Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 548 AIRFOIL (goe548-il)
Reynolds number: 1,000,000
Max Cl/Cd: 76.27 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe548-il-1000000-n5.txt
Download as CSV file: xf-goe548-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 548 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
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.6893   0.10884   0.10695  -0.0435   1.0000   0.0033
 -15.250  -0.7441   0.09413   0.09210  -0.0500   1.0000   0.0031
 -15.000  -0.7945   0.08096   0.07883  -0.0562   1.0000   0.0030
 -14.750  -0.8704   0.06305   0.06073  -0.0660   1.0000   0.0028
 -14.500  -0.8961   0.05452   0.05206  -0.0713   1.0000   0.0029
 -14.250  -0.9227   0.04654   0.04391  -0.0767   1.0000   0.0028
 -14.000  -0.9503   0.03997   0.03715  -0.0803   1.0000   0.0028
 -13.750  -0.9562   0.03664   0.03369  -0.0817   0.9997   0.0029
 -13.500  -0.9534   0.03294   0.02979  -0.0853   0.9978   0.0029
 -13.250  -0.9472   0.03033   0.02701  -0.0871   0.9944   0.0029
 -13.000  -0.9399   0.02833   0.02485  -0.0873   0.9901   0.0030
 -12.500  -0.9181   0.02546   0.02170  -0.0862   0.9785   0.0030
 -12.250  -0.9143   0.02334   0.01937  -0.0845   0.9694   0.0032
 -11.750  -0.8750   0.02077   0.01650  -0.0848   0.9603   0.0033
 -11.500  -0.8503   0.01976   0.01539  -0.0855   0.9565   0.0035
 -11.250  -0.8217   0.01895   0.01450  -0.0868   0.9540   0.0037
 -11.000  -0.7924   0.01802   0.01344  -0.0883   0.9514   0.0038
 -10.750  -0.7644   0.01718   0.01250  -0.0894   0.9472   0.0039
 -10.500  -0.7350   0.01644   0.01163  -0.0906   0.9432   0.0041
 -10.250  -0.7055   0.01566   0.01073  -0.0919   0.9391   0.0043
 -10.000  -0.6790   0.01508   0.01005  -0.0923   0.9347   0.0045
  -9.750  -0.6537   0.01454   0.00941  -0.0924   0.9306   0.0046
  -9.500  -0.6282   0.01403   0.00881  -0.0925   0.9269   0.0047
  -9.250  -0.6051   0.01339   0.00807  -0.0921   0.9233   0.0051
  -9.000  -0.5830   0.01292   0.00756  -0.0914   0.9199   0.0056
  -8.750  -0.5595   0.01255   0.00713  -0.0908   0.9167   0.0059
  -8.500  -0.5357   0.01214   0.00663  -0.0904   0.9133   0.0062
  -8.250  -0.5107   0.01183   0.00625  -0.0901   0.9103   0.0067
  -8.000  -0.4872   0.01153   0.00589  -0.0894   0.9074   0.0070
  -7.750  -0.4654   0.01110   0.00541  -0.0884   0.9041   0.0078
  -7.500  -0.4420   0.01077   0.00504  -0.0878   0.9010   0.0086
  -7.250  -0.4174   0.01049   0.00471  -0.0873   0.8981   0.0095
  -7.000  -0.3919   0.01025   0.00441  -0.0870   0.8955   0.0103
  -6.750  -0.3688   0.00995   0.00410  -0.0863   0.8928   0.0130
  -6.500  -0.3453   0.00968   0.00384  -0.0855   0.8894   0.0161
  -6.250  -0.3209   0.00944   0.00361  -0.0850   0.8861   0.0231
  -6.000  -0.2954   0.00924   0.00343  -0.0847   0.8831   0.0281
  -5.750  -0.2695   0.00910   0.00327  -0.0844   0.8802   0.0318
  -5.500  -0.2442   0.00898   0.00313  -0.0840   0.8769   0.0331
  -5.250  -0.2194   0.00878   0.00293  -0.0834   0.8732   0.0361
