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FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 73-CL3-152 (fx73cl3152-il)
Reynolds number: 200,000
Max Cl/Cd: 71.01 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73cl3152-il-200000-n5.txt
Download as CSV file: xf-fx73cl3152-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-CL3-152                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.1797   0.09554   0.09123  -0.1185   0.8608   0.0449
  -9.500   0.1884   0.09309   0.08874  -0.1196   0.8514   0.0456
  -9.000   0.1905   0.08587   0.08146  -0.1221   0.8318   0.0371
  -8.750   0.1987   0.08384   0.07941  -0.1220   0.8191   0.0366
  -8.500   0.2047   0.08146   0.07701  -0.1223   0.8049   0.0364
  -8.250   0.2050   0.07861   0.07413  -0.1231   0.7880   0.0370
  -8.000   0.2072   0.07600   0.07146  -0.1234   0.7633   0.0370
  -7.750   0.2133   0.07394   0.06924  -0.1231   0.7267   0.0368
  -7.500   0.2158   0.07185   0.06692  -0.1225   0.6892   0.0365
  -7.250   0.2165   0.06967   0.06457  -0.1220   0.6611   0.0363
  -7.000   0.2160   0.06739   0.06217  -0.1216   0.6389   0.0361
  -6.750   0.2136   0.06501   0.05970  -0.1211   0.6215   0.0360
  -6.250   0.1658   0.02526   0.01865  -0.1736   0.6207   0.0377
  -6.000   0.1907   0.02425   0.01739  -0.1744   0.6026   0.0383
  -5.750   0.2162   0.02319   0.01603  -0.1752   0.5871   0.0389
  -5.500   0.2423   0.02213   0.01467  -0.1759   0.5734   0.0397
  -5.250   0.2686   0.02114   0.01336  -0.1765   0.5621   0.0407
  -5.000   0.2949   0.02026   0.01211  -0.1767   0.5516   0.0418
  -4.750   0.3211   0.01975   0.01148  -0.1767   0.5423   0.0429
  -4.500   0.3469   0.01940   0.01101  -0.1765   0.5336   0.0441
  -4.250   0.3733   0.01896   0.01039  -0.1764   0.5260   0.0455
  -4.000   0.3998   0.01848   0.00970  -0.1762   0.5182   0.0469
  -3.750   0.4255   0.01813   0.00921  -0.1758   0.5116   0.0480
  -3.500   0.4521   0.01784   0.00888  -0.1756   0.5052   0.0495
  -3.250   0.4786   0.01759   0.00853  -0.1753   0.4994   0.0516
  -3.000   0.5049   0.01737   0.00817  -0.1750   0.4944   0.0537
  -2.750   0.5314   0.01718   0.00793  -0.1747   0.4899   0.0558
  -2.500   0.5583   0.01698   0.00766  -0.1744   0.4855   0.0584
  -2.250   0.5849   0.01681   0.00745  -0.1742   0.4811   0.0612
  -2.000   0.6113   0.01672   0.00727  -0.1738   0.4770   0.0650
  -1.500   0.6646   0.01654   0.00697  -0.1731   0.4695   0.0742
  -1.250   0.6914   0.01645   0.00688  -0.1729   0.4657   0.0810
  -1.000   0.7180   0.01639   0.00681  -0.1725   0.4623   0.0903
  -0.750   0.7446   0.01637   0.00677  -0.1722   0.4592   0.1032
  -0.500   0.7711   0.01639   0.00678  -0.1719   0.4564   0.1198
  -0.250   0.7978   0.01645   0.00681  -0.1716   0.4537   0.1393
   0.000   0.8244   0.01647   0.00688  -0.1712   0.4507   0.1590
   0.250   0.8508   0.01653   0.00695  -0.1709   0.4476   0.1780
   0.500   0.8771   0.01661   0.00705  -0.1705   0.4445   0.1970
   0.750   0.9034   0.01671   0.00715  -0.1701   0.4418   0.2162
   1.000   0.9296   0.01683   0.00726  -0.1697   0.4393   0.2367
   1.250   0.9560   0.01697   0.00739  -0.1694   0.4369   0.2582
   1.500   0.9825   0.01712   0.00753  -0.1690   0.4344   0.2788
   1.750   1.0083   0.01721   0.00769  -0.1686   0.4318   0.2986
   2.000   1.0341   0.01733   0.00786  -0.1681   0.4291   0.3197
   2.250   1.0599   0.01746   0.00804  -0.1677   0.4265   0.3426
   2.500   1.0855   0.01759   0.00822  -0.1672   0.4239   0.3675
   2.750   1.1108   0.01775   0.00839  -0.1667   0.4214   0.3950
   3.000   1.1366   0.01793   0.00859  -0.1663   0.4190   0.4244
   3.250   1.1631   0.01816   0.00881  -0.1661   0.4167   0.4576
   3.500   1.1882   0.01830   0.00908  -0.1656   0.4143   0.4935
