Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

PT40 (pt40-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: PT40 (pt40-il)
Reynolds number: 500,000
Max Cl/Cd: 76.13 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-pt40-il-500000-n5.txt
Download as CSV file: xf-pt40-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: PT40                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4229   0.12775   0.12481  -0.0184   1.0000   0.0302
 -11.500  -0.4188   0.12426   0.12132  -0.0197   1.0000   0.0305
  -9.500  -0.7212   0.03101   0.02676  -0.0715   0.9936   0.0394
  -9.250  -0.6945   0.02990   0.02557  -0.0724   0.9908   0.0396
  -9.000  -0.6662   0.02893   0.02454  -0.0735   0.9878   0.0397
  -8.750  -0.6365   0.02796   0.02349  -0.0747   0.9852   0.0399
  -8.500  -0.6061   0.02686   0.02230  -0.0761   0.9830   0.0401
  -8.250  -0.5794   0.02565   0.02097  -0.0768   0.9790   0.0404
  -8.000  -0.5520   0.02413   0.01929  -0.0777   0.9749   0.0408
  -7.750  -0.5227   0.02245   0.01738  -0.0790   0.9719   0.0414
  -7.500  -0.4970   0.02057   0.01522  -0.0795   0.9666   0.0422
  -7.250  -0.4708   0.01875   0.01305  -0.0799   0.9605   0.0429
  -7.000  -0.4407   0.01762   0.01171  -0.0807   0.9554   0.0434
  -6.750  -0.4120   0.01707   0.01114  -0.0808   0.9474   0.0436
  -6.500  -0.3800   0.01661   0.01065  -0.0816   0.9410   0.0439
  -6.250  -0.3504   0.01619   0.01021  -0.0818   0.9314   0.0442
  -6.000  -0.3198   0.01577   0.00973  -0.0822   0.9219   0.0445
  -5.750  -0.2898   0.01533   0.00923  -0.0825   0.9110   0.0449
  -5.500  -0.2612   0.01488   0.00870  -0.0824   0.8981   0.0454
  -5.250  -0.2329   0.01445   0.00817  -0.0823   0.8852   0.0459
  -5.000  -0.2051   0.01402   0.00761  -0.0820   0.8719   0.0466
  -4.750  -0.1778   0.01359   0.00705  -0.0816   0.8582   0.0471
  -4.500  -0.1506   0.01321   0.00654  -0.0812   0.8452   0.0476
  -4.250  -0.1234   0.01289   0.00618  -0.0808   0.8326   0.0480
  -4.000  -0.0960   0.01266   0.00592  -0.0804   0.8203   0.0484
  -3.750  -0.0685   0.01246   0.00568  -0.0801   0.8087   0.0488
  -3.500  -0.0411   0.01225   0.00543  -0.0797   0.7968   0.0493
  -3.250  -0.0135   0.01204   0.00517  -0.0793   0.7864   0.0499
  -3.000   0.0140   0.01183   0.00490  -0.0789   0.7752   0.0505
  -2.750   0.0416   0.01162   0.00463  -0.0785   0.7648   0.0512
  -2.500   0.0692   0.01144   0.00438  -0.0781   0.7542   0.0519
  -2.250   0.0968   0.01123   0.00416  -0.0778   0.7439   0.0526
  -2.000   0.1239   0.01112   0.00400  -0.0773   0.7290   0.0532
  -1.750   0.1508   0.01102   0.00384  -0.0767   0.7095   0.0539
  -1.500   0.1776   0.01093   0.00368  -0.0762   0.6887   0.0546
  -1.250   0.2045   0.01085   0.00352  -0.0756   0.6678   0.0554
  -1.000   0.2313   0.01077   0.00336  -0.0751   0.6465   0.0563
  -0.750   0.2585   0.01071   0.00322  -0.0746   0.6276   0.0571
  -0.500   0.2856   0.01061   0.00311  -0.0742   0.6099   0.0580
  -0.250   0.3129   0.01058   0.00304  -0.0737   0.5919   0.0591
   0.000   0.3400   0.01056   0.00297  -0.0733   0.5730   0.0602
   0.250   0.3670   0.01055   0.00290  -0.0728   0.5541   0.0613
   0.500   0.3940   0.01057   0.00284  -0.0723   0.5338   0.0624
   0.750   0.4208   0.01056   0.00279  -0.0718   0.5138   0.0636
   1.000   0.4477   0.01061   0.00279  -0.0713   0.4928   0.0650
   1.250   0.4743   0.01069   0.00280  -0.0708   0.4690   0.0667
   1.500   0.5008   0.01080   0.00281  -0.0703   0.4437   0.0683
   1.750   0.5270   0.01090   0.00283  -0.0697   0.4142   0.0699
   2.000   0.5526   0.01110   0.00290  -0.0691   0.3770   0.0718
   2.250   0.5776   0.01138   0.00299  -0.0684   0.3351   0.0740
   2.500   0.6029   0.01163   0.00311  -0.0677   0.3002   0.0766
   2.750   0.6285   0.01186   0.00324  -0.0671   0.2738   0.0797
   3.000   0.6545   0.01206   0.00336  -0.0665   0.2528   0.0831
   3.250   0.6804   0.01226   0.00350  -0.0660   0.2336   0.0882
   3.500   0.7062   0.01246   0.00364  -0.0654   0.2160   0.0958
