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GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il)
Reynolds number: 200,000
Max Cl/Cd: 71.63 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe207-il-200000-n5.txt
Download as CSV file: xf-goe207-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 207 (AVIATIK V8) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2139   0.09494   0.09141  -0.0194   0.8118   0.0273
  -7.250  -0.2043   0.09273   0.08908  -0.0233   0.7859   0.0275
  -7.000  -0.1903   0.09008   0.08631  -0.0278   0.7624   0.0275
  -6.750  -0.1743   0.08714   0.08326  -0.0321   0.7413   0.0276
  -6.500  -0.1643   0.08353   0.07956  -0.0308   0.7216   0.0277
  -6.250  -0.1514   0.08042   0.07636  -0.0316   0.7029   0.0280
  -6.000  -0.1359   0.07752   0.07337  -0.0336   0.6848   0.0283
  -5.750  -0.1181   0.07469   0.07044  -0.0363   0.6673   0.0287
  -5.500  -0.0985   0.07187   0.06751  -0.0394   0.6506   0.0292
  -5.250  -0.0769   0.06908   0.06461  -0.0428   0.6344   0.0301
  -5.000  -0.0513   0.06627   0.06166  -0.0471   0.6189   0.0313
  -4.750  -0.0171   0.06356   0.05876  -0.0536   0.6042   0.0319
  -4.500   0.0200   0.06096   0.05592  -0.0601   0.5906   0.0321
  -4.250   0.0462   0.05792   0.05275  -0.0630   0.5780   0.0323
  -4.000   0.0629   0.05485   0.04962  -0.0632   0.5663   0.0325
  -3.750   0.0854   0.05226   0.04694  -0.0647   0.5549   0.0330
  -3.500   0.1117   0.04989   0.04444  -0.0669   0.5440   0.0336
  -3.250   0.1401   0.04769   0.04208  -0.0693   0.5336   0.0348
  -3.000   0.1763   0.04567   0.03987  -0.0727   0.5232   0.0370
  -2.750   0.2211   0.04416   0.03798  -0.0769   0.5136   0.0375
  -2.500   0.2470   0.04143   0.03515  -0.0784   0.5039   0.0378
  -2.250   0.2708   0.03907   0.03273  -0.0794   0.4951   0.0383
  -2.000   0.2985   0.03719   0.03074  -0.0808   0.4858   0.0391
  -1.750   0.3288   0.03551   0.02892  -0.0822   0.4772   0.0403
  -1.500   0.3613   0.03398   0.02719  -0.0837   0.4684   0.0422
  -1.250   0.4006   0.03272   0.02558  -0.0853   0.4599   0.0441
  -1.000   0.4257   0.03084   0.02367  -0.0864   0.4506   0.0452
  -0.750   0.4553   0.02956   0.02226  -0.0873   0.4413   0.0472
  -0.500   0.4932   0.02928   0.02153  -0.0878   0.4322   0.0505
  -0.250   0.5222   0.02735   0.01953  -0.0889   0.4230   0.0511
   0.000   0.5503   0.02600   0.01808  -0.0897   0.4143   0.0521
   0.250   0.5801   0.02499   0.01694  -0.0904   0.4052   0.0538
   0.500   0.6143   0.02501   0.01652  -0.0902   0.3971   0.0580
   0.750   0.6446   0.02383   0.01517  -0.0907   0.3886   0.0582
   1.000   0.6751   0.02157   0.01276  -0.0914   0.3813   0.0411
   1.250   0.7053   0.02081   0.01180  -0.0916   0.3734   0.0419
   1.750   0.7664   0.01894   0.00933  -0.0915   0.3596   0.0376
   2.000   0.7949   0.01840   0.00863  -0.0915   0.3527   0.0374
   2.250   0.8234   0.01792   0.00801  -0.0915   0.3464   0.0375
   2.500   0.8515   0.01752   0.00751  -0.0915   0.3399   0.0378
