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AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AG03 (flat aft bottom) (ag03-il)
Reynolds number: 200,000
Max Cl/Cd: 60.57 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag03-il-200000.txt
Download as CSV file: xf-ag03-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG03 (flat aft bottom)                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5353   0.10285   0.09944   0.0043   1.0000   0.0276
  -8.000  -0.5305   0.09893   0.09557   0.0008   1.0000   0.0277
  -7.750  -0.5322   0.09233   0.08903  -0.0016   1.0000   0.0282
  -7.500  -0.5273   0.08855   0.08526   0.0012   1.0000   0.0293
  -7.250  -0.5191   0.08502   0.08174   0.0000   1.0000   0.0303
  -7.000  -0.5096   0.08111   0.07785  -0.0031   1.0000   0.0314
  -6.750  -0.4982   0.07698   0.07372  -0.0071   1.0000   0.0332
  -6.500  -0.4833   0.07231   0.06902  -0.0129   1.0000   0.0359
  -6.250  -0.4511   0.06666   0.06311  -0.0254   1.0000   0.0390
  -6.000  -0.4393   0.05971   0.05604  -0.0293   1.0000   0.0400
  -5.750  -0.4309   0.05675   0.05322  -0.0275   1.0000   0.0419
  -5.500  -0.4135   0.05337   0.04978  -0.0287   1.0000   0.0442
  -5.250  -0.3919   0.04937   0.04562  -0.0311   1.0000   0.0476
  -5.000  -0.3634   0.04393   0.03959  -0.0351   1.0000   0.0528
  -4.750  -0.3467   0.04056   0.03632  -0.0350   1.0000   0.0547
  -4.500  -0.3259   0.03791   0.03356  -0.0351   1.0000   0.0582
  -4.250  -0.3004   0.03432   0.02946  -0.0360   1.0000   0.0666
  -4.000  -0.2797   0.03170   0.02685  -0.0357   1.0000   0.0695
  -3.750  -0.2554   0.02928   0.02402  -0.0355   1.0000   0.0802
  -3.500  -0.2198   0.02114   0.01458  -0.0328   1.0000   0.0283
  -3.250  -0.1949   0.01867   0.01184  -0.0319   1.0000   0.0263
  -3.000  -0.1694   0.01653   0.00937  -0.0310   1.0000   0.0253
  -2.750  -0.1436   0.01492   0.00754  -0.0301   1.0000   0.0252
  -2.500  -0.1181   0.01366   0.00616  -0.0292   1.0000   0.0262
  -2.250  -0.0926   0.01234   0.00477  -0.0285   1.0000   0.0297
  -2.000  -0.0665   0.01137   0.00391  -0.0281   1.0000   0.0580
  -1.750  -0.0401   0.01026   0.00338  -0.0281   1.0000   0.1796
  -1.500  -0.0149   0.00855   0.00318  -0.0286   1.0000   0.5573
  -1.250   0.0150   0.00749   0.00312  -0.0276   1.0000   1.0000
  -1.000   0.0389   0.00758   0.00302  -0.0270   1.0000   1.0000
  -0.750   0.0627   0.00771   0.00301  -0.0266   1.0000   1.0000
  -0.500   0.1120   0.00775   0.00289  -0.0312   0.9885   1.0000
  -0.250   0.1607   0.00775   0.00276  -0.0356   0.9763   1.0000
   0.000   0.2061   0.00772   0.00265  -0.0391   0.9616   1.0000
   0.250   0.2475   0.00768   0.00253  -0.0416   0.9436   1.0000
   0.500   0.2814   0.00765   0.00243  -0.0424   0.9197   1.0000
   0.750   0.3102   0.00765   0.00236  -0.0419   0.8926   1.0000
   1.000   0.3355   0.00769   0.00230  -0.0407   0.8632   1.0000
   1.250   0.3599   0.00776   0.00225  -0.0394   0.8324   1.0000
   1.500   0.3842   0.00788   0.00224  -0.0381   0.7998   1.0000
