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

SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SD7062 (14%) (sd7062-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.55 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7062-il-1000000.txt
Download as CSV file: xf-sd7062-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7062 (14%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4635   0.06916   0.06731  -0.0574   1.0000   0.0173
 -11.000  -0.5283   0.05315   0.05120  -0.0691   1.0000   0.0166
 -10.750  -0.5740   0.04265   0.04049  -0.0796   0.9995   0.0164
 -10.500  -0.5872   0.03163   0.02880  -0.0962   0.9691   0.0159
 -10.250  -0.5821   0.02742   0.02413  -0.0980   0.9422   0.0158
 -10.000  -0.5748   0.02507   0.02145  -0.0968   0.9172   0.0157
  -9.750  -0.5615   0.02352   0.01964  -0.0956   0.8973   0.0158
  -9.500  -0.5462   0.02197   0.01784  -0.0945   0.8807   0.0159
  -9.250  -0.5279   0.02069   0.01633  -0.0935   0.8665   0.0160
  -8.750  -0.4865   0.01849   0.01375  -0.0920   0.8415   0.0162
  -8.500  -0.4638   0.01760   0.01270  -0.0914   0.8309   0.0163
  -8.250  -0.4403   0.01680   0.01175  -0.0909   0.8200   0.0165
  -8.000  -0.4156   0.01616   0.01099  -0.0904   0.8101   0.0167
  -7.500  -0.3646   0.01516   0.00976  -0.0896   0.7907   0.0172
  -7.250  -0.3387   0.01472   0.00919  -0.0892   0.7814   0.0173
  -7.000  -0.3150   0.01357   0.00796  -0.0887   0.7724   0.0176
  -6.750  -0.2902   0.01286   0.00717  -0.0883   0.7634   0.0179
  -6.500  -0.2638   0.01236   0.00664  -0.0881   0.7544   0.0182
  -6.250  -0.2373   0.01198   0.00619  -0.0877   0.7456   0.0185
  -6.000  -0.2102   0.01160   0.00578  -0.0875   0.7368   0.0188
  -5.750  -0.1833   0.01128   0.00538  -0.0873   0.7280   0.0192
  -5.500  -0.1558   0.01094   0.00500  -0.0871   0.7193   0.0196
  -5.250  -0.1286   0.01067   0.00465  -0.0869   0.7103   0.0199
  -5.000  -0.1007   0.01039   0.00433  -0.0867   0.7017   0.0203
  -4.750  -0.0731   0.01019   0.00406  -0.0865   0.6926   0.0206
  -4.500  -0.0457   0.00975   0.00358  -0.0864   0.6838   0.0214
  -4.250  -0.0180   0.00954   0.00331  -0.0862   0.6747   0.0222
  -4.000   0.0104   0.00935   0.00310  -0.0861   0.6657   0.0232
  -3.750   0.0384   0.00922   0.00290  -0.0860   0.6567   0.0241
  -3.500   0.0667   0.00899   0.00265  -0.0859   0.6474   0.0254
  -3.250   0.0948   0.00885   0.00247  -0.0858   0.6383   0.0272
  -3.000   0.1232   0.00869   0.00229  -0.0857   0.6287   0.0303
  -2.750   0.1512   0.00848   0.00211  -0.0856   0.6197   0.0450
  -2.500   0.1790   0.00818   0.00196  -0.0856   0.6100   0.0860
  -2.250   0.2070   0.00796   0.00185  -0.0856   0.6010   0.1252
  -2.000   0.2349   0.00776   0.00177  -0.0855   0.5911   0.1689
  -1.750   0.2631   0.00757   0.00170  -0.0855   0.5820   0.2144
  -1.250   0.3192   0.00724   0.00162  -0.0855   0.5628   0.3196
  -1.000   0.3470   0.00712   0.00161  -0.0855   0.5532   0.3745
  -0.750   0.3753   0.00700   0.00161  -0.0855   0.5436   0.4246
  -0.500   0.4033   0.00694   0.00162  -0.0854   0.5340   0.4697
  -0.250   0.4315   0.00689   0.00164  -0.0854   0.5240   0.5098
   0.000   0.4596   0.00685   0.00167  -0.0853   0.5147   0.5530
   0.250   0.4875   0.00685   0.00171  -0.0852   0.5044   0.5864
   0.500   0.5158   0.00684   0.00174  -0.0851   0.4950   0.6150
   0.750   0.5436   0.00688   0.00179  -0.0850   0.4850   0.6448
   1.000   0.5716   0.00688   0.00184  -0.0849   0.4755   0.6766
   1.250   0.5992   0.00691   0.00191  -0.0847   0.4659   0.7061
   1.500   0.6269   0.00694   0.00197  -0.0845   0.4560   0.7353
   1.750   0.6543   0.00697   0.00204  -0.0842   0.4469   0.7662
   2.000   0.6810   0.00701   0.00212  -0.0839   0.4369   0.7985
   2.250   0.7076   0.00702   0.00221  -0.0834   0.4280   0.8340
   2.500   0.7325   0.00707   0.00230  -0.0826   0.4185   0.8735
   2.750   0.7558   0.00705   0.00237  -0.0813   0.4099   0.9212
   3.000   0.7895   0.00711   0.00243  -0.0824   0.4000   0.9839
   3.250   0.8199   0.00724   0.00251  -0.0829   0.3905   1.0000
   3.500   0.8474   0.00739   0.00260  -0.0828   0.3816   1.0000