   2.750   0.8789   0.01738   0.00731  -0.0915   0.3342   0.0392
   3.000   0.9067   0.01725   0.00718  -0.0915   0.3286   0.0414
   3.250   0.9344   0.01707   0.00694  -0.0914   0.3234   0.0422
   3.500   0.9617   0.01699   0.00678  -0.0914   0.3190   0.0431
   3.750   0.9895   0.01692   0.00673  -0.0914   0.3148   0.0442
   4.000   1.0171   0.01694   0.00679  -0.0915   0.3104   0.0461
   4.250   1.0441   0.01707   0.00688  -0.0914   0.3065   0.0505
   4.750   1.0981   0.01739   0.00718  -0.0913   0.2988   0.0628
   5.000   1.1252   0.01753   0.00734  -0.0912   0.2945   0.0878
   5.250   1.1453   0.01640   0.00757  -0.0898   0.2906   1.0000
   5.500   1.1712   0.01676   0.00780  -0.0896   0.2867   1.0000
   5.750   1.1979   0.01702   0.00807  -0.0895   0.2832   1.0000
   6.000   1.2243   0.01732   0.00837  -0.0894   0.2801   1.0000
   6.250   1.2503   0.01763   0.00868  -0.0892   0.2768   1.0000
   6.500   1.2757   0.01798   0.00897  -0.0890   0.2724   1.0000
   6.750   1.3012   0.01829   0.00929  -0.0888   0.2676   1.0000
   7.000   1.3269   0.01857   0.00962  -0.0887   0.2625   1.0000
   7.250   1.3518   0.01891   0.00996  -0.0884   0.2575   1.0000
   7.500   1.3763   0.01926   0.01031  -0.0881   0.2517   1.0000
   7.750   1.4011   0.01956   0.01066  -0.0879   0.2449   1.0000
   8.000   1.4246   0.01997   0.01105  -0.0875   0.2386   1.0000
   8.250   1.4489   0.02031   0.01148  -0.0872   0.2319   1.0000
   8.500   1.4715   0.02076   0.01191  -0.0867   0.2227   1.0000
   8.750   1.4945   0.02119   0.01239  -0.0862   0.2120   1.0000
   9.000   1.5149   0.02181   0.01296  -0.0856   0.1934   1.0000
   9.250   1.5173   0.02415   0.01471  -0.0832   0.1148   1.0000
   9.500   1.5239   0.02599   0.01644  -0.0811   0.0894   1.0000
   9.750   1.5163   0.02874   0.01897  -0.0775   0.0367   1.0000
  10.000   1.5193   0.03023   0.02056  -0.0749   0.0327   1.0000
  10.250   1.5221   0.03183   0.02230  -0.0726   0.0309   1.0000
  10.500   1.5225   0.03387   0.02450  -0.0708   0.0295   1.0000
  10.750   1.5224   0.03624   0.02703  -0.0697   0.0284   1.0000
  11.000   1.5233   0.03877   0.02972  -0.0691   0.0274   1.0000
  11.250   1.5215   0.04182   0.03294  -0.0689   0.0265   1.0000
  11.500   1.5170   0.04543   0.03672  -0.0692   0.0257   1.0000
  11.750   1.5096   0.04963   0.04109  -0.0698   0.0251   1.0000
  12.000   1.4991   0.05442   0.04606  -0.0708   0.0247   1.0000
  12.250   1.4860   0.05972   0.05152  -0.0719   0.0244   1.0000
  12.500   1.4704   0.06542   0.05740  -0.0732   0.0241   1.0000
  12.750   1.4533   0.07140   0.06355  -0.0746   0.0240   1.0000
  13.000   1.4348   0.07761   0.06992  -0.0760   0.0238   1.0000
  13.250   1.4166   0.08394   0.07641  -0.0776   0.0237   1.0000
  13.500   1.4019   0.08988   0.08249  -0.0791   0.0236   1.0000
  13.750   1.3883   0.09578   0.08855  -0.0807   0.0234   1.0000
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