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NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il)
Reynolds number: 200,000
Max Cl/Cd: 50.94 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ames03-il-200000.txt
Download as CSV file: xf-ames03-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5914   0.08844   0.08549  -0.0173   1.0000   0.0545
  -9.000  -0.6098   0.08102   0.07791  -0.0278   0.9990   0.0549
  -8.750  -0.6196   0.07627   0.07286  -0.0327   0.9864   0.0553
  -8.500  -0.6239   0.06796   0.06448  -0.0355   0.9820   0.0563
  -8.250  -0.6010   0.06582   0.06255  -0.0346   0.9796   0.0583
  -8.000  -0.5893   0.06301   0.05968  -0.0355   0.9757   0.0607
  -7.750  -0.5822   0.05903   0.05550  -0.0373   0.9715   0.0638
  -7.500  -0.5888   0.05381   0.04948  -0.0388   0.9653   0.0693
  -7.250  -0.5714   0.04989   0.04567  -0.0391   0.9623   0.0709
  -7.000  -0.5531   0.04727   0.04302  -0.0393   0.9596   0.0732
  -6.750  -0.5453   0.03553   0.02957  -0.0368   0.9555   0.0446
  -6.500  -0.5236   0.03180   0.02566  -0.0366   0.9530   0.0418
  -6.250  -0.5018   0.02903   0.02246  -0.0359   0.9504   0.0417
  -6.000  -0.4771   0.02718   0.02022  -0.0355   0.9478   0.0427
  -5.750  -0.4507   0.02507   0.01776  -0.0353   0.9452   0.0430
  -5.500  -0.4234   0.02357   0.01594  -0.0352   0.9429   0.0436
  -5.250  -0.3970   0.02141   0.01358  -0.0350   0.9408   0.0450
  -5.000  -0.3708   0.02036   0.01256  -0.0350   0.9388   0.0486
  -4.750  -0.3443   0.01963   0.01176  -0.0348   0.9369   0.0519
  -4.500  -0.3163   0.01888   0.01090  -0.0348   0.9349   0.0548
  -4.250  -0.2901   0.01771   0.00979  -0.0349   0.9325   0.0603
  -4.000  -0.2624   0.01726   0.00930  -0.0351   0.9304   0.0677
  -3.750  -0.2366   0.01648   0.00860  -0.0351   0.9284   0.0781
  -3.500  -0.2107   0.01591   0.00808  -0.0350   0.9263   0.0980
  -3.250  -0.1890   0.01504   0.00771  -0.0341   0.9232   0.1799
  -3.000  -0.1720   0.01302   0.00738  -0.0335   0.9186   0.5467
  -2.750  -0.1545   0.01264   0.00769  -0.0305   0.9135   0.7238
  -2.500  -0.1365   0.01287   0.00806  -0.0272   0.9090   0.7943
  -2.250  -0.1143   0.01303   0.00825  -0.0254   0.9039   0.8398
  -2.000  -0.0952   0.01328   0.00850  -0.0225   0.8991   0.8713
  -1.750  -0.0778   0.01358   0.00875  -0.0192   0.8947   0.8976
  -1.500  -0.0554   0.01376   0.00889  -0.0172   0.8891   0.9197
  -1.250  -0.0327   0.01395   0.00902  -0.0149   0.8844   0.9427
  -1.000   0.0058   0.01412   0.00912  -0.0157   0.8796   0.9604
  -0.750   0.0670   0.01421   0.00913  -0.0214   0.8738   0.9753
  -0.500   0.1071   0.01414   0.00898  -0.0230   0.8682   0.9854
  -0.250   0.1467   0.01395   0.00874  -0.0253   0.8592   0.9920
   0.000   0.1786   0.01367   0.00840  -0.0253   0.8508   0.9990
   0.250   0.1994   0.01336   0.00805  -0.0238   0.8409   1.0000
   0.500   0.2176   0.01309   0.00774  -0.0219   0.8322   1.0000
   0.750   0.2323   0.01273   0.00734  -0.0188   0.8243   1.0000
   1.000   0.2523   0.01244   0.00703  -0.0172   0.8142   1.0000
   1.250   0.2654   0.01201   0.00655  -0.0136   0.8075   1.0000
   1.500   0.2870   0.01170   0.00625  -0.0122   0.7960   1.0000
   1.750   0.3059   0.01132   0.00585  -0.0100   0.7843   1.0000
   2.000   0.3244   0.01089   0.00540  -0.0075   0.7711   1.0000
   2.250   0.3444   0.01045   0.00495  -0.0053   0.7538   1.0000
   2.500   0.3663   0.01003   0.00451  -0.0035   0.7266   1.0000
