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D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 200,000
Max Cl/Cd: 57.38 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dga1138-il-200000-n5.txt
Download as CSV file: xf-dga1138-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: D.G.A. 1138                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5136   0.08860   0.08512  -0.0193   1.0000   0.0136
  -9.250  -0.5217   0.08311   0.07970  -0.0223   1.0000   0.0139
  -9.000  -0.5266   0.07847   0.07513  -0.0254   1.0000   0.0143
  -8.750  -0.5155   0.07758   0.07423  -0.0259   1.0000   0.0154
  -8.500  -0.5118   0.07354   0.07021  -0.0288   1.0000   0.0160
  -8.250  -0.5093   0.06827   0.06492  -0.0325   1.0000   0.0165
  -8.000  -0.5060   0.06214   0.05875  -0.0363   1.0000   0.0172
  -7.750  -0.5015   0.05464   0.05111  -0.0401   1.0000   0.0180
  -7.500  -0.5030   0.03925   0.03511  -0.0451   1.0000   0.0193
  -7.250  -0.4931   0.03393   0.02926  -0.0451   1.0000   0.0215
  -7.000  -0.4731   0.03498   0.03045  -0.0439   1.0000   0.0234
  -6.750  -0.4592   0.03178   0.02685  -0.0428   1.0000   0.0250
  -6.500  -0.4442   0.02864   0.02321  -0.0414   0.9999   0.0264
  -6.250  -0.4130   0.02597   0.01994  -0.0429   0.9968   0.0281
  -6.000  -0.3790   0.02536   0.01890  -0.0442   0.9936   0.0298
  -5.750  -0.3495   0.02241   0.01546  -0.0453   0.9899   0.0304
  -5.500  -0.3185   0.02017   0.01286  -0.0464   0.9869   0.0312
  -5.250  -0.2878   0.01875   0.01124  -0.0473   0.9834   0.0323
  -5.000  -0.2567   0.01772   0.00998  -0.0481   0.9795   0.0338
  -4.750  -0.2237   0.01683   0.00894  -0.0493   0.9764   0.0357
  -4.500  -0.1926   0.01606   0.00804  -0.0499   0.9713   0.0378
  -4.250  -0.1597   0.01538   0.00725  -0.0510   0.9670   0.0398
  -4.000  -0.1266   0.01493   0.00669  -0.0521   0.9630   0.0422
  -3.750  -0.0966   0.01426   0.00600  -0.0527   0.9575   0.0450
  -3.500  -0.0647   0.01359   0.00535  -0.0537   0.9536   0.0477
  -3.250  -0.0337   0.01313   0.00482  -0.0544   0.9482   0.0501
  -3.000  -0.0018   0.01275   0.00439  -0.0552   0.9425   0.0525
  -2.750   0.0320   0.01242   0.00401  -0.0564   0.9375   0.0556
  -2.500   0.0633   0.01198   0.00355  -0.0571   0.9293   0.0611
  -2.250   0.0964   0.01168   0.00320  -0.0581   0.9212   0.0655
  -2.000   0.1285   0.01132   0.00293  -0.0589   0.9124   0.0776
  -1.750   0.1580   0.01104   0.00285  -0.0593   0.9034   0.1397
  -1.500   0.1883   0.01089   0.00277  -0.0597   0.8962   0.1691
  -1.250   0.2165   0.01074   0.00272  -0.0598   0.8860   0.2021
  -1.000   0.2443   0.01061   0.00267  -0.0596   0.8739   0.2291
  -0.500   0.2982   0.01033   0.00257  -0.0591   0.8485   0.2961
  -0.250   0.3206   0.00946   0.00255  -0.0582   0.8352   0.5535
   0.000   0.3815   0.00859   0.00267  -0.0648   0.8230   1.0000
   0.250   0.4072   0.00863   0.00263  -0.0642   0.8058   1.0000
   0.500   0.4330   0.00867   0.00260  -0.0636   0.7874   1.0000
   0.750   0.4583   0.00874   0.00257  -0.0628   0.7632   1.0000