  -5.000  -0.1938   0.00863   0.00275  -0.0831   0.8688   0.0389
  -4.750  -0.1689   0.00849   0.00260  -0.0826   0.8628   0.0411
  -4.500  -0.1435   0.00840   0.00246  -0.0821   0.8551   0.0430
  -4.250  -0.1188   0.00827   0.00230  -0.0815   0.8459   0.0442
  -4.000  -0.0943   0.00812   0.00210  -0.0808   0.8344   0.0470
  -3.750  -0.0703   0.00799   0.00193  -0.0800   0.8181   0.0502
  -3.500  -0.0475   0.00792   0.00177  -0.0789   0.7912   0.0534
  -3.250  -0.0258   0.00792   0.00163  -0.0775   0.7643   0.0564
  -3.000  -0.0033   0.00786   0.00152  -0.0764   0.7477   0.0686
  -2.750   0.0181   0.00760   0.00139  -0.0753   0.7366   0.1195
  -2.500   0.0404   0.00738   0.00129  -0.0743   0.7279   0.1699
  -2.250   0.0646   0.00723   0.00122  -0.0736   0.7213   0.2023
  -2.000   0.0882   0.00715   0.00117  -0.0728   0.7124   0.2294
  -1.750   0.1121   0.00701   0.00112  -0.0721   0.7034   0.2638
  -1.500   0.1356   0.00687   0.00108  -0.0713   0.6962   0.3058
  -1.250   0.1592   0.00670   0.00105  -0.0706   0.6882   0.3574
  -1.000   0.1832   0.00659   0.00102  -0.0699   0.6818   0.3950
  -0.750   0.2077   0.00648   0.00101  -0.0693   0.6737   0.4318
  -0.500   0.2315   0.00637   0.00100  -0.0685   0.6661   0.4707
  -0.250   0.2555   0.00625   0.00100  -0.0678   0.6584   0.5131
   0.000   0.2786   0.00617   0.00101  -0.0668   0.6460   0.5547
   0.250   0.3009   0.00610   0.00102  -0.0657   0.6307   0.5975
   0.500   0.3239   0.00610   0.00103  -0.0647   0.6129   0.6198
   0.750   0.3458   0.00616   0.00105  -0.0634   0.5866   0.6385
   1.000   0.3666   0.00625   0.00109  -0.0620   0.5589   0.6605
   1.250   0.3870   0.00632   0.00116  -0.0605   0.5346   0.6920
   1.500   0.4059   0.00638   0.00125  -0.0586   0.5085   0.7342
   1.750   0.4261   0.00640   0.00134  -0.0570   0.4892   0.7758
   2.000   0.4464   0.00644   0.00143  -0.0554   0.4705   0.8145
   2.250   0.4673   0.00653   0.00153  -0.0539   0.4503   0.8455
   2.500   0.4897   0.00661   0.00164  -0.0528   0.4302   0.8717
   2.750   0.5135   0.00677   0.00177  -0.0520   0.4045   0.8969
   3.000   0.5415   0.00710   0.00197  -0.0524   0.3565   0.9222
   3.250   0.5712   0.00832   0.00253  -0.0538   0.2016   0.9455
   3.500   0.6116   0.00883   0.00284  -0.0571   0.1549   0.9570
   3.750   0.6476   0.00937   0.00313  -0.0595   0.1032   0.9658
   4.250   0.7115   0.00996   0.00361  -0.0619   0.0764   0.9818
   4.500   0.7426   0.01025   0.00385  -0.0629   0.0662   0.9891
   4.750   0.7697   0.01092   0.00430  -0.0633   0.0171   0.9955
   5.000   0.8023   0.01122   0.00459  -0.0646   0.0131   0.9987
   5.250   0.8312   0.01149   0.00490  -0.0652   0.0111   1.0000
   5.500   0.8486   0.01169   0.00512  -0.0631   0.0103   1.0000
   5.750   0.8658   0.01192   0.00536  -0.0611   0.0095   1.0000
   6.000   0.8823   0.01219   0.00564  -0.0589   0.0086   1.0000
   6.250   0.8973   0.01254   0.00601  -0.0564   0.0075   1.0000
   6.500   0.9125   0.01284   0.00635  -0.0539   0.0072   1.0000
