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

NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(2)-215 MOD B (n63215b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.28 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63215b-il-1000000.txt
Download as CSV file: xf-n63215b-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)-215 MOD B                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.0885   0.10678   0.10342  -0.0223   1.0000   0.0114
 -19.500  -1.1019   0.10042   0.09696  -0.0259   1.0000   0.0115
 -19.250  -1.1157   0.09425   0.09068  -0.0292   1.0000   0.0115
 -19.000  -1.1343   0.08746   0.08376  -0.0329   1.0000   0.0115
 -18.750  -1.1452   0.08209   0.07830  -0.0356   1.0000   0.0116
 -18.500  -1.1568   0.07674   0.07284  -0.0383   1.0000   0.0117
 -18.250  -1.1679   0.07163   0.06762  -0.0407   1.0000   0.0116
 -18.000  -1.1789   0.06672   0.06261  -0.0429   1.0000   0.0118
 -17.750  -1.1833   0.06281   0.05862  -0.0446   1.0000   0.0119
 -17.500  -1.1908   0.05862   0.05434  -0.0463   1.0000   0.0119
 -17.250  -1.1955   0.05489   0.05053  -0.0477   1.0000   0.0122
 -17.000  -1.1971   0.05167   0.04722  -0.0487   1.0000   0.0122
 -16.750  -1.1966   0.04878   0.04427  -0.0496   1.0000   0.0123
 -16.500  -1.1948   0.04612   0.04155  -0.0503   1.0000   0.0125
 -16.250  -1.1921   0.04364   0.03901  -0.0508   1.0000   0.0126
 -16.000  -1.1861   0.04161   0.03694  -0.0511   1.0000   0.0128
 -15.750  -1.1839   0.03924   0.03449  -0.0514   1.0000   0.0129
 -15.500  -1.1792   0.03718   0.03236  -0.0515   1.0000   0.0130
 -15.250  -1.1697   0.03562   0.03077  -0.0514   1.0000   0.0133
 -15.000  -1.1645   0.03369   0.02877  -0.0513   1.0000   0.0134
 -14.750  -1.1563   0.03209   0.02712  -0.0511   1.0000   0.0136
 -14.500  -1.1446   0.03083   0.02581  -0.0508   1.0000   0.0139
 -14.250  -1.1370   0.02924   0.02415  -0.0504   1.0000   0.0141
 -14.000  -1.1289   0.02777   0.02262  -0.0499   1.0000   0.0141
 -13.750  -1.1197   0.02641   0.02121  -0.0492   1.0000   0.0143
 -13.500  -1.1150   0.02478   0.01954  -0.0484   1.0000   0.0148
 -13.250  -1.1054   0.02356   0.01829  -0.0475   1.0000   0.0151
 -13.000  -1.0945   0.02250   0.01721  -0.0465   1.0000   0.0154
 -12.750  -1.0816   0.02163   0.01631  -0.0455   1.0000   0.0158
 -12.500  -1.0688   0.02080   0.01545  -0.0444   1.0000   0.0162
 -12.250  -1.0553   0.02007   0.01469  -0.0433   1.0000   0.0166
 -12.000  -1.0429   0.01934   0.01392  -0.0418   1.0000   0.0170
 -11.750  -1.0313   0.01867   0.01322  -0.0401   1.0000   0.0173
 -11.500  -1.0244   0.01796   0.01248  -0.0376   1.0000   0.0177
 -11.250  -1.0152   0.01729   0.01181  -0.0352   1.0000   0.0185
 -11.000  -0.9978   0.01686   0.01138  -0.0338   1.0000   0.0192
 -10.750  -0.9617   0.01641   0.01093  -0.0360   0.9801   0.0202
 -10.500  -0.9216   0.01604   0.01052  -0.0388   0.9614   0.0211
 -10.250  -0.8967   0.01537   0.00978  -0.0390   0.9345   0.0222
 -10.000  -0.8768   0.01506   0.00940  -0.0378   0.9150   0.0230
  -9.750  -0.8548   0.01485   0.00915  -0.0368   0.9004   0.0240
  -9.500  -0.8337   0.01453   0.00876  -0.0357   0.8875   0.0246
  -9.250  -0.8106   0.01429   0.00846  -0.0349   0.8759   0.0253
  -9.000  -0.7895   0.01385   0.00796  -0.0339   0.8652   0.0261
  -8.750  -0.7673   0.01347   0.00755  -0.0331   0.8555   0.0273
  -8.500  -0.7432   0.01318   0.00723  -0.0325   0.8463   0.0281
  -8.250  -0.7186   0.01292   0.00693  -0.0319   0.8383   0.0290
  -8.000  -0.6932   0.01267   0.00664  -0.0315   0.8304   0.0298
