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NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il)
Reynolds number: 200,000
Max Cl/Cd: 53.29 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames03-il-200000-n5.txt
Download as CSV file: xf-ames03-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/AMES A-03 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6928   0.10112   0.09800   0.0197   0.9027   0.0160
 -10.000  -0.7005   0.09432   0.09122   0.0155   0.9001   0.0160
  -9.750  -0.7169   0.08363   0.08054   0.0075   0.8974   0.0159
  -9.250  -0.7545   0.06596   0.06259  -0.0065   0.8904   0.0156
  -9.000  -0.7776   0.05710   0.05334  -0.0085   0.8870   0.0157
  -8.750  -0.7944   0.04895   0.04460  -0.0085   0.8841   0.0159
  -8.500  -0.7893   0.04550   0.04087  -0.0078   0.8818   0.0162
  -8.250  -0.7773   0.04210   0.03716  -0.0078   0.8791   0.0165
  -8.000  -0.7639   0.03838   0.03302  -0.0075   0.8765   0.0168
  -7.750  -0.7471   0.03532   0.02957  -0.0071   0.8741   0.0171
  -7.500  -0.7280   0.03265   0.02651  -0.0066   0.8721   0.0175
  -7.250  -0.7074   0.03020   0.02365  -0.0061   0.8702   0.0180
  -7.000  -0.6855   0.02804   0.02109  -0.0054   0.8685   0.0187
  -6.750  -0.6620   0.02619   0.01887  -0.0049   0.8669   0.0195
  -6.500  -0.6342   0.02482   0.01713  -0.0051   0.8644   0.0207
  -6.250  -0.6079   0.02344   0.01569  -0.0054   0.8621   0.0218
  -6.000  -0.5810   0.02242   0.01455  -0.0055   0.8601   0.0227
  -5.750  -0.5542   0.02141   0.01341  -0.0054   0.8582   0.0237
  -5.500  -0.5276   0.02046   0.01233  -0.0053   0.8565   0.0249
  -5.250  -0.5011   0.01967   0.01141  -0.0050   0.8550   0.0263
  -5.000  -0.4755   0.01884   0.01056  -0.0048   0.8535   0.0283
  -4.750  -0.4486   0.01827   0.00995  -0.0048   0.8519   0.0304
  -4.500  -0.4191   0.01762   0.00924  -0.0054   0.8496   0.0327
  -4.250  -0.3904   0.01699   0.00856  -0.0058   0.8474   0.0353
  -4.000  -0.3619   0.01651   0.00810  -0.0062   0.8456   0.0397
  -3.750  -0.3334   0.01610   0.00762  -0.0064   0.8438   0.0444
  -3.500  -0.3054   0.01564   0.00717  -0.0066   0.8422   0.0515
  -3.250  -0.2775   0.01525   0.00680  -0.0068   0.8406   0.0630
  -3.000  -0.2510   0.01486   0.00644  -0.0065   0.8387   0.0816
  -2.750  -0.2231   0.01435   0.00613  -0.0068   0.8351   0.1233
  -2.500  -0.1952   0.01371   0.00584  -0.0072   0.8304   0.2040
  -2.250  -0.1707   0.01274   0.00550  -0.0070   0.8265   0.3589
  -2.000  -0.1493   0.01163   0.00530  -0.0058   0.8236   0.5797
  -1.750  -0.1249   0.01118   0.00536  -0.0047   0.8196   0.7076
  -1.500  -0.0998   0.01104   0.00539  -0.0036   0.8151   0.7746
  -1.250  -0.0767   0.01094   0.00536  -0.0018   0.8112   0.8191
  -1.000  -0.0557   0.01086   0.00529   0.0005   0.8078   0.8542
  -0.750  -0.0316   0.01085   0.00532   0.0020   0.8018   0.8872
  -0.500  -0.0105   0.01078   0.00525   0.0044   0.7967   0.9167
  -0.250   0.0129   0.01064   0.00507   0.0062   0.7928   0.9358
   0.000   0.0437   0.01057   0.00496   0.0057   0.7852   0.9460
   0.250   0.0709   0.01036   0.00468   0.0063   0.7784   0.9562
   0.500   0.1043   0.01022   0.00450   0.0054   0.7675   0.9635
   0.750   0.1361   0.01006   0.00430   0.0048   0.7566   0.9718
   1.000   0.1703   0.00991   0.00410   0.0037   0.7441   0.9781
   1.250   0.2046   0.00979   0.00395   0.0025   0.7284   0.9849
   1.500   0.2400   0.00967   0.00379   0.0010   0.7076   0.9906
   1.750   0.2741   0.00954   0.00357  -0.0001   0.6696   0.9966
   2.000   0.3013   0.01001   0.00302   0.0002   0.4676   1.0000
   2.250   0.3302   0.01079   0.00325  -0.0010   0.3593   1.0000
   2.500   0.3571   0.01122   0.00342  -0.0015   0.3152   1.0000
   2.750   0.3840   0.01155   0.00358  -0.0018   0.2901   1.0000
