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FX 69-PR-281 (fx69pr281-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 69-PR-281 (fx69pr281-il)
Reynolds number: 200,000
Max Cl/Cd: 41.14 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx69pr281-il-200000.txt
Download as CSV file: xf-fx69pr281-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 69-PR-281                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.4131   0.09977   0.09475  -0.1462   0.8196   0.1686
 -10.250   0.4399   0.09848   0.09338  -0.1461   0.7992   0.1703
 -10.000   0.3867   0.09081   0.08553  -0.1518   0.7925   0.1674
  -9.750   0.4040   0.08903   0.08370  -0.1510   0.7754   0.1671
  -9.500   0.4209   0.08665   0.08118  -0.1517   0.7608   0.1667
  -9.250   0.4266   0.08406   0.07854  -0.1515   0.7466   0.1663
  -9.000  -0.0368   0.03495   0.02885  -0.1719   0.7607   0.1913
  -8.000  -0.0395   0.03199   0.02567  -0.1626   0.7161   0.1991
  -7.750  -0.0705   0.02941   0.02254  -0.1600   0.7072   0.2024
  -7.500  -0.0593   0.02883   0.02202  -0.1577   0.6970   0.2044
  -7.250  -0.0310   0.02901   0.02226  -0.1567   0.6867   0.2062
  -7.000  -0.0010   0.02916   0.02236  -0.1565   0.6771   0.2085
  -6.750   0.0119   0.02891   0.02213  -0.1543   0.6672   0.2109
  -6.500   0.0227   0.02812   0.02115  -0.1528   0.6583   0.2142
  -6.250   0.0381   0.02708   0.01973  -0.1527   0.6503   0.2177
  -6.000   0.0564   0.02683   0.01963  -0.1507   0.6417   0.2195
  -5.750   0.0789   0.02676   0.01961  -0.1493   0.6330   0.2215
  -5.500   0.1056   0.02662   0.01937  -0.1490   0.6252   0.2240
  -5.250   0.1250   0.02631   0.01902  -0.1478   0.6176   0.2268
  -5.000   0.1416   0.02571   0.01829  -0.1465   0.6096   0.2298
  -4.750   0.1622   0.02509   0.01739  -0.1460   0.6022   0.2328
  -4.500   0.1896   0.02470   0.01702  -0.1458   0.5949   0.2354
  -4.250   0.2087   0.02457   0.01697  -0.1440   0.5869   0.2375
  -4.000   0.2311   0.02437   0.01675  -0.1428   0.5787   0.2401
  -3.750   0.2600   0.02421   0.01641  -0.1430   0.5710   0.2434
  -3.500   0.2784   0.02390   0.01605  -0.1415   0.5632   0.2465
  -3.250   0.2992   0.02363   0.01562  -0.1404   0.5552   0.2494
  -3.000   0.3246   0.02306   0.01499  -0.1400   0.5477   0.2524
  -2.750   0.3486   0.02299   0.01495  -0.1391   0.5401   0.2550
  -2.500   0.3681   0.02289   0.01489  -0.1374   0.5320   0.2578
  -2.250   0.3923   0.02277   0.01467  -0.1366   0.5243   0.2612
  -2.000   0.4191   0.02268   0.01444  -0.1364   0.5165   0.2648
  -1.750   0.4374   0.02251   0.01420  -0.1347   0.5082   0.2676
  -1.500   0.4600   0.02211   0.01371  -0.1338   0.5004   0.2710
  -1.250   0.4869   0.02209   0.01365  -0.1334   0.4927   0.2741
  -1.000   0.5040   0.02204   0.01367  -0.1313   0.4849   0.2770
  -0.750   0.5258   0.02199   0.01357  -0.1300   0.4773   0.2803
  -0.500   0.5558   0.02208   0.01347  -0.1303   0.4696   0.2843
  -0.250   0.5705   0.02201   0.01341  -0.1279   0.4621   0.2875
   0.000   0.5894   0.02189   0.01320  -0.1263   0.4548   0.2905
   0.250   0.6183   0.02179   0.01301  -0.1264   0.4479   0.2944
   0.500   0.6312   0.02177   0.01308  -0.1236   0.4413   0.2974
   0.750   0.6480   0.02179   0.01311  -0.1216   0.4346   0.3009
   1.000   0.6716   0.02186   0.01307  -0.1207   0.4285   0.3050
   1.250   0.6950   0.02200   0.01313  -0.1199   0.4225   0.3089
   1.500   0.7117   0.02211   0.01321  -0.1179   0.4164   0.3119
   1.750   0.7322   0.02202   0.01311  -0.1167   0.4109   0.3163
   2.000   0.7615   0.02220   0.01319  -0.1169   0.4053   0.3209