   1.000   0.4829   0.00886   0.00253  -0.0618   0.7277   1.0000
   1.250   0.5069   0.00904   0.00250  -0.0607   0.6792   1.0000
   1.500   0.5286   0.00940   0.00247  -0.0592   0.5891   1.0000
   1.750   0.5497   0.00992   0.00261  -0.0578   0.5324   1.0000
   2.000   0.5737   0.01026   0.00280  -0.0570   0.5049   1.0000
   2.250   0.5985   0.01053   0.00299  -0.0564   0.4843   1.0000
   2.500   0.6226   0.01085   0.00319  -0.0558   0.4389   1.0000
   2.750   0.6420   0.01165   0.00338  -0.0545   0.3100   1.0000
   3.000   0.6623   0.01254   0.00378  -0.0534   0.2141   1.0000
   3.250   0.6860   0.01301   0.00416  -0.0529   0.1873   1.0000
   3.500   0.7103   0.01338   0.00449  -0.0524   0.1729   1.0000
   3.750   0.7351   0.01370   0.00482  -0.0519   0.1621   1.0000
   4.000   0.7593   0.01409   0.00517  -0.0514   0.1441   1.0000
   4.250   0.7841   0.01440   0.00550  -0.0510   0.1272   1.0000
   4.500   0.8082   0.01481   0.00582  -0.0505   0.0971   1.0000
   4.750   0.8312   0.01538   0.00628  -0.0498   0.0776   1.0000
   5.000   0.8519   0.01632   0.00697  -0.0488   0.0317   1.0000
   5.250   0.8742   0.01704   0.00771  -0.0479   0.0247   1.0000
   5.500   0.8962   0.01787   0.00875  -0.0468   0.0207   1.0000
   5.750   0.9180   0.01866   0.00968  -0.0459   0.0171   1.0000
   6.000   0.9384   0.01967   0.01084  -0.0448   0.0148   1.0000
   6.250   0.9543   0.02132   0.01265  -0.0429   0.0131   1.0000
   6.500   0.9746   0.02227   0.01374  -0.0417   0.0125   1.0000
   6.750   0.9938   0.02346   0.01506  -0.0403   0.0119   1.0000
   7.000   1.0130   0.02467   0.01642  -0.0390   0.0109   1.0000
   7.250   1.0324   0.02582   0.01771  -0.0378   0.0095   1.0000
   7.500   1.0509   0.02715   0.01920  -0.0365   0.0084   1.0000
   7.750   1.0681   0.02882   0.02104  -0.0350   0.0079   1.0000
   8.000   1.0845   0.03062   0.02310  -0.0335   0.0075   1.0000
   8.250   1.0996   0.03258   0.02527  -0.0319   0.0072   1.0000
   8.500   1.1127   0.03470   0.02764  -0.0301   0.0070   1.0000
   8.750   1.1233   0.03704   0.03025  -0.0280   0.0068   1.0000
   9.000   1.1308   0.03957   0.03307  -0.0258   0.0067   1.0000
   9.250   1.1343   0.04232   0.03612  -0.0231   0.0065   1.0000
   9.500   1.1338   0.04515   0.03926  -0.0202   0.0065   1.0000
   9.750   1.1274   0.04790   0.04229  -0.0167   0.0064   1.0000
  10.000   1.1173   0.05076   0.04540  -0.0132   0.0064   1.0000
  10.250   1.1052   0.05396   0.04886  -0.0106   0.0064   1.0000
  10.500   1.0913   0.05761   0.05276  -0.0090   0.0064   1.0000
  10.750   1.0763   0.06179   0.05717  -0.0086   0.0065   1.0000
  11.000   1.0597   0.06675   0.06236  -0.0096   0.0065   1.0000
  11.250   1.0421   0.07262   0.06845  -0.0121   0.0065   1.0000
  11.500   1.0237   0.07984   0.07588  -0.0165   0.0066   1.0000
  11.750   1.0036   0.08875   0.08500  -0.0227   0.0067   1.0000
  12.000   0.9802   0.10010   0.09654  -0.0305   0.0068   1.0000
  12.250   0.9451   0.11731   0.11391  -0.0405   0.0072   1.0000
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