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

Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf)
Reynolds number: 1,000,000
Max Cl/Cd: 72.43 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk0009-jf-1000000.txt
Download as CSV file: xf-joukowsk0009-jf-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=9%                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -1.0340   0.12095   0.11900   0.0357   1.0000   0.0094
 -15.750  -1.0902   0.10307   0.10093   0.0246   1.0000   0.0092
 -15.500  -1.1263   0.09082   0.08853   0.0168   1.0000   0.0091
 -15.250  -1.1520   0.08123   0.07881   0.0107   1.0000   0.0091
 -15.000  -1.1813   0.07130   0.06872   0.0042   1.0000   0.0090
 -14.750  -1.2101   0.06192   0.05917  -0.0021   1.0000   0.0089
 -14.500  -1.2266   0.05502   0.05211  -0.0069   1.0000   0.0089
 -14.250  -1.2427   0.04863   0.04556  -0.0112   1.0000   0.0089
 -14.000  -1.2563   0.04322   0.03999  -0.0146   1.0000   0.0090
 -13.750  -1.2640   0.03923   0.03585  -0.0167   1.0000   0.0090
 -13.500  -1.2722   0.03583   0.03230  -0.0176   1.0000   0.0091
 -13.250  -1.2765   0.03347   0.02982  -0.0171   1.0000   0.0092
 -13.000  -1.2814   0.03159   0.02781  -0.0152   1.0000   0.0093
 -12.750  -1.2780   0.03005   0.02614  -0.0135   1.0000   0.0094
 -12.500  -1.2686   0.02854   0.02449  -0.0123   1.0000   0.0094
 -12.250  -1.2541   0.02740   0.02323  -0.0114   1.0000   0.0095
 -12.000  -1.2471   0.02511   0.02072  -0.0101   1.0000   0.0098
 -11.750  -1.2368   0.02301   0.01845  -0.0090   1.0000   0.0102
 -11.500  -1.2183   0.02189   0.01725  -0.0083   1.0000   0.0104
 -11.250  -1.1976   0.02100   0.01628  -0.0078   1.0000   0.0107
 -11.000  -1.1757   0.02024   0.01547  -0.0073   1.0000   0.0111
 -10.750  -1.1533   0.01949   0.01464  -0.0069   1.0000   0.0114
 -10.500  -1.1305   0.01875   0.01381  -0.0064   1.0000   0.0118
 -10.250  -1.1068   0.01813   0.01311  -0.0061   1.0000   0.0122
 -10.000  -1.0822   0.01761   0.01254  -0.0058   1.0000   0.0126
  -9.750  -1.0594   0.01672   0.01154  -0.0053   1.0000   0.0129
  -9.500  -1.0376   0.01554   0.01026  -0.0048   1.0000   0.0138
  -9.250  -1.0125   0.01496   0.00964  -0.0046   1.0000   0.0144
  -9.000  -0.9870   0.01446   0.00910  -0.0044   1.0000   0.0152
  -8.750  -0.9611   0.01399   0.00858  -0.0041   1.0000   0.0159
  -8.500  -0.9348   0.01361   0.00815  -0.0039   1.0000   0.0165
  -8.250  -0.9101   0.01280   0.00727  -0.0036   1.0000   0.0178
  -8.000  -0.8841   0.01233   0.00678  -0.0034   1.0000   0.0191
  -7.750  -0.8574   0.01198   0.00641  -0.0032   1.0000   0.0204
  -7.500  -0.8304   0.01171   0.00611  -0.0031   1.0000   0.0214
  -7.250  -0.8044   0.01110   0.00547  -0.0029   1.0000   0.0237
  -7.000  -0.7775   0.01075   0.00511  -0.0027   1.0000   0.0256
  -6.750  -0.7502   0.01048   0.00481  -0.0026   1.0000   0.0273
  -6.500  -0.7233   0.01002   0.00435  -0.0025   1.0000   0.0310
  -6.250  -0.6959   0.00974   0.00408  -0.0024   1.0000   0.0342