   3.000   0.4113   0.01185   0.00376  -0.0021   0.2733   1.0000
   3.250   0.4388   0.01212   0.00394  -0.0024   0.2612   1.0000
   3.500   0.4667   0.01240   0.00417  -0.0028   0.2522   1.0000
   3.750   0.4946   0.01268   0.00439  -0.0032   0.2434   1.0000
   4.000   0.5226   0.01296   0.00463  -0.0035   0.2358   1.0000
   4.250   0.5505   0.01324   0.00490  -0.0039   0.2288   1.0000
   4.500   0.5784   0.01355   0.00517  -0.0042   0.2224   1.0000
   4.750   0.6064   0.01382   0.00545  -0.0045   0.2157   1.0000
   5.000   0.6340   0.01419   0.00577  -0.0048   0.2096   1.0000
   5.250   0.6620   0.01443   0.00607  -0.0051   0.2032   1.0000
   5.500   0.6896   0.01476   0.00638  -0.0053   0.1971   1.0000
   5.750   0.7172   0.01507   0.00672  -0.0056   0.1910   1.0000
   6.000   0.7448   0.01535   0.00706  -0.0058   0.1842   1.0000
   6.250   0.7721   0.01570   0.00741  -0.0061   0.1781   1.0000
   6.500   0.7996   0.01597   0.00777  -0.0063   0.1711   1.0000
   6.750   0.8266   0.01633   0.00813  -0.0065   0.1646   1.0000
   7.000   0.8539   0.01661   0.00852  -0.0067   0.1570   1.0000
   7.250   0.8807   0.01697   0.00889  -0.0069   0.1498   1.0000
   7.500   0.9075   0.01729   0.00927  -0.0071   0.1405   1.0000
   7.750   0.9340   0.01764   0.00970  -0.0072   0.1306   1.0000
   8.000   0.9601   0.01804   0.01012  -0.0074   0.1197   1.0000
   8.250   0.9858   0.01850   0.01059  -0.0075   0.1080   1.0000
   8.500   1.0109   0.01903   0.01111  -0.0075   0.0959   1.0000
   8.750   1.0354   0.01964   0.01174  -0.0075   0.0842   1.0000
   9.000   1.0592   0.02035   0.01244  -0.0075   0.0731   1.0000
   9.250   1.0824   0.02110   0.01321  -0.0073   0.0627   1.0000
   9.500   1.1052   0.02191   0.01407  -0.0072   0.0537   1.0000
   9.750   1.1270   0.02281   0.01502  -0.0069   0.0462   1.0000
  10.000   1.1474   0.02385   0.01610  -0.0066   0.0398   1.0000
  10.250   1.1676   0.02484   0.01718  -0.0062   0.0349   1.0000
  10.500   1.1854   0.02605   0.01845  -0.0056   0.0316   1.0000
  10.750   1.2032   0.02714   0.01970  -0.0049   0.0290   1.0000
  11.000   1.2189   0.02839   0.02104  -0.0042   0.0268   1.0000
  11.250   1.2304   0.02993   0.02267  -0.0033   0.0250   1.0000
  11.500   1.2424   0.03123   0.02416  -0.0023   0.0236   1.0000
  11.750   1.2505   0.03267   0.02575  -0.0008   0.0224   1.0000
  12.000   1.2572   0.03430   0.02752   0.0005   0.0215   1.0000
  12.250   1.2621   0.03613   0.02947   0.0017   0.0208   1.0000
  12.500   1.2641   0.03826   0.03172   0.0028   0.0201   1.0000
  12.750   1.2622   0.04082   0.03439   0.0039   0.0196   1.0000
  13.000   1.2618   0.04338   0.03711   0.0046   0.0191   1.0000
  13.250   1.2615   0.04606   0.03997   0.0051   0.0187   1.0000
  13.500   1.2591   0.04907   0.04318   0.0052   0.0183   1.0000
  13.750   1.2547   0.05249   0.04678   0.0049   0.0178   1.0000
  14.000   1.2482   0.05639   0.05086   0.0041   0.0175   1.0000
  14.250   1.2396   0.06090   0.05555   0.0025   0.0171   1.0000
  14.500   1.2287   0.06620   0.06106   0.0001   0.0169   1.0000
  14.750   1.2159   0.07242   0.06747  -0.0034   0.0167   1.0000
  15.000   1.2014   0.07955   0.07478  -0.0077   0.0166   1.0000
  15.250   1.1853   0.08726   0.08266  -0.0123   0.0165   1.0000
  15.500   1.1679   0.09526   0.09083  -0.0169   0.0165   1.0000
  15.750   1.1496   0.10337   0.09907  -0.0214   0.0164   1.0000
  16.000   1.1308   0.11155   0.10738  -0.0259   0.0164   1.0000
  16.250   1.1119   0.11988   0.11584  -0.0304   0.0164   1.0000
  16.500   1.0923   0.12848   0.12458  -0.0352   0.0164   1.0000
  16.750   1.0711   0.13794   0.13417  -0.0405   0.0164   1.0000
  17.000   1.0442   0.14948   0.14586  -0.0471   0.0166   1.0000
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