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

E197 (13.49%) (e197-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E197 (13.49%) (e197-il)
Reynolds number: 500,000
Max Cl/Cd: 110.66 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e197-il-500000.txt
Download as CSV file: xf-e197-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E197  (13.49%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6448   0.04642   0.04349  -0.0760   1.0000   0.0168
 -10.750  -0.6643   0.04342   0.04036  -0.0753   1.0000   0.0167
 -10.500  -0.6910   0.04121   0.03802  -0.0708   1.0000   0.0167
 -10.250  -0.7110   0.03858   0.03524  -0.0665   1.0000   0.0166
 -10.000  -0.7118   0.03525   0.03161  -0.0659   0.9963   0.0166
  -9.750  -0.6909   0.03191   0.02785  -0.0685   0.9878   0.0169
  -9.500  -0.6677   0.02892   0.02440  -0.0708   0.9797   0.0174
  -9.250  -0.6444   0.02496   0.02008  -0.0726   0.9707   0.0178
  -9.000  -0.6174   0.02284   0.01778  -0.0738   0.9574   0.0181
  -8.750  -0.5894   0.02128   0.01606  -0.0748   0.9402   0.0186
  -8.500  -0.5635   0.01997   0.01458  -0.0749   0.9180   0.0190
  -8.250  -0.5409   0.01896   0.01339  -0.0743   0.8938   0.0195
  -8.000  -0.5199   0.01808   0.01230  -0.0732   0.8703   0.0200
  -7.750  -0.4985   0.01735   0.01139  -0.0721   0.8499   0.0206
  -7.500  -0.4763   0.01675   0.01063  -0.0712   0.8319   0.0214
  -7.250  -0.4538   0.01612   0.00984  -0.0703   0.8162   0.0219
  -7.000  -0.4309   0.01554   0.00911  -0.0694   0.8023   0.0222
  -6.750  -0.4115   0.01442   0.00784  -0.0681   0.7897   0.0230
  -6.500  -0.3897   0.01371   0.00702  -0.0672   0.7782   0.0239
  -6.250  -0.3660   0.01321   0.00644  -0.0666   0.7678   0.0250
  -6.000  -0.3416   0.01282   0.00596  -0.0661   0.7586   0.0264
  -5.750  -0.3165   0.01248   0.00552  -0.0656   0.7495   0.0279
  -5.500  -0.2919   0.01201   0.00495  -0.0650   0.7415   0.0299
  -5.250  -0.2668   0.01162   0.00451  -0.0646   0.7339   0.0334
  -5.000  -0.2414   0.01122   0.00409  -0.0642   0.7268   0.0423
  -4.750  -0.2174   0.01064   0.00367  -0.0636   0.7198   0.0841
  -4.500  -0.1922   0.01026   0.00341  -0.0634   0.7138   0.1241
  -4.250  -0.1666   0.00989   0.00319  -0.0631   0.7074   0.1656
  -4.000  -0.1410   0.00958   0.00298  -0.0629   0.7018   0.2098
  -3.750  -0.1153   0.00922   0.00280  -0.0627   0.6960   0.2629
  -3.500  -0.0896   0.00889   0.00265  -0.0625   0.6906   0.3206
  -3.250  -0.0638   0.00866   0.00257  -0.0622   0.6857   0.3816
  -3.000  -0.0371   0.00848   0.00252  -0.0621   0.6803   0.4295
  -2.750  -0.0099   0.00840   0.00247  -0.0620   0.6753   0.4607
  -2.500   0.0176   0.00838   0.00242  -0.0619   0.6709   0.4840
  -2.250   0.0451   0.00830   0.00239  -0.0618   0.6659   0.5058
  -2.000   0.0727   0.00826   0.00236  -0.0617   0.6612   0.5279
