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OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: OAF117 AIRFOIL (oaf117-il)
Reynolds number: 50,000
Max Cl/Cd: 34.84 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf117-il-50000-n5.txt
Download as CSV file: xf-oaf117-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF117 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6808   0.07496   0.06763  -0.0158   1.0000   0.0803
  -9.000  -0.7114   0.06119   0.05352  -0.0309   1.0000   0.0802
  -8.750  -0.7189   0.05215   0.04383  -0.0389   1.0000   0.0813
  -8.500  -0.6994   0.05027   0.04198  -0.0392   1.0000   0.0837
  -8.250  -0.6822   0.04707   0.03854  -0.0411   1.0000   0.0870
  -8.000  -0.6647   0.04238   0.03323  -0.0443   1.0000   0.0908
  -7.750  -0.6423   0.03945   0.02999  -0.0457   1.0000   0.0943
  -7.500  -0.6179   0.03771   0.02815  -0.0464   1.0000   0.0989
  -7.250  -0.5922   0.03479   0.02463  -0.0481   1.0000   0.1048
  -7.000  -0.5666   0.03352   0.02348  -0.0483   1.0000   0.1097
  -6.750  -0.5391   0.03156   0.02110  -0.0493   1.0000   0.1176
  -6.500  -0.5126   0.03033   0.01996  -0.0497   1.0000   0.1244
  -6.250  -0.4847   0.02883   0.01825  -0.0503   1.0000   0.1342
  -6.000  -0.4569   0.02767   0.01702  -0.0508   1.0000   0.1450
  -5.750  -0.4290   0.02667   0.01604  -0.0513   1.0000   0.1572
  -5.500  -0.4007   0.02570   0.01505  -0.0518   1.0000   0.1722
  -5.250  -0.3723   0.02481   0.01412  -0.0523   1.0000   0.1894
  -5.000  -0.3436   0.02404   0.01331  -0.0528   1.0000   0.2087
  -4.750  -0.3155   0.02343   0.01280  -0.0531   1.0000   0.2280
  -4.500  -0.2873   0.02292   0.01234  -0.0535   1.0000   0.2485
  -4.250  -0.2592   0.02245   0.01190  -0.0538   1.0000   0.2704
  -4.000  -0.2312   0.02202   0.01150  -0.0541   1.0000   0.2927
  -3.750  -0.2039   0.02165   0.01121  -0.0542   1.0000   0.3131
  -3.500  -0.1769   0.02130   0.01093  -0.0543   1.0000   0.3337
  -3.250  -0.1509   0.02099   0.01067  -0.0543   1.0000   0.3542
  -3.000  -0.1267   0.02075   0.01047  -0.0542   1.0000   0.3746
  -2.750  -0.1049   0.02062   0.01039  -0.0538   0.9998   0.3942
  -2.500  -0.0601   0.02039   0.01021  -0.0573   0.9756   0.4198
  -2.250  -0.0154   0.02017   0.00998  -0.0606   0.9524   0.4481
  -2.000   0.0254   0.02000   0.00986  -0.0629   0.9283   0.4756
  -1.750   0.0624   0.01988   0.00975  -0.0643   0.9036   0.5038
  -1.500   0.0948   0.01979   0.00966  -0.0646   0.8788   0.5297
  -1.250   0.1243   0.01972   0.00958  -0.0642   0.8554   0.5543
  -1.000   0.1511   0.01966   0.00954  -0.0634   0.8320   0.5792
  -0.750   0.1770   0.01961   0.00952  -0.0622   0.8105   0.6071
  -0.500   0.2022   0.01956   0.00949  -0.0609   0.7904   0.6381
  -0.250   0.2262   0.01948   0.00948  -0.0593   0.7715   0.6714
   0.000   0.2492   0.01938   0.00947  -0.0575   0.7532   0.7090
   0.250   0.2709   0.01923   0.00943  -0.0553   0.7354   0.7540
   0.500   0.2909   0.01900   0.00932  -0.0526   0.7179   0.8157
   0.750   0.3176   0.01860   0.00901  -0.0514   0.6998   1.0000
   1.000   0.3489   0.01885   0.00904  -0.0521   0.6825   1.0000
   1.250   0.3792   0.01913   0.00913  -0.0526   0.6658   1.0000
   1.500   0.4090   0.01943   0.00928  -0.0529   0.6498   1.0000
