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

GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 604 AIRFOIL (goe604-il)
Reynolds number: 500,000
Max Cl/Cd: 85.68 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe604-il-500000-n5.txt
Download as CSV file: xf-goe604-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 604 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
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.6784   0.08985   0.08650  -0.0667   1.0000   0.0217
 -16.750  -0.7014   0.08277   0.07933  -0.0708   1.0000   0.0218
 -16.500  -0.7261   0.07582   0.07228  -0.0749   1.0000   0.0220
 -16.250  -0.7526   0.06897   0.06533  -0.0789   1.0000   0.0220
 -16.000  -0.7778   0.06239   0.05865  -0.0827   1.0000   0.0222
 -15.750  -0.8038   0.05582   0.05197  -0.0866   1.0000   0.0223
 -15.500  -0.8257   0.04973   0.04575  -0.0903   1.0000   0.0224
 -15.250  -0.8442   0.04400   0.03990  -0.0940   1.0000   0.0225
 -15.000  -0.8592   0.03888   0.03464  -0.0974   1.0000   0.0227
 -14.750  -0.8735   0.03488   0.03052  -0.0993   1.0000   0.0228
 -14.250  -0.8560   0.02977   0.02515  -0.1044   0.9836   0.0237
 -14.000  -0.8387   0.02802   0.02325  -0.1064   0.9744   0.0242
 -13.750  -0.8161   0.02643   0.02154  -0.1087   0.9663   0.0246
 -13.500  -0.7885   0.02507   0.02012  -0.1112   0.9571   0.0250
 -13.250  -0.7588   0.02401   0.01898  -0.1134   0.9458   0.0256
 -13.000  -0.7295   0.02306   0.01793  -0.1152   0.9317   0.0261
 -12.750  -0.7059   0.02227   0.01703  -0.1155   0.9141   0.0267
 -12.500  -0.6883   0.02162   0.01623  -0.1144   0.8930   0.0273
 -12.250  -0.6722   0.02105   0.01550  -0.1128   0.8695   0.0278
 -12.000  -0.6576   0.02051   0.01478  -0.1108   0.8422   0.0282
 -11.750  -0.6449   0.01997   0.01409  -0.1085   0.8114   0.0286
 -11.500  -0.6304   0.01956   0.01352  -0.1064   0.7800   0.0291
 -11.250  -0.6142   0.01921   0.01302  -0.1044   0.7514   0.0296
 -11.000  -0.5971   0.01888   0.01252  -0.1026   0.7254   0.0302
 -10.750  -0.5794   0.01854   0.01202  -0.1009   0.7028   0.0308
 -10.500  -0.5603   0.01822   0.01155  -0.0993   0.6830   0.0314
 -10.000  -0.5208   0.01748   0.01056  -0.0965   0.6527   0.0326
  -9.750  -0.5004   0.01710   0.01011  -0.0952   0.6413   0.0332
  -9.500  -0.4789   0.01679   0.00971  -0.0941   0.6298   0.0338
  -9.250  -0.4565   0.01648   0.00933  -0.0931   0.6201   0.0346
  -9.000  -0.4342   0.01619   0.00894  -0.0920   0.6108   0.0353
  -8.750  -0.4109   0.01590   0.00857  -0.0911   0.6029   0.0360
  -8.500  -0.3876   0.01562   0.00821  -0.0901   0.5947   0.0367
  -8.250  -0.3651   0.01527   0.00780  -0.0891   0.5877   0.0376
  -8.000  -0.3413   0.01497   0.00746  -0.0883   0.5804   0.0384
  -7.750  -0.3175   0.01474   0.00715  -0.0874   0.5734   0.0392
  -7.500  -0.2928   0.01450   0.00686  -0.0867   0.5668   0.0403
  -7.250  -0.2681   0.01428   0.00657  -0.0859   0.5595   0.0413
  -7.000  -0.2442   0.01404   0.00625  -0.0851   0.5524   0.0423
  -6.750  -0.2194   0.01378   0.00597  -0.0844   0.5458   0.0435
  -6.500  -0.1943   0.01357   0.00572  -0.0837   0.5396   0.0448
  -6.250  -0.1693   0.01341   0.00548  -0.0830   0.5343   0.0462
  -6.000  -0.1436   0.01320   0.00524  -0.0824   0.5292   0.0479
