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

GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)
Reynolds number: 200,000
Max Cl/Cd: 78.24 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe167-il-200000-n5.txt
Download as CSV file: xf-goe167-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 167 (V.KARMAN PROP.2) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2615   0.10317   0.10001  -0.0242   1.0000   0.0260
  -9.500  -0.2583   0.09983   0.09669  -0.0252   1.0000   0.0270
  -9.250  -0.3789   0.10688   0.10356  -0.0200   1.0000   0.0233
  -9.000  -0.3639   0.10415   0.10083  -0.0171   1.0000   0.0246
  -8.750  -0.3570   0.10116   0.09786  -0.0183   1.0000   0.0256
  -8.500  -0.3515   0.09791   0.09465  -0.0200   1.0000   0.0263
  -8.250  -0.3467   0.09463   0.09141  -0.0218   1.0000   0.0273
  -8.000  -0.3450   0.09162   0.08845  -0.0257   1.0000   0.0296
  -7.750  -0.3360   0.08739   0.08423  -0.0339   0.9686   0.0302
  -7.500  -0.3183   0.08226   0.07905  -0.0419   0.9365   0.0304
  -7.250  -0.3012   0.07744   0.07413  -0.0483   0.8979   0.0306
  -7.000  -0.2863   0.07288   0.06940  -0.0524   0.8582   0.0307
  -6.750  -0.2722   0.06840   0.06471  -0.0553   0.8251   0.0307
  -6.500  -0.2566   0.06390   0.05998  -0.0581   0.7976   0.0308
  -6.000  -0.2357   0.05657   0.05241  -0.0590   0.7486   0.0330
  -5.750  -0.2174   0.05470   0.05037  -0.0597   0.7253   0.0360
  -5.500  -0.1775   0.05114   0.04622  -0.0660   0.7064   0.0417
  -5.250  -0.1676   0.04672   0.04183  -0.0661   0.6890   0.0383
  -5.000  -0.1420   0.04254   0.03733  -0.0685   0.6740   0.0367
  -4.750  -0.1137   0.03925   0.03366  -0.0705   0.6602   0.0389
  -4.500  -0.0868   0.03574   0.02979  -0.0719   0.6478   0.0374
  -4.250  -0.0584   0.03249   0.02614  -0.0731   0.6363   0.0365
  -4.000  -0.0296   0.02994   0.02321  -0.0740   0.6259   0.0371
  -3.750  -0.0005   0.02776   0.02062  -0.0746   0.6169   0.0381
  -3.500   0.0287   0.02556   0.01805  -0.0752   0.6086   0.0376
  -3.250   0.0580   0.02369   0.01579  -0.0756   0.6017   0.0375
  -3.000   0.0873   0.02212   0.01388  -0.0760   0.5948   0.0376
  -2.500   0.1456   0.01998   0.01116  -0.0764   0.5825   0.0394
  -2.250   0.1746   0.01903   0.00995  -0.0766   0.5769   0.0396
  -2.000   0.2035   0.01818   0.00887  -0.0768   0.5721   0.0395
  -1.750   0.2324   0.01744   0.00797  -0.0769   0.5672   0.0397
  -1.500   0.2611   0.01683   0.00721  -0.0770   0.5628   0.0399
  -1.250   0.2897   0.01632   0.00657  -0.0771   0.5590   0.0403
  -1.000   0.3183   0.01587   0.00606  -0.0773   0.5550   0.0408
  -0.750   0.3469   0.01549   0.00563  -0.0774   0.5507   0.0412
  -0.500   0.3754   0.01521   0.00529  -0.0776   0.5468   0.0418
  -0.250   0.4037   0.01476   0.00482  -0.0778   0.5436   0.0440
   0.000   0.4323   0.01453   0.00459  -0.0781   0.5403   0.0458
   0.250   0.4612   0.01435   0.00441  -0.0784   0.5367   0.0467
   0.500   0.4899   0.01423   0.00425  -0.0786   0.5326   0.0479
   0.750   0.5185   0.01419   0.00412  -0.0788   0.5287   0.0494
   1.000   0.5472   0.01414   0.00404  -0.0790   0.5242   0.0518
   1.500   0.6046   0.01404   0.00403  -0.0795   0.5163   0.0810
   1.750   0.6263   0.01190   0.00406  -0.0783   0.5134   1.0000
   2.000   0.6549   0.01204   0.00412  -0.0785   0.5097   1.0000
   2.250   0.6835   0.01217   0.00421  -0.0787   0.5057   1.0000
   2.500   0.7120   0.01231   0.00430  -0.0789   0.5022   1.0000
   2.750   0.7403   0.01248   0.00440  -0.0791   0.4988   1.0000
   3.000   0.7686   0.01261   0.00452  -0.0793   0.4940   1.0000
   3.250   0.7967   0.01272   0.00462  -0.0794   0.4875   1.0000
   3.500   0.8246   0.01287   0.00471  -0.0795   0.4821   1.0000
   3.750   0.8528   0.01297   0.00486  -0.0797   0.4755   1.0000
   4.000   0.8807   0.01309   0.00497  -0.0798   0.4693   1.0000
   4.250   0.9085   0.01321   0.00513  -0.0799   0.4623   1.0000
   4.500   0.9362   0.01332   0.00526  -0.0800   0.4547   1.0000