   1.750   0.4385   0.01974   0.00947  -0.0531   0.6342   1.0000
   2.000   0.4678   0.02006   0.00969  -0.0533   0.6190   1.0000
   2.250   0.4968   0.02040   0.00994  -0.0533   0.6044   1.0000
   2.500   0.5255   0.02074   0.01019  -0.0533   0.5898   1.0000
   2.750   0.5539   0.02108   0.01044  -0.0531   0.5756   1.0000
   3.000   0.5822   0.02143   0.01073  -0.0530   0.5611   1.0000
   3.250   0.6106   0.02181   0.01108  -0.0529   0.5454   1.0000
   3.500   0.6388   0.02219   0.01144  -0.0528   0.5299   1.0000
   3.750   0.6668   0.02258   0.01183  -0.0527   0.5143   1.0000
   4.000   0.6947   0.02298   0.01221  -0.0525   0.4988   1.0000
   4.250   0.7224   0.02338   0.01261  -0.0523   0.4834   1.0000
   4.500   0.7499   0.02380   0.01304  -0.0521   0.4682   1.0000
   4.750   0.7773   0.02423   0.01347  -0.0518   0.4531   1.0000
   5.000   0.8044   0.02466   0.01391  -0.0515   0.4378   1.0000
   5.250   0.8314   0.02511   0.01438  -0.0512   0.4224   1.0000
   5.500   0.8582   0.02557   0.01486  -0.0509   0.4067   1.0000
   5.750   0.8847   0.02606   0.01538  -0.0505   0.3906   1.0000
   6.000   0.9109   0.02659   0.01596  -0.0502   0.3740   1.0000
   6.250   0.9367   0.02715   0.01658  -0.0498   0.3566   1.0000
   6.500   0.9621   0.02774   0.01725  -0.0495   0.3386   1.0000
   6.750   0.9869   0.02837   0.01797  -0.0491   0.3199   1.0000
   7.000   1.0111   0.02903   0.01868  -0.0486   0.3007   1.0000
   7.250   1.0347   0.02970   0.01937  -0.0481   0.2815   1.0000
   7.500   1.0575   0.03044   0.02009  -0.0475   0.2625   1.0000
   7.750   1.0793   0.03135   0.02104  -0.0470   0.2427   1.0000
   8.000   1.1002   0.03236   0.02214  -0.0465   0.2225   1.0000
   8.250   1.1200   0.03344   0.02323  -0.0459   0.2040   1.0000
   8.500   1.1384   0.03468   0.02447  -0.0452   0.1869   1.0000
   8.750   1.1555   0.03608   0.02587  -0.0444   0.1712   1.0000
   9.000   1.1713   0.03766   0.02746  -0.0436   0.1568   1.0000
   9.250   1.1859   0.03938   0.02925  -0.0427   0.1442   1.0000
   9.500   1.1991   0.04121   0.03118  -0.0417   0.1333   1.0000
   9.750   1.2113   0.04306   0.03301  -0.0407   0.1247   1.0000
  10.000   1.2220   0.04508   0.03516  -0.0396   0.1165   1.0000
  10.250   1.2317   0.04719   0.03736  -0.0385   0.1101   1.0000
  10.500   1.2394   0.04941   0.03975  -0.0374   0.1043   1.0000
  10.750   1.2470   0.05151   0.04182  -0.0362   0.0999   1.0000
  11.000   1.2472   0.05431   0.04493  -0.0348   0.0958   1.0000
  11.250   1.2483   0.05699   0.04776  -0.0339   0.0924   1.0000
  11.500   1.2545   0.05923   0.04994  -0.0331   0.0894   1.0000
  11.750   1.2486   0.06312   0.05413  -0.0331   0.0869   1.0000
  12.000   1.2395   0.06761   0.05892  -0.0339   0.0848   1.0000
  12.250   1.2298   0.07236   0.06391  -0.0352   0.0829   1.0000
  12.500   1.2199   0.07734   0.06909  -0.0368   0.0814   1.0000
  12.750   1.2112   0.08232   0.07420  -0.0385   0.0800   1.0000
  13.000   1.2177   0.08488   0.07674  -0.0383   0.0780   1.0000
  13.250   1.1886   0.09361   0.08575  -0.0431   0.0777   1.0000
  13.500   1.1523   0.10449   0.09690  -0.0496   0.0777   1.0000
  13.750   1.1041   0.11918   0.11184  -0.0589   0.0780   1.0000
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