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

NN7 MK20 (nn7mk20-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NN7 MK20 (nn7mk20-il)
Reynolds number: 500,000
Max Cl/Cd: 98.99 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nn7mk20-il-500000-n5.txt
Download as CSV file: xf-nn7mk20-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NN7 MK20                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.6503   0.08383   0.08090  -0.0700   1.0000   0.0068
 -15.250  -0.6760   0.07487   0.07177  -0.0754   1.0000   0.0069
 -15.000  -0.7020   0.06679   0.06349  -0.0800   1.0000   0.0068
 -14.750  -0.7196   0.06070   0.05722  -0.0832   1.0000   0.0068
 -14.500  -0.7323   0.05584   0.05222  -0.0855   1.0000   0.0068
 -14.250  -0.7409   0.05189   0.04814  -0.0870   1.0000   0.0068
 -14.000  -0.7482   0.04848   0.04460  -0.0879   1.0000   0.0070
 -13.750  -0.7563   0.04527   0.04126  -0.0883   1.0000   0.0070
 -13.500  -0.7524   0.04204   0.03788  -0.0902   0.9783   0.0070
 -13.000  -0.7004   0.03557   0.03095  -0.1031   0.9423   0.0074
 -12.750  -0.6651   0.03288   0.02801  -0.1101   0.9272   0.0075
 -12.500  -0.6363   0.03068   0.02556  -0.1150   0.9051   0.0077
 -12.250  -0.6195   0.02930   0.02396  -0.1162   0.8814   0.0078
 -12.000  -0.6103   0.02803   0.02251  -0.1156   0.8606   0.0079
 -11.750  -0.6023   0.02687   0.02119  -0.1146   0.8437   0.0079
 -11.500  -0.5965   0.02562   0.01981  -0.1133   0.8300   0.0082
 -11.250  -0.5878   0.02461   0.01866  -0.1121   0.8187   0.0082
 -11.000  -0.5792   0.02359   0.01755  -0.1108   0.8088   0.0084
 -10.750  -0.5692   0.02269   0.01655  -0.1096   0.8005   0.0086
 -10.500  -0.5585   0.02186   0.01563  -0.1083   0.7927   0.0089
 -10.250  -0.5474   0.02106   0.01475  -0.1070   0.7863   0.0090
 -10.000  -0.5369   0.02028   0.01390  -0.1056   0.7797   0.0093
  -9.750  -0.5288   0.01956   0.01308  -0.1037   0.7736   0.0095
  -9.500  -0.5174   0.01885   0.01231  -0.1023   0.7677   0.0098
  -9.250  -0.5014   0.01820   0.01157  -0.1016   0.7621   0.0102
  -9.000  -0.4835   0.01763   0.01090  -0.1009   0.7575   0.0106
  -8.750  -0.4654   0.01700   0.01024  -0.1002   0.7527   0.0114
  -8.500  -0.4452   0.01652   0.00971  -0.0997   0.7480   0.0120
  -8.000  -0.4023   0.01560   0.00866  -0.0988   0.7391   0.0137
  -7.750  -0.3804   0.01513   0.00814  -0.0984   0.7345   0.0148
  -7.500  -0.3571   0.01475   0.00772  -0.0982   0.7304   0.0164
  -7.250  -0.3331   0.01441   0.00732  -0.0980   0.7267   0.0179
  -7.000  -0.3091   0.01402   0.00691  -0.0978   0.7225   0.0197
  -6.750  -0.2844   0.01370   0.00656  -0.0977   0.7182   0.0217
  -6.500  -0.2591   0.01344   0.00622  -0.0976   0.7144   0.0234
  -6.250  -0.2339   0.01310   0.00585  -0.0976   0.7108   0.0258
  -6.000  -0.2081   0.01281   0.00556  -0.0976   0.7069   0.0286
  -5.750  -0.1821   0.01255   0.00526  -0.0976   0.7030   0.0319
  -5.500  -0.1564   0.01226   0.00495  -0.0976   0.6993   0.0367
  -5.250  -0.1301   0.01198   0.00465  -0.0977   0.6958   0.0431
  -5.000  -0.1039   0.01166   0.00438  -0.0978   0.6920   0.0545
