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

NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NLF(1)-0115 (nlf0115-il)
Reynolds number: 100,000
Max Cl/Cd: 45.46 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf0115-il-100000.txt
Download as CSV file: xf-nlf0115-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLF(1)-0115                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3139   0.11748   0.11275  -0.0464   1.0000   0.1152
 -11.500  -0.2970   0.11503   0.11031  -0.0442   1.0000   0.1187
 -11.250  -0.4318   0.11420   0.10915  -0.0504   1.0000   0.1144
 -11.000  -0.3979   0.11196   0.10687  -0.0454   1.0000   0.1182
 -10.750  -0.3964   0.10903   0.10398  -0.0452   1.0000   0.1224
 -10.500  -0.4305   0.10465   0.09974  -0.0498   1.0000   0.1277
 -10.250  -0.4846   0.09923   0.09444  -0.0555   1.0000   0.1285
 -10.000  -0.4172   0.09822   0.09339  -0.0467   1.0000   0.1341
  -9.750  -0.4247   0.09503   0.09027  -0.0468   1.0000   0.1393
  -9.500  -0.4782   0.08943   0.08482  -0.0511   1.0000   0.1427
  -9.250  -0.5238   0.08633   0.08180  -0.0503   1.0000   0.1431
  -9.000  -0.5621   0.08462   0.08017  -0.0463   1.0000   0.1431
  -8.750  -0.6016   0.08357   0.07920  -0.0407   1.0000   0.1432
  -8.500  -0.6379   0.08264   0.07830  -0.0354   1.0000   0.1433
  -8.250  -0.6782   0.08196   0.07757  -0.0300   1.0000   0.1436
  -7.750  -0.6612   0.07519   0.07105  -0.0261   0.9998   0.1523
  -6.000  -0.5529   0.04224   0.03471  -0.0362   0.9469   0.0792
  -5.750  -0.5321   0.03997   0.03154  -0.0341   0.9405   0.0718
  -5.500  -0.5041   0.03813   0.02942  -0.0343   0.9351   0.0707
  -5.250  -0.4694   0.03533   0.02641  -0.0357   0.9319   0.0691
  -5.000  -0.4445   0.03365   0.02452  -0.0352   0.9268   0.0681
  -4.750  -0.4181   0.03226   0.02294  -0.0349   0.9220   0.0679
  -4.500  -0.3841   0.03094   0.02145  -0.0357   0.9187   0.0685
  -4.250  -0.3458   0.02988   0.02025  -0.0374   0.9162   0.0703
  -4.000  -0.3314   0.02900   0.01944  -0.0352   0.9101   0.0731
  -3.750  -0.3056   0.02821   0.01877  -0.0351   0.9056   0.0787
  -3.500  -0.2752   0.02752   0.01805  -0.0355   0.9025   0.0841
  -3.250  -0.2644   0.02690   0.01755  -0.0329   0.8977   0.0913
  -3.000  -0.2508   0.02643   0.01710  -0.0307   0.8925   0.1030
  -2.750  -0.2448   0.02377   0.01591  -0.0284   0.8884   0.3370
  -2.500  -0.2597   0.02562   0.01924  -0.0156   0.8833   0.7310
  -2.250  -0.0485   0.03316   0.02659  -0.0268   0.8935   0.8921
  -2.000  -0.0282   0.03293   0.02623  -0.0267   0.8892   0.8961
  -1.750   0.0158   0.03263   0.02576  -0.0308   0.8870   0.8987
  -1.500   0.0054   0.03277   0.02587  -0.0253   0.8791   0.9024
  -1.250   0.0174   0.03267   0.02569  -0.0237   0.8744   0.9054
  -1.000   0.0399   0.03249   0.02541  -0.0238   0.8712   0.9078
  -0.750  -0.0034   0.03264   0.02559  -0.0126   0.8622   0.9118
  -0.500   0.0223   0.03256   0.02542  -0.0134   0.8584   0.9134
  -0.250   0.0609   0.03247   0.02523  -0.0163   0.8557   0.9148
   0.000   0.0163   0.03258   0.02537  -0.0051   0.8471   0.9192
   0.250   0.0190   0.03240   0.02514  -0.0016   0.8423   0.9224
   0.500   0.0054   0.03223   0.02495   0.0045   0.8368   0.9261
   0.750   0.0189   0.03236   0.02504   0.0056   0.8308   0.9284
   1.000   0.0510   0.03239   0.02500   0.0040   0.8263   0.9296
   1.250   0.0654   0.03253   0.02512   0.0051   0.8204   0.9320
   1.500   0.0768   0.03263   0.02520   0.0067   0.8136   0.9356
   1.750   0.1192   0.03264   0.02516   0.0037   0.8089   0.9366
   2.000   0.1096   0.03276   0.02528   0.0086   0.7997   0.9412