   1.750   0.4087   0.00802   0.00226  -0.0369   0.7658   1.0000
   2.000   0.4335   0.00820   0.00228  -0.0359   0.7314   1.0000
   2.250   0.4586   0.00841   0.00233  -0.0349   0.6956   1.0000
   2.500   0.4838   0.00863   0.00241  -0.0341   0.6588   1.0000
   2.750   0.5091   0.00889   0.00250  -0.0333   0.6211   1.0000
   3.000   0.5344   0.00916   0.00265  -0.0326   0.5820   1.0000
   3.250   0.5598   0.00946   0.00279  -0.0320   0.5418   1.0000
   3.500   0.5853   0.00978   0.00296  -0.0315   0.5011   1.0000
   3.750   0.6106   0.01014   0.00316  -0.0310   0.4599   1.0000
   4.000   0.6360   0.01052   0.00342  -0.0305   0.4195   1.0000
   4.250   0.6614   0.01092   0.00369  -0.0301   0.3808   1.0000
   4.500   0.6868   0.01135   0.00399  -0.0297   0.3439   1.0000
   4.750   0.7122   0.01179   0.00432  -0.0293   0.3086   1.0000
   5.000   0.7374   0.01227   0.00472  -0.0290   0.2762   1.0000
   5.250   0.7628   0.01275   0.00513  -0.0287   0.2438   1.0000
   5.500   0.7878   0.01328   0.00558  -0.0283   0.2131   1.0000
   5.750   0.8126   0.01388   0.00609  -0.0280   0.1846   1.0000
   6.000   0.8371   0.01455   0.00666  -0.0276   0.1567   1.0000
   6.250   0.8615   0.01526   0.00737  -0.0272   0.1321   1.0000
   6.500   0.8852   0.01613   0.00819  -0.0267   0.1125   1.0000
   6.750   0.9092   0.01693   0.00900  -0.0262   0.0959   1.0000
   7.000   0.9326   0.01790   0.01000  -0.0256   0.0836   1.0000
   7.250   0.9555   0.01897   0.01111  -0.0249   0.0731   1.0000
   7.500   0.9774   0.02025   0.01237  -0.0242   0.0637   1.0000
   7.750   1.0010   0.02116   0.01350  -0.0236   0.0561   1.0000
   8.000   1.0224   0.02265   0.01511  -0.0228   0.0489   1.0000
   8.250   1.0441   0.02396   0.01650  -0.0220   0.0430   1.0000
   8.500   1.0645   0.02581   0.01860  -0.0210   0.0375   1.0000
   8.750   1.0851   0.02728   0.02023  -0.0202   0.0330   1.0000
   9.000   1.1007   0.03041   0.02366  -0.0190   0.0293   1.0000
   9.250   1.1194   0.03197   0.02557  -0.0179   0.0256   1.0000
   9.500   1.1349   0.03417   0.02798  -0.0168   0.0231   1.0000
   9.750   1.1389   0.03916   0.03336  -0.0152   0.0213   1.0000
  10.000   1.1461   0.04177   0.03652  -0.0137   0.0195   1.0000
  10.250   1.1490   0.04503   0.04021  -0.0122   0.0181   1.0000
  10.500   1.1425   0.04927   0.04486  -0.0107   0.0176   1.0000
  10.750   1.1283   0.05342   0.04935  -0.0091   0.0174   1.0000
  11.000   1.1093   0.05797   0.05416  -0.0091   0.0174   1.0000
  11.250   1.0886   0.06372   0.06016  -0.0119   0.0177   1.0000
  11.500   1.0675   0.07101   0.06765  -0.0175   0.0181   1.0000
  11.750   1.0461   0.07985   0.07661  -0.0249   0.0186   1.0000
  12.000   1.0226   0.09007   0.08693  -0.0326   0.0197   1.0000
  12.250   0.9395   0.12131   0.11821  -0.0506   0.0280   1.0000
  12.500   0.9263   0.12973   0.12658  -0.0544   0.0287   1.0000
  12.750   0.9169   0.13718   0.13399  -0.0575   0.0293   1.0000
  13.000   0.9103   0.14379   0.14057  -0.0598   0.0299   1.0000
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