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GOE 767 AIRFOIL (goe767-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 767 AIRFOIL (goe767-il)
Reynolds number: 200,000
Max Cl/Cd: 54.86 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe767-il-200000-n5.txt
Download as CSV file: xf-goe767-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 767 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -1.0210   0.07380   0.06857  -0.0228   1.0000   0.0357
 -14.750  -1.0564   0.06369   0.05816  -0.0309   1.0000   0.0357
 -14.500  -1.0728   0.05765   0.05195  -0.0351   1.0000   0.0358
 -14.250  -1.0849   0.05279   0.04694  -0.0381   1.0000   0.0359
 -14.000  -1.0936   0.04885   0.04287  -0.0400   1.0000   0.0360
 -13.750  -1.0993   0.04567   0.03958  -0.0409   1.0000   0.0362
 -13.500  -1.1034   0.04299   0.03679  -0.0409   1.0000   0.0364
 -13.250  -1.1057   0.04075   0.03445  -0.0402   1.0000   0.0367
 -13.000  -1.1064   0.03883   0.03242  -0.0389   1.0000   0.0369
 -12.750  -1.1057   0.03717   0.03065  -0.0370   1.0000   0.0373
 -12.500  -1.1034   0.03572   0.02910  -0.0347   1.0000   0.0377
 -12.250  -1.0977   0.03430   0.02756  -0.0327   1.0000   0.0382
 -12.000  -1.0885   0.03291   0.02603  -0.0309   1.0000   0.0387
 -11.750  -1.0772   0.03158   0.02454  -0.0293   1.0000   0.0392
 -11.500  -1.0641   0.03030   0.02311  -0.0277   1.0000   0.0397
 -11.250  -1.0493   0.02911   0.02175  -0.0263   1.0000   0.0401
 -11.000  -1.0337   0.02797   0.02057  -0.0249   1.0000   0.0406
 -10.750  -1.0169   0.02696   0.01953  -0.0235   1.0000   0.0411
 -10.500  -0.9991   0.02602   0.01854  -0.0222   1.0000   0.0417
 -10.250  -0.9804   0.02513   0.01758  -0.0210   1.0000   0.0425
 -10.000  -0.9610   0.02428   0.01666  -0.0198   1.0000   0.0433
  -9.750  -0.9410   0.02346   0.01575  -0.0186   1.0000   0.0443
  -9.500  -0.9203   0.02267   0.01484  -0.0175   1.0000   0.0453
  -9.250  -0.9002   0.02188   0.01406  -0.0163   1.0000   0.0463
  -9.000  -0.8790   0.02118   0.01334  -0.0152   1.0000   0.0474
  -8.750  -0.8573   0.02051   0.01262  -0.0141   1.0000   0.0487
  -8.500  -0.8352   0.01987   0.01191  -0.0130   1.0000   0.0502
  -8.250  -0.8131   0.01923   0.01127  -0.0120   1.0000   0.0519
  -8.000  -0.7906   0.01867   0.01070  -0.0109   1.0000   0.0540
  -7.750  -0.7676   0.01813   0.01011  -0.0099   1.0000   0.0570
  -7.500  -0.7446   0.01764   0.00967  -0.0089   1.0000   0.0603
  -7.250  -0.7212   0.01719   0.00922  -0.0079   1.0000   0.0648
  -7.000  -0.6974   0.01680   0.00883  -0.0069   1.0000   0.0702
  -6.750  -0.6735   0.01646   0.00852  -0.0060   1.0000   0.0754
  -6.500  -0.6495   0.01614   0.00818  -0.0050   1.0000   0.0810
  -6.250  -0.6254   0.01587   0.00791  -0.0041   1.0000   0.0863
  -6.000  -0.6014   0.01559   0.00762  -0.0031   1.0000   0.0912