  -1.750   0.1004   0.00824   0.00232  -0.0617   0.6570   0.5448
  -1.500   0.1281   0.00821   0.00230  -0.0616   0.6526   0.5612
  -1.250   0.1557   0.00816   0.00228  -0.0616   0.6479   0.5780
  -1.000   0.1834   0.00813   0.00226  -0.0615   0.6437   0.5956
  -0.750   0.2110   0.00813   0.00226  -0.0614   0.6398   0.6144
  -0.500   0.2385   0.00807   0.00227  -0.0614   0.6352   0.6344
  -0.250   0.2658   0.00802   0.00227  -0.0612   0.6309   0.6552
   0.000   0.2932   0.00801   0.00228  -0.0611   0.6271   0.6785
   0.250   0.3202   0.00796   0.00233  -0.0609   0.6229   0.7043
   0.500   0.3469   0.00789   0.00236  -0.0606   0.6185   0.7342
   0.750   0.3732   0.00782   0.00240  -0.0602   0.6144   0.7682
   1.000   0.3993   0.00781   0.00246  -0.0597   0.6106   0.8057
   1.250   0.4246   0.00771   0.00253  -0.0590   0.6063   0.8473
   1.500   0.4507   0.00766   0.00261  -0.0583   0.6020   0.8904
   1.750   0.4820   0.00770   0.00269  -0.0588   0.5979   0.9285
   2.000   0.5182   0.00779   0.00277  -0.0605   0.5937   0.9547
   2.250   0.5564   0.00784   0.00285  -0.0627   0.5889   0.9715
   2.500   0.5960   0.00791   0.00289  -0.0652   0.5842   0.9824
   2.750   0.6389   0.00800   0.00294  -0.0686   0.5795   0.9890
   3.000   0.6803   0.00802   0.00300  -0.0716   0.5736   0.9960
   3.250   0.7171   0.00807   0.00301  -0.0736   0.5678   1.0000
   3.500   0.7400   0.00813   0.00308  -0.0728   0.5618   1.0000
   3.750   0.7634   0.00817   0.00314  -0.0719   0.5556   1.0000
   4.000   0.7871   0.00827   0.00320  -0.0711   0.5498   1.0000
   4.250   0.8107   0.00831   0.00329  -0.0704   0.5428   1.0000
   4.500   0.8346   0.00842   0.00336  -0.0696   0.5363   1.0000
   4.750   0.8586   0.00846   0.00347  -0.0689   0.5287   1.0000
   5.000   0.8824   0.00858   0.00355  -0.0681   0.5216   1.0000
   5.250   0.9064   0.00863   0.00366  -0.0674   0.5126   1.0000
   5.500   0.9302   0.00874   0.00378  -0.0666   0.5038   1.0000
   5.750   0.9540   0.00885   0.00390  -0.0658   0.4941   1.0000
   6.000   0.9780   0.00896   0.00404  -0.0651   0.4832   1.0000
   6.250   1.0016   0.00910   0.00420  -0.0644   0.4708   1.0000
   6.500   1.0247   0.00926   0.00436  -0.0635   0.4559   1.0000
   6.750   1.0474   0.00947   0.00454  -0.0626   0.4388   1.0000
   7.000   1.0691   0.00973   0.00477  -0.0616   0.4194   1.0000
   7.250   1.0892   0.01009   0.00504  -0.0603   0.3904   1.0000
   7.500   1.1059   0.01064   0.00542  -0.0585   0.3476   1.0000
   7.750   1.1185   0.01144   0.00595  -0.0562   0.2937   1.0000
   8.000   1.1285   0.01240   0.00661  -0.0535   0.2413   1.0000
   8.250   1.1384   0.01333   0.00730  -0.0508   0.1968   1.0000
   8.500   1.1485   0.01420   0.00797  -0.0482   0.1621   1.0000
   8.750   1.1583   0.01500   0.00863  -0.0455   0.1345   1.0000
