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

LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: LDS-2 AIRFOIL (lds2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.48 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lds2-il-1000000.txt
Download as CSV file: xf-lds2-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LDS-2 AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3483   0.11868   0.11700  -0.0308   1.0000   0.0166
 -12.500  -0.8106   0.04351   0.04099  -0.0707   1.0000   0.0118
 -12.250  -0.8563   0.03676   0.03386  -0.0719   1.0000   0.0117
 -12.000  -0.8362   0.03723   0.03443  -0.0711   1.0000   0.0119
 -11.750  -0.8748   0.03343   0.03032  -0.0655   1.0000   0.0118
 -11.500  -0.8795   0.03190   0.02867  -0.0619   1.0000   0.0119
 -11.250  -0.8866   0.02973   0.02630  -0.0580   1.0000   0.0119
 -11.000  -0.8847   0.02846   0.02492  -0.0547   1.0000   0.0120
 -10.750  -0.8814   0.02752   0.02389  -0.0513   1.0000   0.0121
 -10.500  -0.8553   0.02566   0.02184  -0.0529   0.9974   0.0123
 -10.250  -0.8269   0.02429   0.02033  -0.0544   0.9942   0.0126
 -10.000  -0.8023   0.02249   0.01832  -0.0552   0.9896   0.0127
  -9.750  -0.7734   0.02119   0.01686  -0.0565   0.9860   0.0132
  -9.500  -0.7458   0.01992   0.01542  -0.0573   0.9811   0.0135
  -9.250  -0.7160   0.01885   0.01420  -0.0584   0.9763   0.0138
  -9.000  -0.6814   0.01837   0.01361  -0.0602   0.9728   0.0141
  -8.750  -0.6552   0.01630   0.01134  -0.0609   0.9646   0.0146
  -8.500  -0.6233   0.01549   0.01048  -0.0623   0.9571   0.0150
  -8.250  -0.5919   0.01486   0.00979  -0.0634   0.9475   0.0154
  -8.000  -0.5642   0.01439   0.00924  -0.0636   0.9350   0.0158
  -7.750  -0.5392   0.01382   0.00858  -0.0632   0.9220   0.0162
  -7.500  -0.5148   0.01340   0.00806  -0.0625   0.9097   0.0167
  -7.250  -0.4909   0.01298   0.00754  -0.0618   0.8984   0.0171
  -7.000  -0.4665   0.01270   0.00717  -0.0611   0.8875   0.0175
  -6.750  -0.4464   0.01185   0.00623  -0.0597   0.8769   0.0181
  -6.250  -0.3981   0.01122   0.00552  -0.0583   0.8576   0.0194
  -6.000  -0.3733   0.01097   0.00520  -0.0577   0.8491   0.0203
  -5.750  -0.3481   0.01071   0.00490  -0.0571   0.8404   0.0210
  -5.500  -0.3227   0.01051   0.00463  -0.0565   0.8324   0.0214
  -5.250  -0.3002   0.00994   0.00401  -0.0555   0.8238   0.0227
  -5.000  -0.2749   0.00972   0.00375  -0.0550   0.8161   0.0236
  -4.750  -0.2489   0.00952   0.00351  -0.0545   0.8080   0.0249
  -4.500  -0.2226   0.00940   0.00334  -0.0541   0.8009   0.0260
  -4.250  -0.1978   0.00903   0.00295  -0.0535   0.7934   0.0281
  -4.000  -0.1717   0.00888   0.00275  -0.0531   0.7863   0.0300
  -3.750  -0.1454   0.00867   0.00252  -0.0527   0.7792   0.0324
  -3.500  -0.1193   0.00849   0.00232  -0.0522   0.7719   0.0363
  -3.250  -0.0930   0.00831   0.00214  -0.0519   0.7646   0.0420
  -3.000  -0.0668   0.00813   0.00197  -0.0514   0.7570   0.0522