  -6.000  -0.6687   0.00938   0.00373  -0.0022   1.0000   0.0395
  -5.750  -0.6411   0.00913   0.00348  -0.0022   1.0000   0.0440
  -5.500  -0.6138   0.00878   0.00319  -0.0021   1.0000   0.0530
  -5.250  -0.5863   0.00847   0.00293  -0.0020   1.0000   0.0632
  -5.000  -0.5588   0.00818   0.00270  -0.0019   1.0000   0.0758
  -4.750  -0.5312   0.00790   0.00249  -0.0019   1.0000   0.0915
  -4.500  -0.5037   0.00759   0.00228  -0.0018   1.0000   0.1118
  -4.250  -0.4760   0.00732   0.00210  -0.0018   1.0000   0.1329
  -4.000  -0.4485   0.00702   0.00192  -0.0017   1.0000   0.1600
  -3.750  -0.4210   0.00673   0.00177  -0.0017   1.0000   0.1897
  -3.500  -0.3898   0.00647   0.00163  -0.0025   0.9891   0.2206
  -3.250  -0.3540   0.00623   0.00152  -0.0041   0.9615   0.2557
  -3.000  -0.3272   0.00608   0.00143  -0.0037   0.9281   0.2873
  -2.750  -0.3026   0.00596   0.00133  -0.0027   0.8970   0.3170
  -2.500  -0.2768   0.00586   0.00124  -0.0021   0.8684   0.3464
  -2.250  -0.2502   0.00576   0.00116  -0.0016   0.8415   0.3772
  -2.000  -0.2231   0.00568   0.00109  -0.0013   0.8159   0.4067
  -1.750  -0.1957   0.00561   0.00102  -0.0010   0.7909   0.4354
  -1.500  -0.1680   0.00554   0.00096  -0.0008   0.7660   0.4636
  -1.250  -0.1402   0.00549   0.00092  -0.0006   0.7419   0.4913
  -1.000  -0.1123   0.00546   0.00088  -0.0005   0.7175   0.5184
  -0.750  -0.0843   0.00542   0.00085  -0.0003   0.6935   0.5448
  -0.500  -0.0562   0.00540   0.00083  -0.0002   0.6695   0.5702
  -0.250  -0.0281   0.00538   0.00082  -0.0001   0.6449   0.5954
   0.000   0.0000   0.00538   0.00082   0.0000   0.6206   0.6206
   0.250   0.0281   0.00538   0.00082   0.0001   0.5954   0.6449
   0.500   0.0562   0.00540   0.00083   0.0002   0.5701   0.6695
   0.750   0.0843   0.00542   0.00085   0.0003   0.5448   0.6935
   1.250   0.1402   0.00549   0.00092   0.0006   0.4914   0.7418
   1.500   0.1680   0.00554   0.00096   0.0008   0.4634   0.7660
   1.750   0.1957   0.00561   0.00102   0.0010   0.4353   0.7909
   2.000   0.2231   0.00568   0.00109   0.0013   0.4067   0.8158
   2.250   0.2502   0.00576   0.00116   0.0016   0.3773   0.8414
   2.500   0.2768   0.00586   0.00124   0.0021   0.3464   0.8683
   2.750   0.3026   0.00596   0.00133   0.0027   0.3171   0.8969
   3.000   0.3272   0.00608   0.00143   0.0037   0.2874   0.9282
   3.250   0.3540   0.00623   0.00152   0.0041   0.2553   0.9614
   3.500   0.3898   0.00647   0.00163   0.0024   0.2206   0.9891
   3.750   0.4211   0.00673   0.00177   0.0017   0.1897   1.0000
   4.000   0.4486   0.00702   0.00192   0.0017   0.1600   1.0000
   4.250   0.4761   0.00732   0.00210   0.0018   0.1330   1.0000
   4.500   0.5037   0.00759   0.00228   0.0018   0.1118   1.0000
   4.750   0.5312   0.00790   0.00249   0.0019   0.0915   1.0000
   5.000   0.5587   0.00818   0.00270   0.0019   0.0758   1.0000
   5.250   0.5863   0.00847   0.00293   0.0020   0.0632   1.0000