  -4.750  -0.0781   0.01130   0.00410  -0.0979   0.6882   0.0802
  -4.500  -0.0518   0.01099   0.00385  -0.0980   0.6847   0.1064
  -4.250  -0.0261   0.01055   0.00354  -0.0981   0.6812   0.1493
  -4.000  -0.0020   0.00980   0.00317  -0.0983   0.6773   0.2523
  -3.750   0.0227   0.00914   0.00284  -0.0985   0.6733   0.3466
  -3.500   0.0481   0.00865   0.00258  -0.0986   0.6696   0.4271
  -3.250   0.0741   0.00834   0.00256  -0.0986   0.6661   0.5117
  -3.000   0.1023   0.00833   0.00261  -0.0986   0.6622   0.5463
  -2.750   0.1308   0.00839   0.00262  -0.0988   0.6584   0.5661
  -2.500   0.1592   0.00843   0.00263  -0.0989   0.6550   0.5734
  -2.250   0.1879   0.00846   0.00258  -0.0992   0.6516   0.5803
  -2.000   0.2164   0.00851   0.00263  -0.0993   0.6479   0.5876
  -1.750   0.2451   0.00856   0.00262  -0.0995   0.6440   0.5954
  -1.500   0.2734   0.00862   0.00265  -0.0996   0.6404   0.6002
  -1.250   0.3019   0.00868   0.00267  -0.0998   0.6371   0.6046
  -1.000   0.3306   0.00870   0.00266  -0.1001   0.6333   0.6085
  -0.750   0.3592   0.00873   0.00264  -0.1003   0.6295   0.6112
  -0.500   0.3874   0.00876   0.00264  -0.1005   0.6259   0.6131
  -0.250   0.4157   0.00880   0.00266  -0.1006   0.6226   0.6152
   0.000   0.4442   0.00883   0.00269  -0.1009   0.6189   0.6173
   0.250   0.4725   0.00886   0.00271  -0.1011   0.6149   0.6197
   0.500   0.5007   0.00892   0.00273  -0.1012   0.6110   0.6230
   0.750   0.5289   0.00899   0.00275  -0.1014   0.6076   0.6263
   1.000   0.5571   0.00902   0.00282  -0.1016   0.6037   0.6286
   1.250   0.5850   0.00906   0.00287  -0.1017   0.5995   0.6304
   1.500   0.6129   0.00912   0.00291  -0.1018   0.5955   0.6322
   1.750   0.6408   0.00917   0.00296  -0.1019   0.5917   0.6339
   2.000   0.6688   0.00922   0.00301  -0.1021   0.5873   0.6357
   2.250   0.6964   0.00927   0.00307  -0.1022   0.5826   0.6377
   2.750   0.7517   0.00940   0.00318  -0.1024   0.5738   0.6414
   3.000   0.7789   0.00945   0.00327  -0.1024   0.5687   0.6427
   3.250   0.8058   0.00954   0.00335  -0.1023   0.5641   0.6441
   3.500   0.8331   0.00960   0.00345  -0.1024   0.5589   0.6456
   3.750   0.8596   0.00968   0.00355  -0.1023   0.5523   0.6474
   4.000   0.8856   0.00977   0.00365  -0.1020   0.5434   0.6493
   4.250   0.9105   0.00989   0.00374  -0.1016   0.5328   0.6512
   4.500   0.9363   0.00999   0.00385  -0.1014   0.5236   0.6530
   4.750   0.9618   0.01011   0.00398  -0.1011   0.5156   0.6548
   5.000   0.9867   0.01025   0.00411  -0.1007   0.5063   0.6565
   5.250   1.0116   0.01038   0.00426  -0.1003   0.4975   0.6579
   5.500   1.0353   0.01054   0.00444  -0.0997   0.4883   0.6594
   5.750   1.0592   0.01070   0.00463  -0.0991   0.4782   0.6612
   6.000   1.0809   0.01093   0.00483  -0.0982   0.4639   0.6631
   6.250   1.1000   0.01123   0.00508  -0.0967   0.4458   0.6651
   6.500   1.1187   0.01155   0.00535  -0.0952   0.4270   0.6671
   6.750   1.1371   0.01186   0.00562  -0.0937   0.4097   0.6691
   7.000   1.1542   0.01221   0.00592  -0.0920   0.3923   0.6710
   7.250   1.1672   0.01257   0.00624  -0.0895   0.3736   0.6726
