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GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 504 AIRFOIL (goe504-il)
Reynolds number: 200,000
Max Cl/Cd: 62.79 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe504-il-200000-n5.txt
Download as CSV file: xf-goe504-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 504 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.2982   0.07902   0.07534  -0.1004   0.9666   0.0226
 -12.500  -0.3466   0.06402   0.06007  -0.1139   0.9610   0.0220
 -12.250  -0.3731   0.05423   0.04998  -0.1246   0.9516   0.0220
 -12.000  -0.3826   0.04668   0.04205  -0.1354   0.9451   0.0223
 -11.500  -0.4017   0.03885   0.03350  -0.1413   0.9187   0.0231
 -11.250  -0.4069   0.03659   0.03089  -0.1402   0.9051   0.0234
 -11.000  -0.4051   0.03466   0.02872  -0.1385   0.8933   0.0238
 -10.750  -0.3909   0.03301   0.02696  -0.1382   0.8838   0.0243
 -10.500  -0.3800   0.03176   0.02557  -0.1368   0.8725   0.0248
 -10.250  -0.3659   0.03058   0.02425  -0.1357   0.8623   0.0255
 -10.000  -0.3508   0.02933   0.02278  -0.1347   0.8530   0.0264
  -9.750  -0.3389   0.02831   0.02151  -0.1329   0.8422   0.0273
  -9.500  -0.3244   0.02730   0.02020  -0.1313   0.8327   0.0282
  -9.250  -0.3073   0.02622   0.01888  -0.1301   0.8236   0.0288
  -9.000  -0.2880   0.02498   0.01762  -0.1292   0.8149   0.0296
  -8.750  -0.2675   0.02408   0.01663  -0.1285   0.8067   0.0306
  -8.500  -0.2494   0.02334   0.01578  -0.1272   0.7978   0.0317
  -8.250  -0.2282   0.02258   0.01486  -0.1263   0.7903   0.0327
  -8.000  -0.2094   0.02191   0.01406  -0.1249   0.7817   0.0335
  -7.750  -0.1877   0.02130   0.01328  -0.1240   0.7745   0.0342
  -7.500  -0.1701   0.02048   0.01243  -0.1225   0.7665   0.0352
  -7.250  -0.1511   0.01977   0.01167  -0.1213   0.7593   0.0363
  -7.000  -0.1322   0.01922   0.01107  -0.1199   0.7519   0.0374
  -6.750  -0.1124   0.01871   0.01047  -0.1186   0.7447   0.0381
  -6.500  -0.0921   0.01825   0.00992  -0.1173   0.7380   0.0390
  -6.250  -0.0720   0.01786   0.00943  -0.1160   0.7307   0.0403
  -6.000  -0.0497   0.01749   0.00892  -0.1151   0.7247   0.0413
  -5.750  -0.0312   0.01705   0.00844  -0.1135   0.7174   0.0426
  -5.500  -0.0093   0.01669   0.00798  -0.1125   0.7110   0.0438
  -5.250   0.0126   0.01640   0.00759  -0.1114   0.7045   0.0451
  -5.000   0.0351   0.01615   0.00724  -0.1105   0.6978   0.0467
  -4.750   0.0591   0.01590   0.00689  -0.1098   0.6921   0.0495
  -4.500   0.0806   0.01563   0.00663  -0.1086   0.6850   0.0542
  -4.250   0.1038   0.01534   0.00634  -0.1078   0.6789   0.0673
  -4.000   0.1261   0.01504   0.00608  -0.1069   0.6728   0.0941
  -3.750   0.1462   0.01454   0.00581  -0.1056   0.6663   0.1435
  -3.500   0.1689   0.01425   0.00571  -0.1049   0.6607   0.2168
  -3.250   0.1918   0.01418   0.00566  -0.1039   0.6537   0.2372
  -3.000   0.2164   0.01414   0.00558  -0.1033   0.6476   0.2566
  -2.750   0.2407   0.01411   0.00551  -0.1026   0.6416   0.2734
  -2.500   0.2641   0.01408   0.00546  -0.1018   0.6350   0.2873
  -2.250   0.2893   0.01406   0.00536  -0.1013   0.6294   0.2964
  -2.000   0.3125   0.01404   0.00532  -0.1004   0.6229   0.3070
  -1.750   0.3362   0.01400   0.00526  -0.0996   0.6166   0.3186
  -1.500   0.3601   0.01397   0.00521  -0.0989   0.6110   0.3339
  -1.250   0.3826   0.01393   0.00520  -0.0980   0.6044   0.3498
  -1.000   0.4061   0.01389   0.00515  -0.0972   0.5985   0.3665
  -0.750   0.4285   0.01385   0.00515  -0.0962   0.5925   0.3838
  -0.500   0.4507   0.01380   0.00513  -0.0952   0.5862   0.4018
  -0.250   0.4739   0.01376   0.00509  -0.0943   0.5809   0.4227
   0.000   0.4948   0.01371   0.00513  -0.0930   0.5744   0.4464
   0.250   0.5161   0.01364   0.00513  -0.0918   0.5686   0.4795
   0.500   0.5363   0.01353   0.00516  -0.0904   0.5631   0.5285
   0.750   0.5539   0.01337   0.00525  -0.0884   0.5571   0.6003
   1.000   0.5724   0.01317   0.00534  -0.0864   0.5516   0.6964
