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GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
Reynolds number: 500,000
Max Cl/Cd: 79.63 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe280-il-500000-n5.txt
Download as CSV file: xf-goe280-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 280 (DAIMLER XI) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3323   0.10445   0.10229  -0.0212   1.0000   0.0084
  -8.500  -0.3270   0.10120   0.09907  -0.0226   1.0000   0.0084
  -8.250  -0.3226   0.09804   0.09594  -0.0237   1.0000   0.0084
  -8.000  -0.2083   0.07731   0.07535  -0.0355   0.9840   0.0079
  -7.750  -0.2015   0.07329   0.07132  -0.0377   0.9778   0.0074
  -7.250  -0.2904   0.08417   0.08214  -0.0323   0.9844   0.0075
  -7.000  -0.2720   0.07951   0.07747  -0.0385   0.9769   0.0069
  -6.750  -0.2531   0.07428   0.07222  -0.0453   0.9677   0.0064
  -6.500  -0.2325   0.06880   0.06671  -0.0523   0.9581   0.0061
  -6.250  -0.2108   0.06432   0.06217  -0.0578   0.9492   0.0062
  -6.000  -0.1885   0.06010   0.05789  -0.0626   0.9396   0.0063
  -5.750  -0.1651   0.05597   0.05367  -0.0671   0.9303   0.0065
  -5.500  -0.1399   0.05194   0.04954  -0.0711   0.9224   0.0068
  -5.250  -0.1121   0.04734   0.04480  -0.0753   0.9142   0.0077
  -5.000  -0.0825   0.04214   0.03941  -0.0794   0.9067   0.0080
  -4.750  -0.0508   0.03624   0.03322  -0.0829   0.8988   0.0083
  -4.500  -0.0216   0.03251   0.02927  -0.0849   0.8907   0.0088
  -4.250   0.0062   0.03034   0.02691  -0.0858   0.8819   0.0094
  -4.000   0.0360   0.02751   0.02384  -0.0868   0.8719   0.0109
  -3.750   0.0697   0.02207   0.01785  -0.0879   0.8624   0.0128
  -3.500   0.0969   0.02145   0.01711  -0.0881   0.8495   0.0135
  -3.250   0.1255   0.02014   0.01557  -0.0882   0.8339   0.0155
  -3.000   0.1575   0.01651   0.01133  -0.0883   0.8171   0.0190
  -2.750   0.1840   0.01651   0.01122  -0.0882   0.7935   0.0199
  -2.500   0.2109   0.01630   0.01085  -0.0882   0.7696   0.0213
  -2.250   0.2392   0.01544   0.00968  -0.0881   0.7464   0.0229
  -1.750   0.2958   0.01432   0.00800  -0.0879   0.7028   0.0262
  -1.500   0.3240   0.01397   0.00743  -0.0878   0.6813   0.0267
  -1.250   0.3522   0.01367   0.00695  -0.0879   0.6601   0.0271
  -1.000   0.3803   0.01273   0.00574  -0.0880   0.6316   0.0283
  -0.750   0.4077   0.01240   0.00517  -0.0879   0.5891   0.0283
  -0.500   0.4350   0.01219   0.00472  -0.0878   0.5516   0.0281
  -0.250   0.4628   0.01187   0.00425  -0.0878   0.5286   0.0281
   0.000   0.4907   0.01150   0.00376  -0.0879   0.5105   0.0284
   0.250   0.5186   0.01118   0.00335  -0.0880   0.4928   0.0292
   0.750   0.5745   0.01096   0.00297  -0.0883   0.4563   0.0318
   1.000   0.6025   0.01093   0.00287  -0.0884   0.4380   0.0330
   1.250   0.6304   0.01092   0.00279  -0.0886   0.4208   0.0339
   1.500   0.6584   0.01093   0.00274  -0.0887   0.4052   0.0346
   1.750   0.6863   0.01099   0.00273  -0.0888   0.3887   0.0358
   2.000   0.7139   0.01107   0.00274  -0.0889   0.3713   0.0370
   2.250   0.7416   0.01115   0.00274  -0.0890   0.3532   0.0370
   2.500   0.7689   0.01131   0.00278  -0.0891   0.3298   0.0370
   2.750   0.7957   0.01154   0.00287  -0.0891   0.3001   0.0370
   3.000   0.8223   0.01183   0.00299  -0.0890   0.2692   0.0371
   3.250   0.8487   0.01212   0.00313  -0.0890   0.2415   0.0374
