05439   0.04900  -0.0298   0.0080   1.0000
  15.000   1.4172   0.05806   0.05278  -0.0300   0.0079   1.0000
  15.250   1.4137   0.06158   0.05638  -0.0303   0.0079   1.0000
  15.500   1.4143   0.06464   0.05953  -0.0306   0.0078   1.0000
  15.750   1.4113   0.06823   0.06321  -0.0310   0.0077   1.0000
  16.000   1.4071   0.07207   0.06713  -0.0317   0.0076   1.0000
  16.250   1.4012   0.07619   0.07135  -0.0324   0.0075   1.0000
  16.500   1.3961   0.08027   0.07551  -0.0333   0.0074   1.0000
  16.750   1.3903   0.08453   0.07987  -0.0343   0.0073   1.0000
  17.000   1.3852   0.08875   0.08417  -0.0354   0.0072   1.0000
  17.250   1.3802   0.09302   0.08853  -0.0365   0.0071   1.0000
  17.500   1.3740   0.09750   0.09310  -0.0378   0.0070   1.0000
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