  -5.750  -0.1182   0.01299   0.00502  -0.0818   0.5236   0.0500
  -5.500  -0.0927   0.01284   0.00481  -0.0811   0.5184   0.0523
  -5.250  -0.0670   0.01267   0.00461  -0.0805   0.5141   0.0548
  -5.000  -0.0411   0.01249   0.00442  -0.0800   0.5094   0.0582
  -4.750  -0.0154   0.01233   0.00424  -0.0794   0.5040   0.0624
  -4.500   0.0101   0.01220   0.00407  -0.0788   0.4990   0.0681
  -4.250   0.0358   0.01200   0.00390  -0.0783   0.4945   0.0771
  -4.000   0.0611   0.01177   0.00374  -0.0777   0.4899   0.0934
  -3.750   0.0864   0.01159   0.00366  -0.0771   0.4852   0.1201
  -3.500   0.1124   0.01154   0.00359  -0.0766   0.4807   0.1344
  -3.250   0.1391   0.01145   0.00353  -0.0762   0.4764   0.1450
  -3.000   0.1657   0.01140   0.00346  -0.0758   0.4713   0.1526
  -2.750   0.1918   0.01135   0.00340  -0.0752   0.4660   0.1601
  -2.500   0.2182   0.01134   0.00335  -0.0748   0.4612   0.1657
  -2.250   0.2446   0.01126   0.00329  -0.0744   0.4564   0.1741
  -2.000   0.2709   0.01123   0.00325  -0.0739   0.4514   0.1824
  -1.750   0.2964   0.01119   0.00322  -0.0733   0.4466   0.1931
  -1.500   0.3225   0.01113   0.00319  -0.0729   0.4421   0.2072
  -1.250   0.3484   0.01106   0.00318  -0.0724   0.4370   0.2265
  -1.000   0.3738   0.01102   0.00317  -0.0718   0.4318   0.2476
  -0.750   0.3992   0.01100   0.00318  -0.0713   0.4269   0.2664
  -0.500   0.4252   0.01097   0.00318  -0.0708   0.4215   0.2848
  -0.250   0.4506   0.01096   0.00319  -0.0702   0.4157   0.3029
   0.000   0.4756   0.01097   0.00322  -0.0696   0.4104   0.3216
   0.250   0.5012   0.01096   0.00324  -0.0691   0.4052   0.3416
   0.500   0.5262   0.01096   0.00328  -0.0685   0.3998   0.3635
   0.750   0.5503   0.01098   0.00333  -0.0677   0.3949   0.3898
   1.000   0.5751   0.01093   0.00338  -0.0671   0.3903   0.4243
   1.250   0.5988   0.01088   0.00344  -0.0662   0.3853   0.4664
   1.500   0.6211   0.01082   0.00351  -0.0652   0.3805   0.5200
   1.750   0.6426   0.01073   0.00360  -0.0639   0.3758   0.5876
   2.000   0.6625   0.01059   0.00370  -0.0623   0.3701   0.6675
   2.250   0.6801   0.01047   0.00382  -0.0601   0.3643   0.7542
   2.500   0.7012   0.01037   0.00397  -0.0585   0.3593   0.8446
   2.750   0.7657   0.01055   0.00428  -0.0661   0.3526   0.9351
   3.000   0.8247   0.01085   0.00451  -0.0728   0.3469   0.9630
   3.250   0.8645   0.01106   0.00467  -0.0754   0.3430   0.9767
   3.500   0.8996   0.01123   0.00483  -0.0770   0.3395   0.9861
   3.750   0.9337   0.01144   0.00499  -0.0785   0.3354   0.9940
   4.000   0.9745   0.01168   0.00518  -0.0814   0.3313   1.0000
   4.250   0.9921   0.01187   0.00533  -0.0795   0.3279   1.0000
   4.500   1.0116   0.01200   0.00545  -0.0780   0.3248   1.0000
   4.750   1.0305   0.01215   0.00560  -0.0763   0.3216   1.0000
   5.000   1.0491   0.01232   0.00575  -0.0746   0.3189   1.0000
   5.250   1.0670   0.01251   0.00592  -0.0728   0.3163   1.0000
   5.500   1.0844   0.01272   0.00611  -0.0709   0.3138   1.0000
   5.750   1.1008   0.01293   0.00630  -0.0688   0.3116   1.0000
   6.000   1.1180   0.01308   0.00647  -0.0668   0.3098   1.0000
   6.250   1.1349   0.01325   0.00665  -0.0649   0.3076   1.0000