   2.250   0.1570   0.03276   0.02526   0.0049   0.7938   0.9419
   2.500   0.1802   0.03300   0.02550   0.0046   0.7833   0.9444
   2.750   0.2479   0.03242   0.02491  -0.0012   0.7766   0.9441
   3.000   0.2707   0.03243   0.02494  -0.0011   0.7639   0.9472
   3.250   0.3050   0.03218   0.02471  -0.0022   0.7528   0.9493
   3.500   0.3740   0.03103   0.02359  -0.0077   0.7462   0.9486
   3.750   0.3933   0.03098   0.02358  -0.0067   0.7341   0.9524
   4.000   0.4843   0.02906   0.02173  -0.0151   0.7303   0.9495
   4.250   0.5028   0.02885   0.02158  -0.0136   0.7183   0.9536
   4.500   0.6091   0.02638   0.01920  -0.0243   0.7138   0.9493
   4.750   0.6330   0.02591   0.01879  -0.0233   0.7011   0.9531
   5.000   0.6726   0.02493   0.01789  -0.0243   0.6892   0.9557
   5.250   0.7294   0.02363   0.01667  -0.0281   0.6761   0.9564
   5.500   0.7755   0.02261   0.01573  -0.0305   0.6587   0.9581
   5.750   0.8162   0.02161   0.01482  -0.0319   0.6379   0.9603
   6.000   0.8471   0.02078   0.01404  -0.0317   0.6127   0.9639
   6.250   0.8624   0.02017   0.01350  -0.0290   0.5803   0.9700
   6.500   0.8842   0.01964   0.01295  -0.0276   0.5167   0.9755
   6.750   0.8982   0.01976   0.01238  -0.0249   0.4260   0.9828
   7.000   0.9147   0.02092   0.01292  -0.0239   0.3626   0.9901
   7.250   0.9368   0.02209   0.01367  -0.0242   0.3243   0.9982
   7.500   0.9335   0.02254   0.01399  -0.0196   0.3072   1.0000
   7.750   0.9154   0.02256   0.01398  -0.0123   0.2977   1.0000
   8.000   0.9256   0.02321   0.01446  -0.0101   0.2814   1.0000
   8.250   0.9460   0.02409   0.01518  -0.0098   0.2650   1.0000
   8.500   0.9687   0.02501   0.01601  -0.0098   0.2502   1.0000
   8.750   0.9937   0.02600   0.01697  -0.0101   0.2373   1.0000
   9.000   1.0197   0.02706   0.01798  -0.0107   0.2256   1.0000
   9.250   1.0491   0.02823   0.01902  -0.0117   0.2145   1.0000
   9.500   1.0699   0.02920   0.02007  -0.0113   0.2051   1.0000
   9.750   1.0956   0.03043   0.02133  -0.0117   0.1964   1.0000
  10.000   1.1203   0.03152   0.02238  -0.0119   0.1878   1.0000
  10.250   1.1407   0.03284   0.02385  -0.0114   0.1805   1.0000
  10.500   1.1634   0.03398   0.02499  -0.0112   0.1733   1.0000
  10.750   1.1827   0.03545   0.02661  -0.0106   0.1668   1.0000
  11.000   1.1981   0.03665   0.02795  -0.0094   0.1606   1.0000
  11.250   1.2246   0.03838   0.02965  -0.0101   0.1546   1.0000
  11.500   1.2306   0.03975   0.03133  -0.0074   0.1497   1.0000
  11.750   1.2469   0.04098   0.03261  -0.0064   0.1444   1.0000
  12.000   1.2643   0.04303   0.03479  -0.0059   0.1398   1.0000
  12.250   1.2613   0.04467   0.03675  -0.0021   0.1363   1.0000
  12.500   1.2692   0.04617   0.03839  -0.0002   0.1322   1.0000
  12.750   1.2984   0.04835   0.04047  -0.0015   0.1271   1.0000
  13.000   1.2817   0.05030   0.04281   0.0034   0.1254   1.0000
  13.250   1.2671   0.05269   0.04553   0.0074   0.1233   1.0000
  13.500   1.2555   0.05521   0.04832   0.0105   0.1210   1.0000
  13.750   1.2568   0.05727   0.05051   0.0122   0.1181   1.0000
  14.000   1.2879   0.05932   0.05243   0.0110   0.1135   1.0000
  14.250   1.2594   0.06254   0.05598   0.0146   0.1129   1.0000
  14.500   1.2290   0.06648   0.06024   0.0172   0.1124   1.0000
  14.750   1.1952   0.07127   0.06532   0.0188   0.1121   1.0000
  15.000   1.1571   0.07709   0.07138   0.0192   0.1121   1.0000
  15.250   1.1134   0.08433   0.07885   0.0182   0.1124   1.0000
  15.500   1.0666   0.09324   0.08794   0.0155   0.1130   1.0000
<< Back to NLF(1)-0115 (nlf0115-il)

Polar data table (+)

Polar graphs


<< Back to NLF(1)-0115 (nlf0115-il)