  -5.750  -0.5774   0.01535   0.00739  -0.0021   1.0000   0.0959
  -5.500  -0.5532   0.01511   0.00710  -0.0011   1.0000   0.1004
  -5.250  -0.5299   0.01480   0.00686   0.0000   1.0000   0.1043
  -5.000  -0.4995   0.01454   0.00659  -0.0004   0.9928   0.1087
  -4.750  -0.4584   0.01423   0.00627  -0.0029   0.9664   0.1136
  -4.500  -0.4038   0.01396   0.00599  -0.0080   0.8960   0.1215
  -4.250  -0.3625   0.01398   0.00562  -0.0099   0.7380   0.1284
  -4.000  -0.3401   0.01413   0.00538  -0.0083   0.6459   0.1334
  -3.750  -0.3155   0.01414   0.00515  -0.0072   0.6039   0.1381
  -3.500  -0.2904   0.01400   0.00492  -0.0064   0.5746   0.1424
  -3.250  -0.2650   0.01388   0.00472  -0.0056   0.5496   0.1468
  -3.000  -0.2390   0.01378   0.00451  -0.0049   0.5276   0.1518
  -2.750  -0.2131   0.01365   0.00432  -0.0043   0.5083   0.1576
  -2.500  -0.1870   0.01353   0.00416  -0.0036   0.4912   0.1650
  -2.250  -0.1606   0.01341   0.00400  -0.0030   0.4757   0.1732
  -2.000  -0.1343   0.01328   0.00385  -0.0024   0.4614   0.1837
  -1.750  -0.1082   0.01315   0.00371  -0.0018   0.4478   0.1971
  -1.500  -0.0821   0.01300   0.00358  -0.0013   0.4340   0.2152
  -1.250  -0.0563   0.01280   0.00348  -0.0007   0.4212   0.2436
  -1.000  -0.0311   0.01257   0.00340   0.0000   0.4090   0.2959
  -0.750  -0.0059   0.01232   0.00334   0.0007   0.3971   0.3550
  -0.500   0.0186   0.01205   0.00330   0.0016   0.3868   0.4237
  -0.250   0.0424   0.01177   0.00329   0.0026   0.3764   0.5031
   0.000   0.0657   0.01149   0.00332   0.0039   0.3667   0.5881
   0.250   0.0894   0.01131   0.00337   0.0052   0.3570   0.6634
   0.500   0.1142   0.01119   0.00344   0.0064   0.3477   0.7260
   0.750   0.1402   0.01114   0.00352   0.0074   0.3381   0.7851
   1.000   0.1711   0.01114   0.00366   0.0076   0.3282   0.8433
   1.500   0.2536   0.01144   0.00395   0.0035   0.3090   0.9316
   2.000   0.3361   0.01180   0.00417  -0.0011   0.2908   0.9711
   2.250   0.3763   0.01198   0.00424  -0.0034   0.2811   0.9828
   2.500   0.4204   0.01212   0.00431  -0.0065   0.2708   0.9936
   2.750   0.4590   0.01226   0.00437  -0.0086   0.2635   1.0000
   3.000   0.4820   0.01239   0.00448  -0.0076   0.2577   1.0000
   3.250   0.5051   0.01256   0.00458  -0.0065   0.2525   1.0000
   3.500   0.5282   0.01275   0.00471  -0.0054   0.2480   1.0000
   3.750   0.5519   0.01290   0.00488  -0.0045   0.2429   1.0000
   4.000   0.5755   0.01309   0.00503  -0.0035   0.2376   1.0000
   4.500   0.6229   0.01351   0.00540  -0.0015   0.2280   1.0000
   4.750   0.6468   0.01372   0.00561  -0.0006   0.2231   1.0000
   5.000   0.6704   0.01397   0.00581   0.0004   0.2181   1.0000
   5.250   0.6945   0.01421   0.00605   0.0013   0.2131   1.0000
   5.500   0.7187   0.01442   0.00629   0.0021   0.2073   1.0000
   5.750   0.7423   0.01469   0.00653   0.0031   0.2019   1.0000