   6.750   0.9269   0.01310   0.00664  -0.0513   0.0069   1.0000
   7.000   0.9414   0.01339   0.00695  -0.0487   0.0065   1.0000
   7.250   0.9562   0.01370   0.00730  -0.0462   0.0062   1.0000
   7.500   0.9718   0.01402   0.00763  -0.0440   0.0058   1.0000
   7.750   0.9881   0.01434   0.00795  -0.0420   0.0054   1.0000
   8.000   1.0021   0.01483   0.00847  -0.0395   0.0051   1.0000
   8.250   1.0169   0.01530   0.00898  -0.0373   0.0048   1.0000
   8.500   1.0326   0.01574   0.00948  -0.0353   0.0046   1.0000
   8.750   1.0482   0.01620   0.00999  -0.0333   0.0044   1.0000
   9.000   1.0626   0.01675   0.01059  -0.0312   0.0042   1.0000
   9.250   1.0762   0.01736   0.01126  -0.0290   0.0041   1.0000
   9.500   1.0886   0.01807   0.01204  -0.0266   0.0041   1.0000
   9.750   1.1037   0.01862   0.01263  -0.0249   0.0039   1.0000
  10.000   1.1179   0.01925   0.01330  -0.0230   0.0038   1.0000
  10.250   1.1339   0.01977   0.01384  -0.0215   0.0035   1.0000
  10.500   1.1491   0.02034   0.01443  -0.0200   0.0034   1.0000
  10.750   1.1554   0.02154   0.01573  -0.0172   0.0033   1.0000
  11.000   1.1606   0.02282   0.01712  -0.0144   0.0031   1.0000
  11.250   1.1711   0.02379   0.01817  -0.0125   0.0031   1.0000
  11.500   1.1818   0.02476   0.01922  -0.0106   0.0030   1.0000
  11.750   1.1934   0.02568   0.02021  -0.0090   0.0029   1.0000
  12.000   1.2042   0.02667   0.02127  -0.0074   0.0028   1.0000
  12.250   1.2090   0.02816   0.02287  -0.0053   0.0028   1.0000
  12.500   1.2173   0.02942   0.02421  -0.0036   0.0027   1.0000
  12.750   1.2243   0.03080   0.02569  -0.0020   0.0026   1.0000
  13.000   1.2298   0.03236   0.02735  -0.0004   0.0025   1.0000
  13.250   1.2327   0.03422   0.02932   0.0012   0.0025   1.0000
  13.500   1.2296   0.03672   0.03197   0.0031   0.0025   1.0000
  13.750   1.2348   0.03846   0.03382   0.0041   0.0025   1.0000
  14.000   1.2389   0.04041   0.03586   0.0050   0.0024   1.0000
  14.250   1.2475   0.04194   0.03744   0.0054   0.0023   1.0000
  14.500   1.2456   0.04462   0.04025   0.0063   0.0023   1.0000
  14.750   1.2409   0.04771   0.04349   0.0070   0.0023   1.0000
  15.000   1.2422   0.05024   0.04611   0.0072   0.0022   1.0000
  15.250   1.2383   0.05348   0.04948   0.0073   0.0022   1.0000
  15.500   1.2413   0.05601   0.05208   0.0070   0.0022   1.0000
  15.750   1.2336   0.05998   0.05618   0.0066   0.0022   1.0000
  16.000   1.2191   0.06506   0.06145   0.0058   0.0022   1.0000
  16.250   1.2232   0.06784   0.06427   0.0048   0.0021   1.0000
  16.500   1.2134   0.07263   0.06920   0.0034   0.0021   1.0000
  16.750   1.2069   0.07717   0.07384   0.0018   0.0021   1.0000
  17.000   1.1781   0.08532   0.08224  -0.0010   0.0021   1.0000
  17.250   1.1604   0.09205   0.08912  -0.0038   0.0021   1.0000
  17.500   1.1601   0.09613   0.09324  -0.0058   0.0021   1.0000
<< Back to GOE 548 AIRFOIL (goe548-il)

Polar data table (+)

Polar graphs


<< Back to GOE 548 AIRFOIL (goe548-il)