  -2.750  -0.0415   0.00784   0.00180  -0.0509   0.7500   0.0866
  -2.500  -0.0185   0.00727   0.00159  -0.0502   0.7427   0.1907
  -2.250   0.0030   0.00662   0.00141  -0.0492   0.7358   0.3321
  -2.000   0.0275   0.00628   0.00134  -0.0486   0.7288   0.4157
  -1.750   0.0533   0.00614   0.00130  -0.0481   0.7224   0.4623
  -1.500   0.0801   0.00602   0.00127  -0.0478   0.7161   0.4995
  -1.250   0.1067   0.00595   0.00125  -0.0475   0.7095   0.5274
  -1.000   0.1335   0.00590   0.00123  -0.0472   0.7027   0.5516
  -0.750   0.1595   0.00578   0.00123  -0.0467   0.6954   0.5909
  -0.500   0.1850   0.00569   0.00122  -0.0461   0.6887   0.6312
  -0.250   0.2120   0.00562   0.00122  -0.0458   0.6823   0.6529
   0.000   0.2384   0.00558   0.00121  -0.0454   0.6756   0.6745
   0.250   0.2647   0.00552   0.00121  -0.0450   0.6665   0.7010
   0.500   0.2900   0.00547   0.00121  -0.0443   0.6557   0.7315
   0.750   0.3155   0.00540   0.00122  -0.0437   0.6461   0.7645
   1.000   0.3405   0.00533   0.00125  -0.0429   0.6386   0.8018
   1.250   0.3653   0.00525   0.00129  -0.0421   0.6295   0.8448
   1.500   0.3912   0.00520   0.00135  -0.0414   0.6188   0.8867
   1.750   0.4207   0.00523   0.00141  -0.0416   0.6079   0.9225
   2.000   0.4553   0.00531   0.00149  -0.0429   0.5961   0.9465
   2.250   0.4917   0.00540   0.00156  -0.0447   0.5837   0.9606
   2.500   0.5291   0.00551   0.00163  -0.0467   0.5699   0.9686
   2.750   0.5638   0.00564   0.00171  -0.0482   0.5535   0.9751
   3.000   0.5992   0.00580   0.00179  -0.0498   0.5331   0.9798
   3.250   0.6323   0.00599   0.00189  -0.0510   0.5080   0.9851
   3.500   0.6676   0.00627   0.00200  -0.0528   0.4669   0.9883
   3.750   0.6997   0.00670   0.00218  -0.0540   0.4109   0.9925
   4.000   0.7323   0.00722   0.00241  -0.0554   0.3454   0.9960
   4.250   0.7655   0.00776   0.00267  -0.0570   0.2878   0.9989
   4.500   0.7915   0.00817   0.00289  -0.0570   0.2474   1.0000
   4.750   0.8097   0.00852   0.00309  -0.0552   0.2168   1.0000
   5.000   0.8280   0.00888   0.00331  -0.0535   0.1901   1.0000
   5.250   0.8471   0.00919   0.00352  -0.0518   0.1684   1.0000
   5.500   0.8664   0.00949   0.00373  -0.0502   0.1512   1.0000
   5.750   0.8861   0.00979   0.00396  -0.0487   0.1358   1.0000
   6.000   0.9057   0.01009   0.00419  -0.0472   0.1219   1.0000
   6.250   0.9257   0.01038   0.00442  -0.0457   0.1103   1.0000
   6.500   0.9458   0.01067   0.00467  -0.0443   0.1012   1.0000
   6.750   0.9656   0.01098   0.00492  -0.0428   0.0929   1.0000
   7.000   0.9865   0.01123   0.00517  -0.0415   0.0871   1.0000
   7.250   1.0061   0.01156   0.00545  -0.0400   0.0806   1.0000
   7.500   1.0269   0.01183   0.00573  -0.0387   0.0762   1.0000
   7.750   1.0469   0.01212   0.00601  -0.0373   0.0721   1.0000
   8.000   1.0653   0.01251   0.00637  -0.0357   0.0670   1.0000
   8.250   1.0864   0.01274   0.00662  -0.0345   0.0648   1.0000