   6.000   0.7664   0.01495   0.00681   0.0039   0.1967   1.0000
   6.250   0.7905   0.01519   0.00709   0.0048   0.1906   1.0000
   6.500   0.8139   0.01550   0.00735   0.0057   0.1849   1.0000
   6.750   0.8384   0.01574   0.00767   0.0065   0.1781   1.0000
   7.000   0.8620   0.01604   0.00795   0.0073   0.1717   1.0000
   7.250   0.8860   0.01635   0.00831   0.0082   0.1656   1.0000
   7.500   0.9095   0.01668   0.00864   0.0090   0.1592   1.0000
   7.750   0.9330   0.01705   0.00901   0.0098   0.1535   1.0000
   8.000   0.9562   0.01743   0.00941   0.0106   0.1479   1.0000
   8.250   0.9788   0.01787   0.00983   0.0115   0.1433   1.0000
   8.500   1.0018   0.01830   0.01031   0.0123   0.1383   1.0000
   8.750   1.0237   0.01879   0.01078   0.0132   0.1330   1.0000
   9.000   1.0460   0.01927   0.01130   0.0141   0.1278   1.0000
   9.250   1.0675   0.01980   0.01183   0.0149   0.1228   1.0000
   9.500   1.0880   0.02040   0.01243   0.0159   0.1190   1.0000
   9.750   1.1096   0.02093   0.01305   0.0168   0.1155   1.0000
  10.000   1.1301   0.02152   0.01369   0.0177   0.1122   1.0000
  10.250   1.1490   0.02222   0.01438   0.0188   0.1091   1.0000
  10.500   1.1686   0.02286   0.01511   0.0198   0.1063   1.0000
  10.750   1.1880   0.02349   0.01584   0.0209   0.1032   1.0000
  11.000   1.2058   0.02420   0.01661   0.0220   0.1004   1.0000
  11.250   1.2213   0.02504   0.01745   0.0233   0.0979   1.0000
  11.500   1.2381   0.02578   0.01831   0.0245   0.0952   1.0000
  11.750   1.2537   0.02656   0.01920   0.0257   0.0923   1.0000
  12.000   1.2665   0.02743   0.02014   0.0272   0.0895   1.0000
  12.250   1.2750   0.02847   0.02120   0.0290   0.0873   1.0000
  12.500   1.2836   0.02941   0.02229   0.0309   0.0848   1.0000
  12.750   1.2889   0.03055   0.02354   0.0328   0.0824   1.0000
  13.000   1.2913   0.03199   0.02505   0.0343   0.0803   1.0000
  13.250   1.2902   0.03391   0.02703   0.0352   0.0786   1.0000
  13.500   1.2901   0.03614   0.02940   0.0352   0.0767   1.0000
  13.750   1.2886   0.03891   0.03233   0.0343   0.0747   1.0000
  14.000   1.2846   0.04236   0.03589   0.0326   0.0728   1.0000
  14.250   1.2777   0.04635   0.03998   0.0305   0.0713   1.0000
  14.500   1.2679   0.05076   0.04444   0.0281   0.0700   1.0000
  14.750   1.2592   0.05512   0.04896   0.0260   0.0684   1.0000
  15.000   1.2475   0.05990   0.05388   0.0235   0.0668   1.0000
  15.250   1.2337   0.06504   0.05912   0.0209   0.0654   1.0000
  15.500   1.2194   0.07030   0.06447   0.0182   0.0643   1.0000
  15.750   1.2050   0.07564   0.06987   0.0154   0.0632   1.0000
  16.000   1.1916   0.08094   0.07522   0.0127   0.0621   1.0000
  16.250   1.1760   0.08699   0.08142   0.0095   0.0607   1.0000
  16.500   1.1618   0.09297   0.08752   0.0063   0.0595   1.0000
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