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

USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 31 AIRFOIL (usa31-il)
Reynolds number: 200,000
Max Cl/Cd: 54.84 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa31-il-200000-n5.txt
Download as CSV file: xf-usa31-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 31 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.2092   0.09588   0.09168  -0.1388   0.8966   0.0417
  -9.500   0.2178   0.09333   0.08912  -0.1404   0.8927   0.0434
  -9.250   0.2165   0.08971   0.08549  -0.1469   0.8894   0.0446
  -9.000   0.2177   0.08856   0.08438  -0.1415   0.8814   0.0450
  -8.750   0.2336   0.08628   0.08210  -0.1419   0.8781   0.0456
  -8.500   0.2507   0.08364   0.07945  -0.1441   0.8756   0.0465
  -8.250   0.2516   0.08198   0.07781  -0.1427   0.8688   0.0472
  -8.000   0.2558   0.07983   0.07566  -0.1429   0.8628   0.0485
  -7.750   0.2381   0.07698   0.07282  -0.1456   0.8545   0.0504
  -7.500   0.2346   0.07486   0.07073  -0.1442   0.8469   0.0506
  -7.250   0.2598   0.07230   0.06815  -0.1456   0.8445   0.0511
  -7.000   0.2849   0.06970   0.06551  -0.1483   0.8421   0.0520
  -6.750   0.2697   0.06903   0.06488  -0.1430   0.8307   0.0525
  -6.500   0.2879   0.06621   0.06201  -0.1463   0.8266   0.0542
  -6.000   0.2926   0.06094   0.05670  -0.1489   0.8101   0.0582
  -5.500   0.2841   0.04745   0.04293  -0.1554   0.7919   0.0395
  -5.250   0.2846   0.04676   0.04225  -0.1517   0.7815   0.0398
  -5.000   0.3070   0.04321   0.03857  -0.1547   0.7751   0.0380
  -4.750   0.2814   0.02825   0.02225  -0.1594   0.7632   0.0348
  -4.500   0.3064   0.02605   0.01955  -0.1600   0.7572   0.0346
  -4.250   0.3221   0.02503   0.01846  -0.1581   0.7491   0.0350
  -4.000   0.3429   0.02396   0.01722  -0.1572   0.7415   0.0354
  -3.750   0.3706   0.02286   0.01591  -0.1575   0.7354   0.0360
  -3.500   0.3835   0.02209   0.01493  -0.1547   0.7261   0.0363
  -3.250   0.4136   0.02102   0.01355  -0.1551   0.7199   0.0363
  -3.000   0.4280   0.02042   0.01277  -0.1525   0.7107   0.0363
  -2.750   0.4557   0.01967   0.01179  -0.1523   0.7036   0.0363
  -2.500   0.4756   0.01916   0.01112  -0.1506   0.6953   0.0365
  -2.250   0.5010   0.01864   0.01043  -0.1500   0.6877   0.0366
  -2.000   0.5248   0.01820   0.00987  -0.1491   0.6801   0.0368
  -1.750   0.5476   0.01784   0.00940  -0.1479   0.6721   0.0372
  -1.500   0.5747   0.01748   0.00892  -0.1476   0.6652   0.0375
  -1.250   0.5945   0.01728   0.00865  -0.1459   0.6575   0.0377
  -1.000   0.6209   0.01704   0.00830  -0.1455   0.6506   0.0383
  -0.750   0.6420   0.01695   0.00814  -0.1440   0.6431   0.0391
  -0.500   0.6640   0.01676   0.00795  -0.1429   0.6358   0.0401
  -0.250   0.6896   0.01663   0.00777  -0.1423   0.6294   0.0409
   0.000   0.7081   0.01664   0.00777  -0.1404   0.6221   0.0415
   0.250   0.7317   0.01661   0.00767  -0.1395   0.6154   0.0421
   0.500   0.7542   0.01663   0.00761  -0.1384   0.6086   0.0428
   0.750   0.7740   0.01668   0.00762  -0.1368   0.6015   0.0435
   1.000   0.7986   0.01670   0.00752  -0.1361   0.5950   0.0444
   1.250   0.8191   0.01674   0.00753  -0.1347   0.5885   0.0456
   1.500   0.8387   0.01681   0.00755  -0.1331   0.5812   0.0473
   1.750   0.8632   0.01685   0.00750  -0.1324   0.5749   0.0510
   2.000   0.8809   0.01693   0.00762  -0.1305   0.5678   0.0585
   2.250   0.9016   0.01673   0.00797  -0.1295   0.5609   0.2235
   2.500   0.9230   0.01700   0.00820  -0.1282   0.5546   0.2571
   2.750   0.9395   0.01730   0.00849  -0.1261   0.5473   0.2725
   3.000   0.9582   0.01765   0.00874  -0.1244   0.5402   0.2871
   3.250   0.9756   0.01804   0.00914  -0.1224   0.5336   0.2962
   3.500   0.9926   0.01836   0.00941  -0.1205   0.5264   0.3050
   3.750   1.0120   0.01865   0.00964  -0.1190   0.5200   0.3108
   4.000   1.0272   0.01902   0.01003  -0.1168   0.5127   0.3176
   4.250   1.0445   0.01936   0.01029  -0.1150   0.5058   0.3256