   3.500   0.8752   0.01241   0.00331  -0.0889   0.2176   0.0380
   4.000   0.9266   0.01320   0.00380  -0.0887   0.1561   0.0752
   4.500   0.9723   0.01221   0.00441  -0.0875   0.1243   1.0000
   4.750   0.9980   0.01261   0.00470  -0.0873   0.1079   1.0000
   5.000   1.0217   0.01329   0.00510  -0.0870   0.0652   1.0000
   5.250   1.0439   0.01420   0.00579  -0.0863   0.0224   1.0000
   5.500   1.0695   0.01454   0.00612  -0.0861   0.0145   1.0000
   5.750   1.0951   0.01490   0.00656  -0.0858   0.0124   1.0000
   6.000   1.1199   0.01536   0.00713  -0.0854   0.0101   1.0000
   6.250   1.1451   0.01573   0.00757  -0.0851   0.0091   1.0000
   6.500   1.1696   0.01617   0.00810  -0.0847   0.0082   1.0000
   6.750   1.1934   0.01670   0.00871  -0.0841   0.0074   1.0000
   7.000   1.2159   0.01738   0.00950  -0.0834   0.0067   1.0000
   7.250   1.2394   0.01788   0.01009  -0.0829   0.0060   1.0000
   7.500   1.2615   0.01855   0.01084  -0.0821   0.0055   1.0000
   7.750   1.2826   0.01931   0.01168  -0.0812   0.0051   1.0000
   8.000   1.3021   0.02019   0.01264  -0.0801   0.0048   1.0000
   8.250   1.3171   0.02152   0.01408  -0.0783   0.0046   1.0000
   8.500   1.3340   0.02252   0.01517  -0.0768   0.0045   1.0000
   8.750   1.3505   0.02347   0.01622  -0.0752   0.0042   1.0000
   9.000   1.3661   0.02442   0.01729  -0.0736   0.0037   1.0000
   9.250   1.3787   0.02553   0.01848  -0.0716   0.0035   1.0000
   9.500   1.3881   0.02675   0.01980  -0.0690   0.0034   1.0000
   9.750   1.3939   0.02800   0.02114  -0.0660   0.0033   1.0000
  10.000   1.3972   0.02937   0.02260  -0.0628   0.0032   1.0000
  10.250   1.3993   0.03097   0.02429  -0.0597   0.0031   1.0000
  10.500   1.3985   0.03293   0.02635  -0.0568   0.0030   1.0000
  10.750   1.3952   0.03532   0.02883  -0.0540   0.0029   1.0000
  11.000   1.3963   0.03749   0.03111  -0.0518   0.0029   1.0000
  11.250   1.3971   0.03985   0.03356  -0.0498   0.0028   1.0000
  11.500   1.3983   0.04233   0.03615  -0.0481   0.0028   1.0000
  11.750   1.4001   0.04487   0.03878  -0.0465   0.0027   1.0000
  12.000   1.4021   0.04749   0.04154  -0.0451   0.0027   1.0000
  12.250   1.4042   0.05019   0.04435  -0.0438   0.0026   1.0000
  12.500   1.4059   0.05300   0.04729  -0.0427   0.0026   1.0000
  12.750   1.4066   0.05600   0.05042  -0.0418   0.0026   1.0000
  13.000   1.4059   0.05923   0.05379  -0.0412   0.0026   1.0000
  13.250   1.4031   0.06272   0.05743  -0.0408   0.0026   1.0000
  13.500   1.3983   0.06654   0.06142  -0.0409   0.0025   1.0000
  13.750   1.3917   0.07070   0.06575  -0.0414   0.0025   1.0000
  14.000   1.3837   0.07514   0.07037  -0.0422   0.0024   1.0000
  14.250   1.3746   0.07992   0.07532  -0.0435   0.0024   1.0000
  14.500   1.3652   0.08498   0.08055  -0.0452   0.0023   1.0000
  14.750   1.3553   0.09033   0.08606  -0.0473   0.0023   1.0000
  15.000   1.3448   0.09592   0.09180  -0.0497   0.0022   1.0000
  15.250   1.3342   0.10175   0.09778  -0.0525   0.0022   1.0000
  15.500   1.3227   0.10796   0.10415  -0.0555   0.0022   1.0000
  15.750   1.3116   0.11432   0.11065  -0.0588   0.0022   1.0000
  16.000   1.2999   0.12096   0.11744  -0.0624   0.0021   1.0000
  16.250   1.2883   0.12785   0.12448  -0.0663   0.0021   1.0000
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