   3.750   0.8747   0.00755   0.00270  -0.0827   0.3721   1.0000
   4.000   0.9021   0.00770   0.00281  -0.0826   0.3635   1.0000
   4.250   0.9290   0.00788   0.00293  -0.0824   0.3539   1.0000
   4.500   0.9564   0.00803   0.00305  -0.0823   0.3459   1.0000
   5.000   1.0101   0.00839   0.00331  -0.0819   0.3280   1.0000
   5.250   1.0364   0.00861   0.00347  -0.0817   0.3190   1.0000
   5.500   1.0633   0.00878   0.00361  -0.0815   0.3107   1.0000
   5.750   1.0893   0.00900   0.00379  -0.0812   0.3023   1.0000
   6.000   1.1158   0.00918   0.00394  -0.0810   0.2943   1.0000
   6.250   1.1415   0.00942   0.00413  -0.0806   0.2860   1.0000
   6.500   1.1676   0.00961   0.00431  -0.0804   0.2786   1.0000
   6.750   1.1928   0.00987   0.00452  -0.0800   0.2705   1.0000
   7.000   1.2185   0.01008   0.00471  -0.0797   0.2629   1.0000
   7.250   1.2432   0.01035   0.00494  -0.0792   0.2552   1.0000
   7.500   1.2686   0.01056   0.00514  -0.0789   0.2484   1.0000
   7.750   1.2925   0.01087   0.00540  -0.0783   0.2402   1.0000
   8.000   1.3175   0.01109   0.00562  -0.0779   0.2341   1.0000
   8.250   1.3407   0.01141   0.00590  -0.0772   0.2263   1.0000
   8.500   1.3650   0.01165   0.00614  -0.0767   0.2200   1.0000
   8.750   1.3876   0.01198   0.00643  -0.0760   0.2128   1.0000
   9.000   1.4107   0.01226   0.00671  -0.0753   0.2067   1.0000
   9.250   1.4327   0.01259   0.00702  -0.0745   0.1999   1.0000
   9.500   1.4543   0.01293   0.00734  -0.0736   0.1936   1.0000
   9.750   1.4757   0.01325   0.00766  -0.0726   0.1876   1.0000
  10.000   1.4947   0.01367   0.00804  -0.0714   0.1809   1.0000
  10.250   1.5148   0.01397   0.00836  -0.0702   0.1757   1.0000
  10.500   1.5302   0.01439   0.00876  -0.0683   0.1697   1.0000
  10.750   1.5464   0.01477   0.00915  -0.0665   0.1646   1.0000
  11.000   1.5618   0.01520   0.00958  -0.0647   0.1591   1.0000
  11.250   1.5747   0.01576   0.01012  -0.0626   0.1531   1.0000
  11.500   1.5909   0.01619   0.01057  -0.0611   0.1488   1.0000
  11.750   1.6037   0.01678   0.01116  -0.0591   0.1436   1.0000
  12.000   1.6166   0.01741   0.01180  -0.0573   0.1387   1.0000
  12.250   1.6303   0.01802   0.01243  -0.0557   0.1344   1.0000
  12.500   1.6405   0.01884   0.01324  -0.0538   0.1293   1.0000
  12.750   1.6528   0.01959   0.01401  -0.0522   0.1252   1.0000
  13.000   1.6643   0.02042   0.01486  -0.0507   0.1211   1.0000
  13.250   1.6723   0.02150   0.01594  -0.0489   0.1164   1.0000
  13.500   1.6834   0.02243   0.01692  -0.0476   0.1130   1.0000
  13.750   1.6931   0.02350   0.01801  -0.0462   0.1093   1.0000
  14.000   1.6995   0.02485   0.01937  -0.0447   0.1052   1.0000
  14.250   1.7081   0.02611   0.02067  -0.0435   0.1021   1.0000
  14.500   1.7168   0.02740   0.02200  -0.0425   0.0991   1.0000
  14.750   1.7221   0.02900   0.02363  -0.0413   0.0958   1.0000
  15.000   1.7252   0.03085   0.02551  -0.0402   0.0922   1.0000
  15.250   1.7331   0.03236   0.02707  -0.0395   0.0898   1.0000
  15.500   1.7375   0.03422   0.02898  -0.0387   0.0870   1.0000
  15.750   1.7377   0.03652   0.03130  -0.0379   0.0836   1.0000
  16.000   1.7405   0.03867   0.03352  -0.0374   0.0813   1.0000
  16.250   1.7442   0.04080   0.03571  -0.0370   0.0787   1.0000
  16.500   1.7437   0.04343   0.03838  -0.0367   0.0758   1.0000
  16.750   1.7391   0.04661   0.04159  -0.0366   0.0727   1.0000
  17.000   1.7417   0.04910   0.04415  -0.0366   0.0709   1.0000
  17.250   1.7406   0.05206   0.04718  -0.0367   0.0686   1.0000
  17.500   1.7358   0.05555   0.05071  -0.0371   0.0662   1.0000
  17.750   1.7286   0.05946   0.05469  -0.0376   0.0637   1.0000
  18.000   1.7279   0.06265   0.05797  -0.0382   0.0622   1.0000
  18.250   1.7232   0.06641   0.06180  -0.0390   0.0604   1.0000
  18.500   1.7150   0.07075   0.06620  -0.0401   0.0583   1.0000
  18.750   1.7040   0.07560   0.07111  -0.0414   0.0564   1.0000
  19.000   1.6984   0.07976   0.07537  -0.0427   0.0548   1.0000
  19.250   1.6913   0.08423   0.07992  -0.0441   0.0532   1.0000
<< Back to SD7062 (14%) (sd7062-il)

Polar data table (+)

Polar graphs


<< Back to SD7062 (14%) (sd7062-il)