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

NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.55 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nplx-il-1000000-n5.txt
Download as CSV file: xf-nplx-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL AIRFOIL FROM ARC CP 1372                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.9875   0.08264   0.08004  -0.0347   1.0000   0.0061
 -15.250  -1.0247   0.07030   0.06747  -0.0425   1.0000   0.0060
 -15.000  -1.0522   0.06202   0.05901  -0.0473   1.0000   0.0060
 -14.750  -1.0649   0.05689   0.05375  -0.0499   1.0000   0.0060
 -14.500  -1.0783   0.05198   0.04870  -0.0521   1.0000   0.0060
 -14.250  -1.0878   0.04789   0.04448  -0.0536   1.0000   0.0060
 -14.000  -1.0925   0.04457   0.04104  -0.0546   1.0000   0.0060
 -13.750  -1.1029   0.04076   0.03707  -0.0555   1.0000   0.0060
 -13.500  -1.1031   0.03828   0.03448  -0.0557   1.0000   0.0059
 -13.250  -1.1114   0.03507   0.03111  -0.0557   1.0000   0.0060
 -13.000  -1.1089   0.03312   0.02906  -0.0552   1.0000   0.0060
 -12.750  -1.1126   0.03075   0.02654  -0.0544   1.0000   0.0060
 -12.500  -1.1101   0.02914   0.02483  -0.0532   1.0000   0.0060
 -12.250  -1.1101   0.02762   0.02320  -0.0514   1.0000   0.0060
 -12.000  -1.1123   0.02640   0.02189  -0.0485   1.0000   0.0060
 -11.750  -1.1129   0.02522   0.02060  -0.0452   1.0000   0.0060
 -11.500  -1.1038   0.02425   0.01954  -0.0432   1.0000   0.0060
 -11.250  -1.0949   0.02317   0.01837  -0.0411   1.0000   0.0061
 -11.000  -1.0839   0.02218   0.01728  -0.0392   1.0000   0.0061
 -10.750  -1.0712   0.02128   0.01629  -0.0374   1.0000   0.0061
 -10.500  -1.0572   0.02042   0.01535  -0.0357   1.0000   0.0062
 -10.250  -1.0421   0.01964   0.01450  -0.0341   1.0000   0.0062
 -10.000  -1.0189   0.01883   0.01361  -0.0342   0.9994   0.0062
  -9.750  -0.9916   0.01805   0.01276  -0.0350   0.9984   0.0062
  -9.500  -0.9643   0.01725   0.01189  -0.0358   0.9971   0.0063
  -9.250  -0.9361   0.01659   0.01117  -0.0367   0.9959   0.0064
  -9.000  -0.9074   0.01592   0.01044  -0.0376   0.9947   0.0065
  -8.750  -0.8788   0.01534   0.00981  -0.0384   0.9934   0.0065
  -8.500  -0.8519   0.01476   0.00918  -0.0388   0.9916   0.0066
  -8.250  -0.8240   0.01424   0.00862  -0.0393   0.9898   0.0067
  -8.000  -0.7953   0.01374   0.00808  -0.0400   0.9881   0.0068
  -7.750  -0.7658   0.01326   0.00757  -0.0408   0.9866   0.0069
  -7.500  -0.7354   0.01281   0.00709  -0.0418   0.9852   0.0071
  -7.250  -0.7042   0.01240   0.00664  -0.0429   0.9841   0.0072
  -7.000  -0.6781   0.01201   0.00623  -0.0429   0.9810   0.0074
  -6.750  -0.6500   0.01163   0.00583  -0.0432   0.9781   0.0076
  -6.500  -0.6201   0.01128   0.00546  -0.0439   0.9759   0.0077
  -6.250  -0.5894   0.01094   0.00510  -0.0448   0.9741   0.0080
  -5.750  -0.5320   0.01029   0.00443  -0.0456   0.9682   0.0089
  -5.500  -0.5032   0.01000   0.00414  -0.0460   0.9643   0.0095
  -5.250  -0.4716   0.00971   0.00386  -0.0470   0.9616   0.0105
  -5.000  -0.4381   0.00942   0.00358  -0.0484   0.9597   0.0130