   2.750   0.3873   0.00957   0.00386  -0.0011   0.6454   1.0000
   3.000   0.4111   0.01090   0.00367  -0.0008   0.3824   1.0000
   3.250   0.4395   0.01159   0.00402  -0.0017   0.3374   1.0000
   3.500   0.4673   0.01212   0.00434  -0.0022   0.3164   1.0000
   3.750   0.4950   0.01258   0.00466  -0.0026   0.3011   1.0000
   4.000   0.5228   0.01296   0.00497  -0.0029   0.2888   1.0000
   4.250   0.5504   0.01336   0.00533  -0.0031   0.2785   1.0000
   4.500   0.5777   0.01385   0.00570  -0.0033   0.2693   1.0000
   4.750   0.6056   0.01420   0.00605  -0.0036   0.2603   1.0000
   5.000   0.6329   0.01468   0.00647  -0.0037   0.2522   1.0000
   5.250   0.6606   0.01507   0.00687  -0.0040   0.2441   1.0000
   5.500   0.6879   0.01556   0.00735  -0.0041   0.2366   1.0000
   5.750   0.7155   0.01595   0.00774  -0.0044   0.2286   1.0000
   6.000   0.7428   0.01644   0.00827  -0.0045   0.2212   1.0000
   6.250   0.7703   0.01683   0.00868  -0.0047   0.2133   1.0000
   6.500   0.7974   0.01733   0.00922  -0.0049   0.2059   1.0000
   6.750   0.8247   0.01769   0.00961  -0.0051   0.1978   1.0000
   7.000   0.8517   0.01816   0.01017  -0.0053   0.1899   1.0000
   7.250   0.8786   0.01851   0.01052  -0.0055   0.1816   1.0000
   7.500   0.9054   0.01882   0.01097  -0.0057   0.1721   1.0000
   7.750   0.9318   0.01914   0.01133  -0.0059   0.1627   1.0000
   8.000   0.9580   0.01935   0.01157  -0.0062   0.1524   1.0000
   8.250   0.9842   0.01956   0.01192  -0.0064   0.1409   1.0000
   8.500   1.0097   0.01989   0.01233  -0.0065   0.1290   1.0000
   8.750   1.0346   0.02031   0.01282  -0.0066   0.1165   1.0000
   9.000   1.0587   0.02084   0.01338  -0.0066   0.1031   1.0000
   9.250   1.0816   0.02155   0.01409  -0.0065   0.0890   1.0000
   9.500   1.1025   0.02257   0.01508  -0.0061   0.0756   1.0000
   9.750   1.1222   0.02377   0.01629  -0.0056   0.0642   1.0000
  10.000   1.1407   0.02510   0.01770  -0.0050   0.0557   1.0000
  10.250   1.1555   0.02687   0.01944  -0.0040   0.0501   1.0000
  10.500   1.1737   0.02811   0.02087  -0.0032   0.0459   1.0000
  10.750   1.1888   0.02955   0.02234  -0.0023   0.0425   1.0000
  11.000   1.2016   0.03159   0.02447  -0.0012   0.0398   1.0000
  11.250   1.2155   0.03313   0.02623  -0.0001   0.0377   1.0000
  11.500   1.2271   0.03482   0.02806   0.0010   0.0360   1.0000
  11.750   1.2355   0.03655   0.02991   0.0025   0.0346   1.0000
  12.000   1.2428   0.03872   0.03215   0.0039   0.0334   1.0000
  12.250   1.2449   0.04232   0.03595   0.0055   0.0323   1.0000
  12.500   1.2453   0.04444   0.03834   0.0070   0.0317   1.0000
  12.750   1.2435   0.04695   0.04111   0.0083   0.0310   1.0000
  13.000   1.2393   0.04985   0.04426   0.0093   0.0304   1.0000
  13.250   1.2326   0.05313   0.04778   0.0099   0.0298   1.0000
  13.500   1.2231   0.05690   0.05179   0.0101   0.0294   1.0000
  13.750   1.2102   0.06129   0.05642   0.0096   0.0292   1.0000
  14.000   1.1941   0.06642   0.06178   0.0082   0.0290   1.0000
  14.250   1.1743   0.07256   0.06817   0.0056   0.0290   1.0000
  14.500   1.1500   0.08023   0.07609   0.0012   0.0292   1.0000
  14.750   1.1201   0.09018   0.08629  -0.0057   0.0295   1.0000
  15.000   1.0822   0.10325   0.09960  -0.0150   0.0302   1.0000
  15.250   1.0331   0.11968   0.11621  -0.0257   0.0314   1.0000
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