  -7.750  -0.6676   0.01247   0.00638  -0.0310   0.8233   0.0304
  -7.500  -0.6436   0.01201   0.00590  -0.0305   0.8160   0.0318
  -7.250  -0.6182   0.01173   0.00559  -0.0301   0.8091   0.0331
  -7.000  -0.5916   0.01149   0.00534  -0.0298   0.8025   0.0345
  -6.750  -0.5649   0.01128   0.00509  -0.0296   0.7956   0.0357
  -6.500  -0.5388   0.01098   0.00476  -0.0292   0.7891   0.0376
  -6.250  -0.5121   0.01069   0.00447  -0.0290   0.7821   0.0400
  -6.000  -0.4852   0.01049   0.00423  -0.0288   0.7755   0.0423
  -5.750  -0.4581   0.01018   0.00395  -0.0286   0.7694   0.0479
  -5.500  -0.4313   0.00988   0.00369  -0.0284   0.7622   0.0593
  -5.250  -0.4050   0.00949   0.00341  -0.0282   0.7539   0.0834
  -5.000  -0.3788   0.00907   0.00313  -0.0280   0.7446   0.1182
  -4.750  -0.3522   0.00863   0.00286  -0.0279   0.7362   0.1592
  -4.500  -0.3261   0.00809   0.00257  -0.0279   0.7281   0.2198
  -4.250  -0.2995   0.00753   0.00228  -0.0279   0.7206   0.2907
  -4.000  -0.2723   0.00706   0.00207  -0.0280   0.7142   0.3599
  -3.750  -0.2441   0.00680   0.00194  -0.0280   0.7080   0.4030
  -3.500  -0.2151   0.00663   0.00186  -0.0282   0.7006   0.4330
  -3.250  -0.1861   0.00654   0.00178  -0.0282   0.6935   0.4550
  -3.000  -0.1567   0.00646   0.00174  -0.0284   0.6864   0.4746
  -2.750  -0.1275   0.00641   0.00168  -0.0284   0.6777   0.4909
  -2.500  -0.0980   0.00635   0.00164  -0.0285   0.6682   0.5039
  -2.250  -0.0688   0.00632   0.00161  -0.0286   0.6591   0.5179
  -2.000  -0.0392   0.00627   0.00159  -0.0287   0.6505   0.5321
  -1.750  -0.0098   0.00629   0.00156  -0.0288   0.6409   0.5429
  -1.500   0.0195   0.00628   0.00155  -0.0289   0.6300   0.5548
  -1.250   0.0489   0.00627   0.00155  -0.0290   0.6196   0.5653
  -1.000   0.0784   0.00631   0.00154  -0.0291   0.6081   0.5736
  -0.750   0.1076   0.00632   0.00153  -0.0292   0.5941   0.5805
  -0.500   0.1368   0.00636   0.00152  -0.0293   0.5774   0.5875
  -0.250   0.1657   0.00643   0.00152  -0.0293   0.5534   0.5937
   0.000   0.1936   0.00661   0.00155  -0.0292   0.5058   0.5998
   0.250   0.2170   0.00738   0.00174  -0.0287   0.3615   0.6059
   0.500   0.2448   0.00762   0.00186  -0.0286   0.3325   0.6118
   0.750   0.2732   0.00778   0.00195  -0.0287   0.3103   0.6185
   1.250   0.3301   0.00807   0.00211  -0.0288   0.2738   0.6312
   1.500   0.3587   0.00821   0.00219  -0.0288   0.2594   0.6375
   1.750   0.3873   0.00834   0.00227  -0.0289   0.2465   0.6433
   2.000   0.4156   0.00847   0.00236  -0.0289   0.2346   0.6494
   2.250   0.4441   0.00862   0.00246  -0.0289   0.2234   0.6557
   2.500   0.4726   0.00873   0.00256  -0.0290   0.2148   0.6619
   2.750   0.5007   0.00888   0.00268  -0.0290   0.2056   0.6688
   3.000   0.5293   0.00899   0.00278  -0.0290   0.1991   0.6754
   3.250   0.5572   0.00915   0.00291  -0.0290   0.1903   0.6819
   3.500   0.5856   0.00927   0.00302  -0.0290   0.1841   0.6885
   3.750   0.6136   0.00942   0.00315  -0.0290   0.1770   0.6948
   4.000   0.6415   0.00957   0.00329  -0.0290   0.1710   0.7019
   4.250   0.6696   0.00971   0.00342  -0.0290   0.1659   0.7089
   4.500   0.6970   0.00990   0.00359  -0.0289   0.1593   0.7160
   4.750   0.7249   0.01004   0.00374  -0.0288   0.1550   0.7228
   5.000   0.7525   0.01019   0.00389  -0.0288   0.1503   0.7292
   5.250   0.7796   0.01039   0.00408  -0.0286   0.1451   0.7360
   5.500   0.8069   0.01057   0.00426  -0.0285   0.1414   0.7424
   5.750   0.8344   0.01071   0.00443  -0.0285   0.1384   0.7491