   5.500   0.6138   0.00878   0.00319   0.0021   0.0530   1.0000
   5.750   0.6411   0.00913   0.00348   0.0022   0.0440   1.0000
   6.000   0.6686   0.00938   0.00373   0.0023   0.0395   1.0000
   6.250   0.6958   0.00974   0.00408   0.0024   0.0342   1.0000
   6.500   0.7232   0.01002   0.00435   0.0025   0.0310   1.0000
   6.750   0.7500   0.01048   0.00481   0.0027   0.0273   1.0000
   7.000   0.7772   0.01075   0.00511   0.0028   0.0257   1.0000
   7.250   0.8040   0.01110   0.00546   0.0030   0.0237   1.0000
   7.500   0.8300   0.01171   0.00611   0.0032   0.0214   1.0000
   7.750   0.8571   0.01198   0.00642   0.0033   0.0204   1.0000
   8.000   0.8839   0.01233   0.00678   0.0035   0.0190   1.0000
   8.250   0.9102   0.01279   0.00726   0.0036   0.0178   1.0000
   8.500   0.9348   0.01361   0.00815   0.0039   0.0165   1.0000
   8.750   0.9611   0.01399   0.00859   0.0041   0.0159   1.0000
   9.000   0.9869   0.01446   0.00910   0.0044   0.0151   1.0000
   9.250   1.0124   0.01496   0.00964   0.0046   0.0144   1.0000
   9.500   1.0374   0.01554   0.01026   0.0049   0.0138   1.0000
   9.750   1.0591   0.01673   0.01155   0.0054   0.0129   1.0000
  10.000   1.0821   0.01760   0.01252   0.0058   0.0126   1.0000
  10.250   1.1064   0.01815   0.01314   0.0061   0.0122   1.0000
  10.500   1.1301   0.01879   0.01385   0.0065   0.0118   1.0000
  10.750   1.1532   0.01948   0.01463   0.0069   0.0114   1.0000
  11.000   1.1756   0.02022   0.01544   0.0073   0.0110   1.0000
  11.250   1.1973   0.02103   0.01632   0.0078   0.0107   1.0000
  11.500   1.2181   0.02188   0.01723   0.0083   0.0104   1.0000
  11.750   1.2361   0.02308   0.01852   0.0090   0.0101   1.0000
  12.000   1.2478   0.02500   0.02061   0.0101   0.0098   1.0000
  12.250   1.2532   0.02751   0.02334   0.0115   0.0095   1.0000
  12.500   1.2680   0.02863   0.02459   0.0123   0.0094   1.0000
  12.750   1.2796   0.02993   0.02601   0.0133   0.0093   1.0000
  13.000   1.2825   0.03158   0.02780   0.0151   0.0092   1.0000
  13.250   1.2776   0.03348   0.02983   0.0170   0.0092   1.0000
  13.500   1.2732   0.03585   0.03233   0.0175   0.0091   1.0000
  13.750   1.2645   0.03931   0.03594   0.0165   0.0090   1.0000
  14.000   1.2550   0.04357   0.04035   0.0143   0.0090   1.0000
  14.250   1.2443   0.04862   0.04555   0.0110   0.0089   1.0000
  14.500   1.2299   0.05476   0.05184   0.0068   0.0089   1.0000
  14.750   1.2084   0.06247   0.05973   0.0016   0.0090   1.0000
  15.000   1.1873   0.07054   0.06795  -0.0039   0.0090   1.0000
  15.250   1.1603   0.08002   0.07757  -0.0101   0.0090   1.0000
  15.500   1.1264   0.09122   0.08894  -0.0174   0.0091   1.0000
  15.750   1.0893   0.10365   0.10151  -0.0252   0.0092   1.0000
  16.000   1.0509   0.11744   0.11545  -0.0337   0.0093   1.0000
  16.250   0.9513   0.14891   0.14721  -0.0523   0.0097   1.0000
<< Back to Joukovsky f=0% t=9% (joukowsk0009-jf)

Polar data table (+)

Polar graphs


<< Back to Joukovsky f=0% t=9% (joukowsk0009-jf)