   4.750   0.9640   0.01345   0.00543  -0.0801   0.4477   1.0000
   5.000   0.9915   0.01358   0.00561  -0.0802   0.4396   1.0000
   5.250   1.0191   0.01372   0.00581  -0.0803   0.4312   1.0000
   5.500   1.0462   0.01387   0.00599  -0.0803   0.4223   1.0000
   5.750   1.0735   0.01402   0.00623  -0.0804   0.4112   1.0000
   6.000   1.1003   0.01419   0.00644  -0.0803   0.3960   1.0000
   6.250   1.1266   0.01440   0.00666  -0.0802   0.3755   1.0000
   6.500   1.1501   0.01485   0.00690  -0.0798   0.3242   1.0000
   6.750   1.1674   0.01611   0.00766  -0.0788   0.2479   1.0000
   7.000   1.1881   0.01702   0.00842  -0.0782   0.2179   1.0000
   7.250   1.2100   0.01774   0.00909  -0.0777   0.1949   1.0000
   7.500   1.2239   0.01928   0.01016  -0.0764   0.1081   1.0000
   7.750   1.2382   0.02068   0.01136  -0.0750   0.0760   1.0000
   8.000   1.2571   0.02153   0.01224  -0.0740   0.0665   1.0000
   8.250   1.2753   0.02239   0.01313  -0.0730   0.0580   1.0000
   8.500   1.2947   0.02307   0.01391  -0.0721   0.0510   1.0000
   8.750   1.3127   0.02384   0.01475  -0.0709   0.0429   1.0000
   9.000   1.3252   0.02500   0.01580  -0.0693   0.0228   1.0000
   9.250   1.3340   0.02631   0.01711  -0.0671   0.0191   1.0000
   9.500   1.3420   0.02751   0.01841  -0.0647   0.0176   1.0000
   9.750   1.3468   0.02881   0.01985  -0.0620   0.0168   1.0000
  10.000   1.3504   0.03037   0.02157  -0.0596   0.0161   1.0000
  10.250   1.3528   0.03224   0.02358  -0.0577   0.0155   1.0000
  10.500   1.3537   0.03446   0.02595  -0.0562   0.0149   1.0000
  10.750   1.3532   0.03706   0.02869  -0.0552   0.0143   1.0000
  11.000   1.3505   0.04009   0.03186  -0.0546   0.0137   1.0000
  11.250   1.3455   0.04357   0.03549  -0.0542   0.0132   1.0000
  11.500   1.3406   0.04711   0.03916  -0.0539   0.0128   1.0000
  11.750   1.3411   0.05008   0.04226  -0.0537   0.0125   1.0000
  12.000   1.3402   0.05321   0.04552  -0.0535   0.0123   1.0000
  12.250   1.3388   0.05640   0.04883  -0.0533   0.0121   1.0000
  12.500   1.3372   0.05962   0.05217  -0.0531   0.0118   1.0000
  12.750   1.3355   0.06282   0.05549  -0.0529   0.0116   1.0000
  13.000   1.3339   0.06602   0.05880  -0.0527   0.0114   1.0000
  13.250   1.3325   0.06920   0.06208  -0.0525   0.0112   1.0000
  13.500   1.3317   0.07233   0.06532  -0.0522   0.0110   1.0000
  13.750   1.3313   0.07547   0.06857  -0.0521   0.0108   1.0000
  14.000   1.3314   0.07861   0.07182  -0.0520   0.0106   1.0000
  14.250   1.3314   0.08180   0.07514  -0.0520   0.0103   1.0000
  14.500   1.3311   0.08505   0.07849  -0.0521   0.0100   1.0000
  14.750   1.3306   0.08838   0.08191  -0.0523   0.0097   1.0000
  15.000   1.3301   0.09169   0.08529  -0.0524   0.0095   1.0000
  15.250   1.3300   0.09478   0.08843  -0.0521   0.0092   1.0000
  15.500   1.3292   0.09813   0.09189  -0.0520   0.0090   1.0000
  15.750   1.3272   0.10205   0.09600  -0.0529   0.0089   1.0000
  16.000   1.3246   0.10614   0.10027  -0.0539   0.0088   1.0000
  16.250   1.3209   0.11050   0.10482  -0.0552   0.0087   1.0000
  16.500   1.3161   0.11515   0.10965  -0.0567   0.0086   1.0000
  16.750   1.3102   0.12011   0.11480  -0.0586   0.0085   1.0000
  17.000   1.3033   0.12540   0.12029  -0.0608   0.0085   1.0000
  17.250   1.2954   0.13108   0.12617  -0.0635   0.0084   1.0000
  17.500   1.2865   0.13717   0.13245  -0.0666   0.0084   1.0000
  17.750   1.2770   0.14363   0.13910  -0.0702   0.0084   1.0000
  18.000   1.2667   0.15051   0.14617  -0.0742   0.0084   1.0000
  18.250   1.2556   0.15789   0.15374  -0.0787   0.0084   1.0000
  18.500   1.2439   0.16579   0.16182  -0.0838   0.0084   1.0000
  18.750   1.2313   0.17442   0.17063  -0.0895   0.0084   1.0000
  19.000   1.2179   0.18381   0.18018  -0.0958   0.0085   1.0000
  19.250   1.2032   0.19424   0.19076  -0.1028   0.0086   1.0000
<< Back to GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)

Polar data table (+)

Polar graphs


<< Back to GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)