   8.500   1.1059   0.01305   0.00693  -0.0331   0.0617   1.0000
   8.750   1.1235   0.01346   0.00732  -0.0313   0.0580   1.0000
   9.000   1.1426   0.01378   0.00767  -0.0299   0.0559   1.0000
   9.250   1.1620   0.01407   0.00799  -0.0285   0.0540   1.0000
   9.500   1.1797   0.01443   0.00835  -0.0268   0.0519   1.0000
   9.750   1.1938   0.01485   0.00877  -0.0244   0.0497   1.0000
  10.000   1.2059   0.01534   0.00929  -0.0218   0.0475   1.0000
  10.250   1.2229   0.01564   0.00964  -0.0200   0.0465   1.0000
  10.500   1.2394   0.01600   0.01003  -0.0182   0.0451   1.0000
  10.750   1.2547   0.01644   0.01048  -0.0164   0.0436   1.0000
  11.000   1.2685   0.01699   0.01103  -0.0144   0.0418   1.0000
  11.250   1.2784   0.01776   0.01185  -0.0120   0.0399   1.0000
  11.500   1.2960   0.01815   0.01229  -0.0107   0.0391   1.0000
  11.750   1.3116   0.01867   0.01285  -0.0092   0.0382   1.0000
  12.000   1.3269   0.01922   0.01344  -0.0078   0.0370   1.0000
  12.250   1.3411   0.01987   0.01411  -0.0063   0.0358   1.0000
  12.500   1.3519   0.02075   0.01500  -0.0045   0.0342   1.0000
  12.750   1.3611   0.02177   0.01609  -0.0027   0.0331   1.0000
  13.000   1.3764   0.02243   0.01680  -0.0016   0.0325   1.0000
  13.250   1.3908   0.02316   0.01760  -0.0005   0.0316   1.0000
  13.500   1.4041   0.02398   0.01846   0.0006   0.0308   1.0000
  13.750   1.4160   0.02495   0.01946   0.0018   0.0297   1.0000
  14.000   1.4255   0.02612   0.02065   0.0030   0.0286   1.0000
  14.250   1.4315   0.02760   0.02220   0.0043   0.0275   1.0000
  14.500   1.4442   0.02859   0.02326   0.0052   0.0270   1.0000
  14.750   1.4559   0.02969   0.02442   0.0060   0.0263   1.0000
  15.000   1.4674   0.03082   0.02560   0.0067   0.0254   1.0000
  15.250   1.4764   0.03218   0.02700   0.0075   0.0246   1.0000
  15.500   1.4819   0.03389   0.02877   0.0083   0.0240   1.0000
  15.750   1.4818   0.03614   0.03108   0.0092   0.0230   1.0000
  16.000   1.4888   0.03780   0.03283   0.0097   0.0226   1.0000
  16.250   1.4971   0.03938   0.03449   0.0101   0.0221   1.0000
  16.500   1.5039   0.04112   0.03630   0.0105   0.0215   1.0000
  16.750   1.5085   0.04313   0.03840   0.0108   0.0210   1.0000
  17.000   1.5119   0.04533   0.04066   0.0109   0.0205   1.0000
  17.250   1.5129   0.04785   0.04324   0.0110   0.0199   1.0000
  17.500   1.5101   0.05087   0.04633   0.0109   0.0194   1.0000
  17.750   1.5027   0.05456   0.05011   0.0105   0.0189   1.0000
  18.000   1.5001   0.05777   0.05343   0.0100   0.0186   1.0000
  18.250   1.5006   0.06067   0.05643   0.0095   0.0183   1.0000
  18.500   1.5012   0.06360   0.05946   0.0088   0.0178   1.0000
  18.750   1.4939   0.06767   0.06364   0.0078   0.0176   1.0000
  19.000   1.4884   0.07161   0.06768   0.0066   0.0173   1.0000
  19.250   1.4799   0.07605   0.07222   0.0052   0.0170   1.0000
<< Back to LDS-2 AIRFOIL (lds2-il)

Polar data table (+)

Polar graphs


<< Back to LDS-2 AIRFOIL (lds2-il)