   6.500   1.1516   0.01344   0.00685  -0.0629   0.3052   1.0000
   6.750   1.1681   0.01366   0.00706  -0.0609   0.3025   1.0000
   7.000   1.1844   0.01391   0.00731  -0.0590   0.3001   1.0000
   7.250   1.2004   0.01419   0.00758  -0.0571   0.2975   1.0000
   7.500   1.2172   0.01448   0.00787  -0.0554   0.2949   1.0000
   7.750   1.2361   0.01471   0.00813  -0.0541   0.2926   1.0000
   8.000   1.2547   0.01498   0.00842  -0.0527   0.2902   1.0000
   8.250   1.2723   0.01528   0.00875  -0.0513   0.2873   1.0000
   8.500   1.2891   0.01564   0.00910  -0.0498   0.2844   1.0000
   8.750   1.3051   0.01604   0.00951  -0.0483   0.2818   1.0000
   9.000   1.3214   0.01645   0.00993  -0.0469   0.2790   1.0000
   9.250   1.3399   0.01679   0.01032  -0.0458   0.2759   1.0000
   9.500   1.3571   0.01720   0.01076  -0.0446   0.2727   1.0000
   9.750   1.3731   0.01768   0.01126  -0.0433   0.2695   1.0000
  10.000   1.3874   0.01826   0.01184  -0.0419   0.2663   1.0000
  10.250   1.4028   0.01882   0.01243  -0.0407   0.2634   1.0000
  10.500   1.4195   0.01934   0.01300  -0.0397   0.2597   1.0000
  10.750   1.4343   0.01998   0.01367  -0.0386   0.2556   1.0000
  11.000   1.4458   0.02082   0.01453  -0.0373   0.2511   1.0000
  11.250   1.4599   0.02157   0.01532  -0.0363   0.2466   1.0000
  11.500   1.4720   0.02247   0.01624  -0.0352   0.2407   1.0000
  11.750   1.4809   0.02362   0.01741  -0.0340   0.2346   1.0000
  12.000   1.4903   0.02480   0.01861  -0.0330   0.2269   1.0000
  12.250   1.4940   0.02647   0.02027  -0.0318   0.2166   1.0000
  12.500   1.4919   0.02868   0.02245  -0.0305   0.2033   1.0000
  12.750   1.4833   0.03159   0.02532  -0.0292   0.1895   1.0000
  13.000   1.4784   0.03433   0.02806  -0.0283   0.1819   1.0000
  13.250   1.4753   0.03700   0.03076  -0.0276   0.1762   1.0000
  13.500   1.4681   0.04013   0.03390  -0.0270   0.1708   1.0000
  13.750   1.4652   0.04290   0.03673  -0.0266   0.1670   1.0000
  14.000   1.4645   0.04552   0.03940  -0.0262   0.1645   1.0000
  14.250   1.4597   0.04857   0.04250  -0.0260   0.1613   1.0000
  14.500   1.4542   0.05175   0.04573  -0.0257   0.1588   1.0000
  14.750   1.4482   0.05505   0.04907  -0.0256   0.1563   1.0000
  15.000   1.4492   0.05766   0.05176  -0.0256   0.1545   1.0000
  15.250   1.4506   0.06021   0.05437  -0.0256   0.1530   1.0000
  15.500   1.4497   0.06306   0.05730  -0.0257   0.1512   1.0000
  15.750   1.4498   0.06583   0.06013  -0.0258   0.1500   1.0000
  16.000   1.4470   0.06895   0.06331  -0.0259   0.1482   1.0000
  16.250   1.4409   0.07250   0.06690  -0.0262   0.1459   1.0000
  16.500   1.4387   0.07558   0.07003  -0.0264   0.1444   1.0000
  16.750   1.4347   0.07893   0.07343  -0.0268   0.1426   1.0000
  17.000   1.4387   0.08137   0.07595  -0.0271   0.1412   1.0000
  17.250   1.4391   0.08426   0.07893  -0.0275   0.1392   1.0000
  17.500   1.4401   0.08706   0.08179  -0.0279   0.1374   1.0000
  17.750   1.4381   0.09026   0.08506  -0.0284   0.1355   1.0000
  18.000   1.4357   0.09352   0.08836  -0.0290   0.1334   1.0000
  18.250   1.4328   0.09687   0.09176  -0.0296   0.1318   1.0000
<< Back to GOE 604 AIRFOIL (goe604-il)

Polar data table (+)

Polar graphs


<< Back to GOE 604 AIRFOIL (goe604-il)