   7.500   1.1773   0.01301   0.00662  -0.0864   0.3530   0.6743
   7.750   1.1859   0.01356   0.00711  -0.0833   0.3291   0.6760
   8.000   1.1920   0.01425   0.00770  -0.0798   0.3027   0.6779
   8.250   1.1964   0.01505   0.00839  -0.0763   0.2764   0.6801
   8.500   1.1994   0.01597   0.00920  -0.0728   0.2512   0.6824
   8.750   1.2056   0.01683   0.00999  -0.0700   0.2315   0.6847
   9.000   1.2121   0.01775   0.01084  -0.0673   0.2140   0.6869
   9.250   1.2184   0.01871   0.01178  -0.0648   0.1976   0.6886
   9.500   1.2246   0.01974   0.01278  -0.0624   0.1817   0.6904
   9.750   1.2290   0.02094   0.01392  -0.0600   0.1624   0.6923
  10.000   1.2308   0.02238   0.01525  -0.0575   0.1406   0.6944
  10.250   1.2335   0.02383   0.01663  -0.0552   0.1212   0.6965
  10.500   1.2341   0.02549   0.01818  -0.0529   0.1008   0.6986
  10.750   1.2373   0.02706   0.01968  -0.0510   0.0863   0.7007
  11.000   1.2438   0.02846   0.02106  -0.0495   0.0769   0.7028
  11.250   1.2483   0.03002   0.02261  -0.0480   0.0665   0.7047
  11.500   1.2560   0.03139   0.02402  -0.0467   0.0618   0.7068
  11.750   1.2648   0.03273   0.02540  -0.0456   0.0570   0.7090
  12.000   1.2705   0.03435   0.02702  -0.0444   0.0510   0.7112
  12.250   1.2791   0.03578   0.02849  -0.0435   0.0468   0.7135
  12.500   1.2843   0.03754   0.03025  -0.0424   0.0413   0.7156
  12.750   1.2922   0.03913   0.03187  -0.0416   0.0373   0.7176
  13.000   1.2972   0.04098   0.03375  -0.0407   0.0325   0.7194
  13.250   1.3032   0.04280   0.03562  -0.0400   0.0279   0.7213
  13.500   1.3073   0.04487   0.03770  -0.0393   0.0224   0.7234
  13.750   1.3093   0.04719   0.04002  -0.0386   0.0162   0.7256
  14.000   1.3081   0.04991   0.04273  -0.0379   0.0105   0.7278
  14.250   1.3093   0.05249   0.04535  -0.0374   0.0082   0.7301
  14.500   1.3126   0.05491   0.04783  -0.0371   0.0072   0.7323
  14.750   1.3157   0.05740   0.05040  -0.0369   0.0065   0.7343
  15.000   1.3203   0.05978   0.05287  -0.0367   0.0061   0.7363
  15.250   1.3239   0.06232   0.05552  -0.0367   0.0058   0.7385
  15.500   1.3279   0.06487   0.05817  -0.0368   0.0054   0.7407
  15.750   1.3296   0.06777   0.06116  -0.0369   0.0050   0.7429
  16.000   1.3323   0.07062   0.06411  -0.0372   0.0049   0.7450
  16.250   1.3338   0.07365   0.06723  -0.0376   0.0047   0.7471
  16.500   1.3335   0.07700   0.07069  -0.0381   0.0045   0.7490
  16.750   1.3352   0.08015   0.07395  -0.0387   0.0044   0.7514
  17.000   1.3358   0.08351   0.07743  -0.0394   0.0043   0.7539
  17.250   1.3358   0.08703   0.08106  -0.0402   0.0042   0.7565
  17.500   1.3353   0.09066   0.08480  -0.0412   0.0041   0.7588
  18.000   1.3323   0.09845   0.09282  -0.0436   0.0040   0.7633
  18.250   1.3303   0.10249   0.09699  -0.0450   0.0039   0.7657
  18.500   1.3272   0.10676   0.10137  -0.0465   0.0038   0.7682
  18.750   1.3232   0.11122   0.10597  -0.0482   0.0037   0.7707
  19.000   1.3191   0.11576   0.11062  -0.0501   0.0037   0.7734
<< Back to NN7 MK20 (nn7mk20-il)

Polar data table (+)

Polar graphs


<< Back to NN7 MK20 (nn7mk20-il)