  -4.750  -0.4083   0.00915   0.00334  -0.0490   0.9553   0.0169
  -4.500  -0.3766   0.00891   0.00312  -0.0500   0.9511   0.0199
  -4.250  -0.3430   0.00868   0.00291  -0.0514   0.9476   0.0233
  -4.000  -0.3093   0.00846   0.00272  -0.0528   0.9436   0.0270
  -3.750  -0.2778   0.00828   0.00254  -0.0537   0.9370   0.0302
  -3.500  -0.2444   0.00808   0.00236  -0.0550   0.9310   0.0346
  -3.250  -0.2139   0.00790   0.00220  -0.0556   0.9232   0.0404
  -3.000  -0.1830   0.00773   0.00205  -0.0563   0.9157   0.0477
  -2.750  -0.1540   0.00758   0.00191  -0.0566   0.9063   0.0569
  -2.500  -0.1253   0.00742   0.00179  -0.0567   0.8940   0.0719
  -2.250  -0.0977   0.00729   0.00167  -0.0567   0.8776   0.0877
  -2.000  -0.0708   0.00715   0.00155  -0.0565   0.8613   0.1092
  -1.750  -0.0451   0.00680   0.00140  -0.0562   0.8475   0.1797
  -1.500  -0.0241   0.00560   0.00100  -0.0557   0.8336   0.4331
  -1.000   0.0298   0.00546   0.00096  -0.0551   0.8089   0.4968
  -0.750   0.0566   0.00546   0.00095  -0.0548   0.7923   0.5136
  -0.500   0.0832   0.00548   0.00095  -0.0543   0.7743   0.5310
  -0.250   0.1100   0.00553   0.00094  -0.0540   0.7550   0.5382
   0.000   0.1362   0.00561   0.00093  -0.0534   0.7272   0.5419
   0.250   0.1605   0.00577   0.00092  -0.0526   0.6770   0.5467
   0.500   0.1814   0.00621   0.00097  -0.0510   0.5713   0.5520
   0.750   0.2014   0.00685   0.00111  -0.0495   0.4364   0.5572
   1.000   0.2244   0.00729   0.00123  -0.0486   0.3448   0.5649
   1.250   0.2488   0.00766   0.00133  -0.0480   0.2741   0.5710
   1.500   0.2724   0.00809   0.00145  -0.0472   0.1878   0.5744
   1.750   0.2962   0.00854   0.00161  -0.0465   0.1081   0.5780
   2.000   0.3228   0.00872   0.00171  -0.0462   0.0876   0.5816
   2.250   0.3498   0.00887   0.00181  -0.0459   0.0759   0.5851
   2.500   0.3767   0.00901   0.00190  -0.0457   0.0666   0.5883
   2.750   0.4035   0.00915   0.00201  -0.0454   0.0570   0.5921
   3.000   0.4303   0.00931   0.00213  -0.0451   0.0484   0.5961
   3.250   0.4571   0.00947   0.00225  -0.0448   0.0423   0.6002
   3.750   0.5107   0.00976   0.00253  -0.0442   0.0364   0.6086
   4.000   0.5373   0.00992   0.00269  -0.0439   0.0345   0.6136
   4.250   0.5639   0.01011   0.00287  -0.0436   0.0328   0.6184
   4.500   0.5904   0.01028   0.00306  -0.0432   0.0318   0.6231
   4.750   0.6170   0.01044   0.00324  -0.0429   0.0312   0.6282
   5.000   0.6434   0.01061   0.00344  -0.0425   0.0305   0.6334
   5.250   0.6698   0.01079   0.00364  -0.0422   0.0297   0.6382
   5.500   0.6959   0.01098   0.00385  -0.0418   0.0288   0.6439
   5.750   0.7219   0.01120   0.00408  -0.0414   0.0281   0.6496
   6.000   0.7477   0.01143   0.00434  -0.0409   0.0274   0.6554
   6.250   0.7729   0.01172   0.00466  -0.0403   0.0266   0.6623
   6.500   0.7979   0.01205   0.00503  -0.0397   0.0260   0.6690
   6.750   0.8235   0.01227   0.00530  -0.0393   0.0258   0.6763
   7.000   0.8490   0.01251   0.00558  -0.0388   0.0255   0.6834
   7.250   0.8742   0.01276   0.00589  -0.0382   0.0252   0.6907
   7.500   0.8993   0.01304   0.00621  -0.0377   0.0248   0.6985