   4.500   1.0632   0.01962   0.01053  -0.1135   0.4997   0.3291
   4.750   1.0801   0.01989   0.01080  -0.1117   0.4927   0.3311
   5.000   1.0984   0.02015   0.01101  -0.1102   0.4862   0.3331
   5.250   1.1165   0.02043   0.01127  -0.1087   0.4801   0.3348
   5.500   1.1341   0.02072   0.01155  -0.1072   0.4738   0.3364
   5.750   1.1528   0.02102   0.01179  -0.1059   0.4676   0.3382
   6.000   1.1706   0.02135   0.01211  -0.1045   0.4619   0.3400
   6.250   1.1876   0.02171   0.01246  -0.1029   0.4556   0.3416
   6.500   1.2061   0.02204   0.01275  -0.1017   0.4501   0.3430
   6.750   1.2239   0.02240   0.01314  -0.1004   0.4446   0.3445
   7.000   1.2405   0.02281   0.01358  -0.0989   0.4387   0.3465
   7.250   1.2580   0.02321   0.01397  -0.0976   0.4332   0.3486
   7.500   1.2746   0.02365   0.01440  -0.0962   0.4276   0.3505
   7.750   1.2896   0.02413   0.01493  -0.0945   0.4212   0.3525
   8.000   1.3048   0.02464   0.01541  -0.0930   0.4150   0.3543
   8.250   1.3209   0.02519   0.01597  -0.0917   0.4088   0.3561
   8.500   1.3374   0.02576   0.01658  -0.0905   0.4029   0.3580
   8.750   1.3559   0.02634   0.01717  -0.0898   0.3974   0.3596
   9.000   1.3752   0.02692   0.01778  -0.0893   0.3927   0.3616
   9.250   1.3921   0.02759   0.01853  -0.0885   0.3869   0.3637
   9.500   1.4083   0.02827   0.01924  -0.0875   0.3815   0.3657
   9.750   1.4250   0.02892   0.01987  -0.0866   0.3768   0.3686
  10.000   1.4382   0.02971   0.02076  -0.0852   0.3710   0.3713
  10.250   1.4519   0.03052   0.02162  -0.0840   0.3654   0.3734
  10.500   1.4658   0.03133   0.02243  -0.0829   0.3599   0.3758
  10.750   1.4778   0.03227   0.02346  -0.0816   0.3539   0.3781
  11.000   1.4887   0.03326   0.02451  -0.0801   0.3477   0.3804
  11.250   1.4990   0.03430   0.02552  -0.0787   0.3414   0.3829
  11.500   1.5078   0.03548   0.02680  -0.0772   0.3346   0.3851
  11.750   1.5178   0.03661   0.02798  -0.0758   0.3286   0.3874
  12.000   1.5280   0.03777   0.02917  -0.0746   0.3233   0.3898
  12.250   1.5380   0.03900   0.03051  -0.0734   0.3177   0.3926
  12.500   1.5462   0.04034   0.03189  -0.0721   0.3119   0.3954
  12.750   1.5538   0.04175   0.03332  -0.0708   0.3060   0.3988
  13.000   1.5604   0.04332   0.03499  -0.0696   0.2993   0.4019
  13.250   1.5646   0.04506   0.03674  -0.0682   0.2921   0.4052
  13.500   1.5702   0.04679   0.03856  -0.0671   0.2854   0.4091
  13.750   1.5731   0.04876   0.04055  -0.0658   0.2780   0.4127
  14.000   1.5764   0.05076   0.04262  -0.0646   0.2708   0.4162
  14.250   1.5775   0.05302   0.04493  -0.0635   0.2628   0.4195
  14.500   1.5788   0.05529   0.04724  -0.0625   0.2556   0.4242
  14.750   1.5801   0.05763   0.04965  -0.0615   0.2481   0.4296
  15.000   1.5799   0.06018   0.05223  -0.0607   0.2412   0.4365
  15.250   1.5796   0.06288   0.05504  -0.0600   0.2329   0.4528
  15.750   1.6224   0.07153   0.06444  -0.0713   0.2116   1.0000
  16.000   1.6209   0.07440   0.06739  -0.0707   0.2048   1.0000
  16.250   1.6146   0.07784   0.07084  -0.0700   0.1979   1.0000
  16.500   1.6125   0.08084   0.07391  -0.0695   0.1919   1.0000
  16.750   1.6076   0.08421   0.07733  -0.0690   0.1858   1.0000
  17.000   1.6023   0.08763   0.08079  -0.0686   0.1806   1.0000
  17.250   1.5984   0.09095   0.08418  -0.0684   0.1743   1.0000
  17.500   1.5918   0.09466   0.08793  -0.0682   0.1689   1.0000
  17.750   1.5884   0.09797   0.09131  -0.0682   0.1641   1.0000
  18.000   1.5835   0.10154   0.09495  -0.0682   0.1583   1.0000
  18.250   1.5756   0.10550   0.09893  -0.0684   0.1532   1.0000
  18.500   1.5725   0.10888   0.10240  -0.0687   0.1478   1.0000
  18.750   1.5650   0.11287   0.10643  -0.0691   0.1417   1.0000
  19.000   1.5593   0.11664   0.11026  -0.0696   0.1369   1.0000
  19.250   1.5543   0.12036   0.11405  -0.0702   0.1308   1.0000
<< Back to USA 31 AIRFOIL (usa31-il)

Polar data table (+)

Polar graphs


<< Back to USA 31 AIRFOIL (usa31-il)