   6.000   0.8616   0.01090   0.00461  -0.0283   0.1346   0.7559
   6.250   0.8879   0.01112   0.00483  -0.0281   0.1300   0.7628
   6.500   0.9146   0.01133   0.00506  -0.0279   0.1267   0.7705
   6.750   0.9416   0.01147   0.00524  -0.0278   0.1243   0.7778
   7.000   0.9680   0.01167   0.00544  -0.0275   0.1208   0.7857
   7.250   0.9935   0.01193   0.00569  -0.0272   0.1159   0.7933
   7.500   1.0193   0.01215   0.00593  -0.0269   0.1122   0.8012
   7.750   1.0456   0.01233   0.00613  -0.0267   0.1092   0.8088
   8.000   1.0709   0.01256   0.00637  -0.0263   0.1059   0.8168
   8.250   1.0951   0.01288   0.00667  -0.0258   0.1009   0.8250
   8.500   1.1201   0.01310   0.00694  -0.0254   0.0987   0.8339
   8.750   1.1449   0.01331   0.00719  -0.0250   0.0970   0.8431
   9.000   1.1691   0.01355   0.00747  -0.0244   0.0949   0.8536
   9.250   1.1922   0.01382   0.00776  -0.0237   0.0927   0.8646
   9.500   1.2143   0.01413   0.00809  -0.0229   0.0897   0.8769
   9.750   1.2348   0.01448   0.00849  -0.0217   0.0868   0.8912
  10.000   1.2559   0.01468   0.00877  -0.0206   0.0860   0.9084
  10.500   1.2930   0.01506   0.00932  -0.0174   0.0830   1.0000
  10.750   1.3150   0.01544   0.00969  -0.0168   0.0813   1.0000
  11.000   1.3352   0.01585   0.01009  -0.0159   0.0793   1.0000
  11.250   1.3516   0.01633   0.01056  -0.0144   0.0768   1.0000
  11.500   1.3672   0.01682   0.01106  -0.0127   0.0749   1.0000
  11.750   1.3856   0.01717   0.01145  -0.0116   0.0743   1.0000
  12.000   1.4035   0.01756   0.01189  -0.0104   0.0735   1.0000
  12.250   1.4207   0.01801   0.01236  -0.0091   0.0724   1.0000
  12.500   1.4371   0.01851   0.01289  -0.0079   0.0710   1.0000
  12.750   1.4528   0.01907   0.01345  -0.0067   0.0693   1.0000
  13.000   1.4673   0.01971   0.01411  -0.0055   0.0678   1.0000
  13.250   1.4808   0.02044   0.01486  -0.0042   0.0664   1.0000
  13.500   1.4922   0.02132   0.01577  -0.0028   0.0646   1.0000
  13.750   1.5083   0.02194   0.01642  -0.0019   0.0634   1.0000
  14.000   1.5233   0.02264   0.01716  -0.0010   0.0626   1.0000
  14.250   1.5373   0.02342   0.01799   0.0000   0.0616   1.0000
  14.500   1.5508   0.02426   0.01884   0.0009   0.0599   1.0000
  14.750   1.5627   0.02524   0.01983   0.0018   0.0584   1.0000
  15.000   1.5731   0.02635   0.02095   0.0027   0.0564   1.0000
  15.250   1.5834   0.02750   0.02215   0.0036   0.0560   1.0000
  15.500   1.5944   0.02862   0.02329   0.0043   0.0533   1.0000
  15.750   1.6044   0.02985   0.02458   0.0050   0.0529   1.0000
  16.000   1.6140   0.03114   0.02591   0.0056   0.0516   1.0000
  16.250   1.6217   0.03263   0.02743   0.0062   0.0500   1.0000
  16.500   1.6286   0.03422   0.02907   0.0067   0.0493   1.0000
  16.750   1.6320   0.03617   0.03103   0.0071   0.0470   1.0000
  17.000   1.6382   0.03794   0.03287   0.0074   0.0469   1.0000
  17.250   1.6399   0.04018   0.03517   0.0076   0.0456   1.0000
  17.500   1.6476   0.04189   0.03696   0.0076   0.0448   1.0000
  17.750   1.6518   0.04404   0.03918   0.0075   0.0444   1.0000
  18.000   1.6549   0.04638   0.04161   0.0072   0.0436   1.0000
  18.250   1.6558   0.04904   0.04433   0.0068   0.0425   1.0000
  18.500   1.6510   0.05246   0.04779   0.0060   0.0403   1.0000
  18.750   1.6413   0.05667   0.05205   0.0047   0.0378   1.0000
  19.000   1.6377   0.06027   0.05575   0.0035   0.0374   1.0000
  19.250   1.6291   0.06469   0.06026   0.0017   0.0357   1.0000
<< Back to NACA 63(2)-215 MOD B (n63215b-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63(2)-215 MOD B (n63215b-il)