   7.750   0.9242   0.01332   0.00655  -0.0371   0.0244   0.7061
   8.000   0.9489   0.01361   0.00688  -0.0365   0.0240   0.7143
   8.250   0.9736   0.01390   0.00722  -0.0359   0.0235   0.7224
   8.500   0.9982   0.01418   0.00755  -0.0353   0.0231   0.7315
   8.750   1.0223   0.01449   0.00792  -0.0346   0.0227   0.7410
   9.000   1.0462   0.01483   0.00831  -0.0339   0.0224   0.7504
   9.250   1.0696   0.01520   0.00874  -0.0331   0.0220   0.7610
   9.500   1.0921   0.01565   0.00926  -0.0322   0.0216   0.7724
   9.750   1.1131   0.01625   0.00994  -0.0310   0.0210   0.7857
  10.000   1.1362   0.01656   0.01036  -0.0302   0.0209   0.8014
  10.250   1.1594   0.01681   0.01070  -0.0294   0.0206   0.8211
  10.500   1.1808   0.01715   0.01118  -0.0283   0.0204   0.8479
  10.750   1.2004   0.01746   0.01165  -0.0267   0.0202   0.8887
  11.000   1.2241   0.01776   0.01214  -0.0261   0.0199   1.0000
  11.250   1.2457   0.01824   0.01267  -0.0251   0.0196   1.0000
  11.500   1.2670   0.01872   0.01320  -0.0241   0.0193   1.0000
  11.750   1.2883   0.01917   0.01369  -0.0231   0.0190   1.0000
  12.000   1.3089   0.01966   0.01423  -0.0220   0.0187   1.0000
  12.250   1.3299   0.02007   0.01468  -0.0210   0.0184   1.0000
  12.500   1.3505   0.02048   0.01511  -0.0199   0.0180   1.0000
  12.750   1.3707   0.02089   0.01552  -0.0188   0.0176   1.0000
  13.000   1.3876   0.02156   0.01625  -0.0173   0.0173   1.0000
  13.250   1.4007   0.02234   0.01709  -0.0151   0.0169   1.0000
  13.500   1.4174   0.02278   0.01759  -0.0134   0.0168   1.0000
  13.750   1.4305   0.02345   0.01835  -0.0112   0.0166   1.0000
  14.000   1.4442   0.02407   0.01904  -0.0092   0.0164   1.0000
  14.250   1.4577   0.02470   0.01973  -0.0073   0.0162   1.0000
  14.500   1.4706   0.02537   0.02047  -0.0053   0.0159   1.0000
  14.750   1.4815   0.02618   0.02136  -0.0032   0.0157   1.0000
  15.000   1.4924   0.02698   0.02224  -0.0012   0.0154   1.0000
  15.250   1.5015   0.02794   0.02328   0.0008   0.0153   1.0000
  15.500   1.5103   0.02893   0.02435   0.0028   0.0151   1.0000
  15.750   1.5201   0.02987   0.02535   0.0044   0.0148   1.0000
  16.000   1.5284   0.03095   0.02649   0.0061   0.0146   1.0000
  16.250   1.5350   0.03221   0.02783   0.0078   0.0144   1.0000
  16.500   1.5407   0.03358   0.02927   0.0093   0.0142   1.0000
  16.750   1.5449   0.03515   0.03092   0.0107   0.0140   1.0000
  17.000   1.5468   0.03699   0.03285   0.0119   0.0138   1.0000
  17.250   1.5463   0.03916   0.03512   0.0130   0.0136   1.0000
  17.500   1.5441   0.04162   0.03769   0.0137   0.0135   1.0000
  17.750   1.5397   0.04447   0.04066   0.0140   0.0134   1.0000
  18.000   1.5356   0.04749   0.04381   0.0140   0.0133   1.0000
  18.250   1.5288   0.05104   0.04749   0.0133   0.0133   1.0000
  18.500   1.5173   0.05554   0.05213   0.0119   0.0132   1.0000
  18.750   1.5033   0.06087   0.05762   0.0094   0.0131   1.0000
<< Back to NPL AIRFOIL FROM ARC CP 1372 (nplx-il)

Polar data table (+)

Polar graphs


<< Back to NPL AIRFOIL FROM ARC CP 1372 (nplx-il)