   4.000   0.7485   0.01102   0.00412  -0.0631   0.1918   0.8250
   4.250   0.7852   0.01101   0.00430  -0.0644   0.1814   1.0000
   4.500   0.8106   0.01126   0.00446  -0.0637   0.1730   1.0000
   4.750   0.8364   0.01148   0.00462  -0.0631   0.1652   1.0000
   5.000   0.8618   0.01173   0.00480  -0.0625   0.1578   1.0000
   5.250   0.8874   0.01197   0.00499  -0.0618   0.1503   1.0000
   5.500   0.9128   0.01223   0.00518  -0.0612   0.1437   1.0000
   5.750   0.9380   0.01250   0.00539  -0.0605   0.1360   1.0000
   6.000   0.9634   0.01275   0.00560  -0.0598   0.1299   1.0000
   6.250   0.9882   0.01305   0.00584  -0.0591   0.1230   1.0000
   6.500   1.0132   0.01332   0.00607  -0.0584   0.1157   1.0000
   6.750   1.0377   0.01363   0.00633  -0.0577   0.1074   1.0000
   7.000   1.0616   0.01398   0.00662  -0.0569   0.0977   1.0000
   7.250   1.0848   0.01440   0.00694  -0.0560   0.0857   1.0000
   7.500   1.1068   0.01492   0.00734  -0.0549   0.0701   1.0000
   7.750   1.1279   0.01549   0.00780  -0.0537   0.0575   1.0000
   8.000   1.1497   0.01600   0.00825  -0.0526   0.0511   1.0000
   8.250   1.1716   0.01646   0.00869  -0.0515   0.0475   1.0000
   8.500   1.1934   0.01693   0.00915  -0.0504   0.0450   1.0000
   8.750   1.2151   0.01739   0.00960  -0.0493   0.0433   1.0000
   9.000   1.2365   0.01784   0.01005  -0.0482   0.0418   1.0000
   9.250   1.2571   0.01834   0.01056  -0.0470   0.0405   1.0000
   9.500   1.2771   0.01886   0.01108  -0.0456   0.0395   1.0000
   9.750   1.2972   0.01933   0.01157  -0.0444   0.0386   1.0000
  10.000   1.3162   0.01984   0.01210  -0.0429   0.0378   1.0000
  10.250   1.3331   0.02037   0.01266  -0.0411   0.0371   1.0000
  10.500   1.3492   0.02097   0.01327  -0.0392   0.0365   1.0000
  10.750   1.3642   0.02163   0.01396  -0.0373   0.0359   1.0000
  11.000   1.3788   0.02233   0.01468  -0.0354   0.0355   1.0000
  11.250   1.3942   0.02298   0.01537  -0.0336   0.0351   1.0000
  11.500   1.4088   0.02369   0.01613  -0.0319   0.0347   1.0000
  11.750   1.4226   0.02447   0.01696  -0.0301   0.0342   1.0000
  12.000   1.4358   0.02531   0.01785  -0.0284   0.0339   1.0000
  12.250   1.4481   0.02622   0.01881  -0.0267   0.0335   1.0000
  12.500   1.4597   0.02722   0.01986  -0.0251   0.0332   1.0000
  12.750   1.4704   0.02833   0.02102  -0.0235   0.0329   1.0000
  13.000   1.4800   0.02955   0.02230  -0.0219   0.0326   1.0000
  13.250   1.4885   0.03092   0.02372  -0.0205   0.0323   1.0000
  13.500   1.4954   0.03247   0.02532  -0.0192   0.0321   1.0000
  13.750   1.5006   0.03423   0.02715  -0.0179   0.0318   1.0000
  14.000   1.5064   0.03603   0.02901  -0.0169   0.0316   1.0000
  14.250   1.5132   0.03778   0.03085  -0.0160   0.0314   1.0000
  14.500   1.5191   0.03971   0.03285  -0.0153   0.0312   1.0000
  14.750   1.5238   0.04179   0.03503  -0.0147   0.0310   1.0000
  15.000   1.5274   0.04406   0.03738  -0.0143   0.0307   1.0000
  15.250   1.5297   0.04653   0.03994  -0.0140   0.0305   1.0000
  15.500   1.5308   0.04922   0.04272  -0.0139   0.0304   1.0000
  15.750   1.5305   0.05213   0.04572  -0.0139   0.0302   1.0000
  16.000   1.5292   0.05527   0.04895  -0.0142   0.0300   1.0000
  16.250   1.5269   0.05863   0.05242  -0.0146   0.0299   1.0000
  16.500   1.5235   0.06224   0.05613  -0.0153   0.0297   1.0000
  16.750   1.5191   0.06606   0.06005  -0.0161   0.0296   1.0000
  17.000   1.5138   0.07013   0.06422  -0.0172   0.0295   1.0000
  17.250   1.5075   0.07444   0.06863  -0.0184   0.0294   1.0000
  17.500   1.5000   0.07897   0.07326  -0.0199   0.0293   1.0000
  17.750   1.4918   0.08371   0.07810  -0.0215   0.0292   1.0000
  18.000   1.4832   0.08860   0.08310  -0.0232   0.0291   1.0000
  18.250   1.4741   0.09362   0.08822  -0.0251   0.0290   1.0000
  18.500   1.4647   0.09872   0.09341  -0.0271   0.0289   1.0000
<< Back to PT40 (pt40-il)

Polar data table (+)

Polar graphs


<< Back to PT40 (pt40-il)