   9.000   1.1664   0.01570   0.00925  -0.0425   0.1140   1.0000
   9.250   1.1726   0.01650   0.00995  -0.0392   0.0954   1.0000
   9.500   1.1795   0.01733   0.01071  -0.0363   0.0794   1.0000
   9.750   1.1864   0.01822   0.01155  -0.0336   0.0653   1.0000
  10.000   1.1931   0.01919   0.01248  -0.0311   0.0533   1.0000
  10.250   1.1974   0.02037   0.01359  -0.0286   0.0407   1.0000
  10.500   1.1965   0.02198   0.01511  -0.0258   0.0259   1.0000
  10.750   1.1977   0.02361   0.01672  -0.0235   0.0190   1.0000
  11.000   1.2018   0.02516   0.01832  -0.0217   0.0163   1.0000
  11.250   1.2073   0.02669   0.01990  -0.0202   0.0145   1.0000
  11.500   1.2095   0.02857   0.02183  -0.0187   0.0135   1.0000
  11.750   1.2139   0.03034   0.02369  -0.0175   0.0128   1.0000
  12.000   1.2189   0.03212   0.02555  -0.0164   0.0120   1.0000
  12.250   1.2235   0.03398   0.02750  -0.0154   0.0118   1.0000
  12.500   1.2274   0.03595   0.02955  -0.0146   0.0114   1.0000
  12.750   1.2297   0.03812   0.03180  -0.0138   0.0110   1.0000
  13.000   1.2285   0.04067   0.03442  -0.0130   0.0105   1.0000
  13.250   1.2285   0.04317   0.03700  -0.0124   0.0104   1.0000
  13.500   1.2184   0.04674   0.04067  -0.0117   0.0100   1.0000
  13.750   1.2201   0.04924   0.04324  -0.0113   0.0099   1.0000
  14.000   1.2240   0.05158   0.04569  -0.0111   0.0097   1.0000
  14.250   1.2262   0.05416   0.04836  -0.0109   0.0094   1.0000
  14.500   1.2279   0.05683   0.05112  -0.0109   0.0094   1.0000
  14.750   1.2325   0.05928   0.05365  -0.0111   0.0091   1.0000
  15.000   1.2325   0.06229   0.05676  -0.0112   0.0089   1.0000
  15.250   1.2334   0.06526   0.05982  -0.0114   0.0087   1.0000
  15.500   1.2349   0.06822   0.06288  -0.0118   0.0086   1.0000
  15.750   1.2353   0.07141   0.06617  -0.0122   0.0085   1.0000
  16.000   1.2351   0.07470   0.06956  -0.0127   0.0083   1.0000
  16.250   1.2352   0.07806   0.07300  -0.0135   0.0081   1.0000
  16.500   1.2348   0.08151   0.07656  -0.0142   0.0081   1.0000
  16.750   1.2346   0.08506   0.08021  -0.0152   0.0081   1.0000
  17.000   1.2323   0.08890   0.08413  -0.0162   0.0079   1.0000
  17.250   1.2308   0.09274   0.08809  -0.0173   0.0079   1.0000
  17.500   1.2284   0.09682   0.09229  -0.0187   0.0078   1.0000
  17.750   1.2252   0.10108   0.09665  -0.0202   0.0078   1.0000
  18.000   1.2207   0.10557   0.10127  -0.0218   0.0077   1.0000
  18.250   1.2157   0.11036   0.10619  -0.0238   0.0077   1.0000
  18.500   1.2090   0.11549   0.11146  -0.0261   0.0076   1.0000
  18.750   1.2004   0.12109   0.11720  -0.0287   0.0076   1.0000
  19.000   1.1923   0.12683   0.12310  -0.0317   0.0076   1.0000
  19.250   1.1848   0.13269   0.12911  -0.0350   0.0077   1.0000
<< Back to E197 (13.49%) (e197-il)

Polar data table (+)

Polar graphs


<< Back to E197 (13.49%) (e197-il)