   3.750   1.2140   0.01847   0.00936  -0.1652   0.4117   0.5328
   4.000   1.2402   0.01865   0.00963  -0.1649   0.4092   0.5752
   4.250   1.2663   0.01883   0.00989  -0.1646   0.4068   0.6196
   4.500   1.2926   0.01900   0.01013  -0.1644   0.4043   0.6684
   4.750   1.3203   0.01914   0.01034  -0.1645   0.4020   0.7304
   5.000   1.3543   0.01918   0.01052  -0.1659   0.3997   1.0000
   5.250   1.3793   0.01950   0.01082  -0.1655   0.3976   1.0000
   5.500   1.4028   0.01980   0.01114  -0.1648   0.3954   1.0000
   5.750   1.4262   0.02012   0.01147  -0.1641   0.3931   1.0000
   6.000   1.4492   0.02043   0.01179  -0.1634   0.3906   1.0000
   6.250   1.4721   0.02074   0.01209  -0.1626   0.3881   1.0000
   6.500   1.4948   0.02105   0.01239  -0.1618   0.3858   1.0000
   6.750   1.5182   0.02138   0.01267  -0.1611   0.3835   1.0000
   7.000   1.5430   0.02175   0.01298  -0.1608   0.3815   1.0000
   7.250   1.5637   0.02212   0.01341  -0.1597   0.3794   1.0000
   7.500   1.5829   0.02250   0.01386  -0.1584   0.3771   1.0000
   7.750   1.6017   0.02289   0.01431  -0.1570   0.3746   1.0000
   8.000   1.6205   0.02328   0.01474  -0.1557   0.3722   1.0000
   8.250   1.6395   0.02367   0.01516  -0.1544   0.3700   1.0000
   8.500   1.6586   0.02405   0.01555  -0.1531   0.3678   1.0000
   8.750   1.6791   0.02444   0.01592  -0.1521   0.3656   1.0000
   9.000   1.6994   0.02488   0.01635  -0.1512   0.3634   1.0000
   9.250   1.7126   0.02543   0.01703  -0.1491   0.3608   1.0000
   9.500   1.7274   0.02598   0.01769  -0.1474   0.3583   1.0000
   9.750   1.7426   0.02654   0.01832  -0.1458   0.3557   1.0000
  10.000   1.7582   0.02710   0.01893  -0.1443   0.3534   1.0000
  10.250   1.7743   0.02764   0.01951  -0.1429   0.3512   1.0000
  10.500   1.7922   0.02815   0.02004  -0.1418   0.3491   1.0000
  10.750   1.8102   0.02870   0.02059  -0.1407   0.3470   1.0000
  11.000   1.8179   0.02961   0.02167  -0.1385   0.3441   1.0000
  11.250   1.8276   0.03050   0.02267  -0.1365   0.3413   1.0000
  11.500   1.8387   0.03136   0.02363  -0.1348   0.3387   1.0000
  11.750   1.8506   0.03219   0.02454  -0.1332   0.3363   1.0000
  12.000   1.8644   0.03295   0.02533  -0.1319   0.3342   1.0000
  12.250   1.8807   0.03360   0.02599  -0.1308   0.3321   1.0000
  12.500   1.8875   0.03481   0.02733  -0.1289   0.3295   1.0000
  12.750   1.8901   0.03630   0.02898  -0.1268   0.3264   1.0000
  13.000   1.8951   0.03770   0.03050  -0.1249   0.3236   1.0000
  13.250   1.9019   0.03901   0.03191  -0.1233   0.3210   1.0000
  13.500   1.9115   0.04012   0.03307  -0.1220   0.3184   1.0000
  13.750   1.9233   0.04104   0.03398  -0.1208   0.3153   1.0000
  14.000   1.9102   0.04395   0.03712  -0.1183   0.3106   1.0000
  14.250   1.9051   0.04635   0.03962  -0.1165   0.3057   1.0000
  14.500   1.9123   0.04771   0.04097  -0.1154   0.3016   1.0000
  14.750   1.9042   0.05077   0.04418  -0.1140   0.2974   1.0000
  15.000   1.8933   0.05434   0.04793  -0.1128   0.2931   1.0000
  15.250   1.8905   0.05714   0.05081  -0.1120   0.2893   1.0000
  15.500   1.8982   0.05877   0.05244  -0.1113   0.2861   1.0000
  15.750   1.8792   0.06374   0.05761  -0.1107   0.2819   1.0000
  16.000   1.8575   0.06927   0.06330  -0.1105   0.2772   1.0000
  16.250   1.8555   0.07230   0.06638  -0.1102   0.2733   1.0000
  16.500   1.8615   0.07428   0.06838  -0.1098   0.2700   1.0000
  16.750   1.8077   0.08464   0.07902  -0.1108   0.2636   1.0000
  17.000   1.8014   0.08846   0.08290  -0.1109   0.2591   1.0000
  17.250   1.8216   0.08846   0.08286  -0.1103   0.2561   1.0000
  17.500   1.7415   0.10337   0.09807  -0.1132   0.2475   1.0000
  17.750   1.7533   0.10461   0.09933  -0.1131   0.2437   1.0000
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