   2.250   0.7786   0.02242   0.01348  -0.1150   0.4002   0.3249
   2.500   0.7967   0.02264   0.01372  -0.1134   0.3950   0.3295
   2.750   0.8182   0.02286   0.01387  -0.1123   0.3903   0.3342
   3.000   0.8479   0.02302   0.01389  -0.1126   0.3856   0.3395
   3.250   0.8684   0.02327   0.01422  -0.1115   0.3813   0.3449
   3.500   0.8846   0.02356   0.01459  -0.1097   0.3769   0.3501
   3.750   0.9043   0.02384   0.01486  -0.1084   0.3726   0.3562
   4.000   0.9282   0.02413   0.01505  -0.1078   0.3687   0.3622
   4.250   0.9655   0.02436   0.01518  -0.1093   0.3645   0.3707
   4.500   0.9764   0.02474   0.01571  -0.1068   0.3613   0.3770
   4.750   0.9917   0.02513   0.01617  -0.1050   0.3575   0.3845
   5.000   1.0107   0.02552   0.01652  -0.1038   0.3538   0.3920
   5.250   1.0330   0.02574   0.01679  -0.1031   0.3503   0.4016
   5.500   1.0672   0.02610   0.01706  -0.1041   0.3466   0.4128
   5.750   1.0858   0.02667   0.01764  -0.1029   0.3436   0.4227
   6.000   1.0959   0.02714   0.01828  -0.1007   0.3405   0.4331
   6.250   1.1101   0.02766   0.01890  -0.0990   0.3373   0.4441
   6.500   1.1283   0.02816   0.01936  -0.0978   0.3340   0.4558
   6.750   1.1509   0.02848   0.01974  -0.0973   0.3309   0.4692
   7.000   1.1889   0.02890   0.02002  -0.0987   0.3275   0.4857
   7.250   1.1969   0.02960   0.02088  -0.0964   0.3248   0.4976
   7.500   1.2016   0.03038   0.02181  -0.0938   0.3220   0.5098
   7.750   1.2119   0.03112   0.02261  -0.0920   0.3191   0.5233
   8.000   1.2267   0.03168   0.02328  -0.0906   0.3161   0.5388
   8.250   1.2481   0.03215   0.02371  -0.0901   0.3133   0.5562
   8.500   1.2799   0.03246   0.02401  -0.0906   0.3105   0.5767
   8.750   1.2942   0.03332   0.02496  -0.0894   0.3079   0.5946
   9.000   1.2903   0.03452   0.02637  -0.0864   0.3053   0.6111
   9.250   1.2931   0.03560   0.02760  -0.0842   0.3025   0.6294
   9.500   1.3029   0.03648   0.02858  -0.0827   0.2998   0.6527
   9.750   1.3202   0.03705   0.02922  -0.0818   0.2973   0.6809
  10.000   1.3457   0.03731   0.02953  -0.0815   0.2949   0.7178
  10.250   1.3791   0.03753   0.02978  -0.0818   0.2924   0.7699
  10.500   1.3557   0.03921   0.03184  -0.0768   0.2904   0.8301
  10.750   1.3378   0.04076   0.03367  -0.0729   0.2880   1.0000
  11.000   1.3374   0.04258   0.03553  -0.0716   0.2852   1.0000
  11.250   1.3482   0.04386   0.03678  -0.0710   0.2828   1.0000
  11.500   1.3694   0.04458   0.03741  -0.0710   0.2806   1.0000
  11.750   1.4041   0.04467   0.03733  -0.0717   0.2785   1.0000
  12.000   1.4274   0.04561   0.03819  -0.0718   0.2762   1.0000
  12.250   1.3905   0.04963   0.04249  -0.0689   0.2738   1.0000
  12.500   1.3595   0.05392   0.04700  -0.0671   0.2709   1.0000
  12.750   1.3484   0.05708   0.05026  -0.0663   0.2682   1.0000
  13.000   1.3601   0.05856   0.05171  -0.0661   0.2661   1.0000
  13.250   1.3903   0.05858   0.05161  -0.0663   0.2643   1.0000
  13.500   1.4347   0.05764   0.05049  -0.0669   0.2627   1.0000
  13.750   1.3806   0.06471   0.05787  -0.0657   0.2597   1.0000
  14.000   1.1061   0.09906   0.09326  -0.0703   0.2472   1.0000
  14.250   1.1543   0.09606   0.09012  -0.0695   0.2471   1.0000
  14.500   1.2080   0.09250   0.08641  -0.0685   0.2471   1.0000
  14.750   1.2712   0.08800   0.08171  -0.0676   0.2472   1.0000
  15.500   0.6552   0.19832   0.19380  -0.1101   0.2155   1.0000
  15.750   0.6689   0.20013   0.19557  -0.1109   0.2132   1.0000
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