   1.250   0.6043   0.01307   0.00556  -0.0870   0.5456   0.8113
   1.500   0.6683   0.01328   0.00586  -0.0946   0.5383   0.8964
   1.750   0.7214   0.01353   0.00602  -0.1000   0.5322   0.9351
   2.000   0.7628   0.01374   0.00620  -0.1031   0.5254   0.9582
   2.250   0.8016   0.01396   0.00633  -0.1056   0.5193   0.9744
   2.500   0.8384   0.01417   0.00650  -0.1079   0.5129   0.9878
   2.750   0.8779   0.01440   0.00667  -0.1107   0.5063   0.9988
   3.000   0.8977   0.01457   0.00676  -0.1094   0.5009   1.0000
   3.250   0.9114   0.01472   0.00690  -0.1069   0.4949   1.0000
   3.500   0.9259   0.01488   0.00701  -0.1045   0.4893   1.0000
   3.750   0.9404   0.01506   0.00713  -0.1021   0.4838   1.0000
   4.000   0.9536   0.01523   0.00729  -0.0994   0.4778   1.0000
   4.250   0.9660   0.01540   0.00742  -0.0966   0.4723   1.0000
   4.500   0.9782   0.01558   0.00758  -0.0938   0.4669   1.0000
   4.750   0.9901   0.01577   0.00776  -0.0909   0.4609   1.0000
   5.000   1.0035   0.01599   0.00792  -0.0883   0.4556   1.0000
   5.250   1.0171   0.01621   0.00815  -0.0859   0.4500   1.0000
   5.500   1.0305   0.01646   0.00839  -0.0834   0.4440   1.0000
   5.750   1.0452   0.01673   0.00861  -0.0813   0.4388   1.0000
   6.250   1.0736   0.01732   0.00922  -0.0770   0.4270   1.0000
   6.500   1.0881   0.01765   0.00952  -0.0749   0.4215   1.0000
   6.750   1.1024   0.01799   0.00990  -0.0729   0.4153   1.0000
   7.000   1.1166   0.01837   0.01026  -0.0709   0.4096   1.0000
   7.250   1.1314   0.01875   0.01066  -0.0691   0.4042   1.0000
   7.500   1.1457   0.01917   0.01111  -0.0673   0.3984   1.0000
   7.750   1.1600   0.01961   0.01153  -0.0655   0.3932   1.0000
   8.000   1.1743   0.02008   0.01205  -0.0638   0.3876   1.0000
   8.250   1.1876   0.02059   0.01258  -0.0620   0.3816   1.0000
   8.500   1.2008   0.02113   0.01309  -0.0602   0.3762   1.0000
   8.750   1.2141   0.02170   0.01373  -0.0585   0.3703   1.0000
   9.000   1.2251   0.02236   0.01439  -0.0566   0.3634   1.0000
   9.250   1.2344   0.02310   0.01516  -0.0545   0.3553   1.0000
   9.500   1.2428   0.02393   0.01597  -0.0525   0.3472   1.0000
   9.750   1.2510   0.02482   0.01690  -0.0505   0.3383   1.0000
  10.000   1.2571   0.02585   0.01789  -0.0484   0.3296   1.0000
  10.250   1.2653   0.02686   0.01896  -0.0467   0.3210   1.0000
  10.500   1.2720   0.02798   0.02008  -0.0449   0.3131   1.0000
  10.750   1.2791   0.02915   0.02129  -0.0433   0.3047   1.0000
  11.000   1.2853   0.03042   0.02257  -0.0417   0.2970   1.0000
  11.250   1.2904   0.03183   0.02400  -0.0401   0.2880   1.0000
  11.500   1.2946   0.03336   0.02556  -0.0386   0.2784   1.0000
  11.750   1.2953   0.03519   0.02738  -0.0370   0.2678   1.0000
  12.000   1.3001   0.03683   0.02906  -0.0358   0.2589   1.0000
  12.250   1.3012   0.03880   0.03104  -0.0344   0.2481   1.0000
  12.500   1.3006   0.04099   0.03323  -0.0331   0.2375   1.0000
  12.750   1.2984   0.04340   0.03564  -0.0319   0.2257   1.0000
  13.000   1.2925   0.04626   0.03847  -0.0307   0.2110   1.0000
  13.250   1.2843   0.04943   0.04160  -0.0296   0.1931   1.0000
  13.500   1.2737   0.05297   0.04507  -0.0286   0.1733   1.0000
  13.750   1.2622   0.05673   0.04877  -0.0278   0.1540   1.0000
  14.000   1.2335   0.06243   0.05426  -0.0269   0.1205   1.0000
  14.250   1.2078   0.06806   0.05974  -0.0263   0.0918   1.0000
  14.500   1.1790   0.07428   0.06581  -0.0260   0.0556   1.0000
  14.750   1.1542   0.08030   0.07177  -0.0260   0.0298   1.0000
  15.000   1.1447   0.08459   0.07610  -0.0263   0.0240   1.0000
  15.250   1.1377   0.08866   0.08025  -0.0266   0.0211   1.0000
  15.500   1.1351   0.09217   0.08386  -0.0269   0.0202   1.0000
  15.750   1.1312   0.09593   0.08772  -0.0274   0.0192   1.0000
  16.000   1.1254   0.10002   0.09193  -0.0280   0.0182   1.0000
  16.250   1.1207   0.10400   0.09602  -0.0287   0.0177   1.0000
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