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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.49 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe182-il-1000000.txt
Download as CSV file: xf-goe182-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 182 (MVA H.27) AIRFOIL                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3383   0.09428   0.09273  -0.0189   1.0000   0.0198
  -8.500  -0.3341   0.09040   0.08886  -0.0209   1.0000   0.0198
  -8.250  -0.3352   0.08588   0.08436  -0.0226   1.0000   0.0201
  -8.000  -0.3255   0.08410   0.08260  -0.0227   1.0000   0.0203
  -7.750  -0.3121   0.08200   0.08051  -0.0242   0.9955   0.0206
  -7.500  -0.2890   0.07895   0.07746  -0.0290   0.9794   0.0212
  -7.250  -0.2709   0.07563   0.07411  -0.0334   0.9595   0.0222
  -7.000  -0.2495   0.01926   0.01619  -0.1006   0.9567   0.0248
  -6.750  -0.2254   0.01878   0.01563  -0.0998   0.9367   0.0252
  -6.500  -0.2019   0.01826   0.01498  -0.0989   0.9055   0.0256
  -6.250  -0.1792   0.01778   0.01422  -0.0978   0.8458   0.0261
  -6.000  -0.1549   0.01710   0.01316  -0.0973   0.7887   0.0268
  -5.750  -0.1291   0.01581   0.01149  -0.0973   0.7590   0.0276
  -5.500  -0.1023   0.01480   0.01017  -0.0972   0.7394   0.0282
  -5.250  -0.0749   0.01418   0.00933  -0.0971   0.7242   0.0286
  -5.000  -0.0473   0.01355   0.00847  -0.0970   0.7108   0.0290
  -4.750  -0.0207   0.01197   0.00663  -0.0971   0.6987   0.0299
  -4.500   0.0070   0.01151   0.00605  -0.0970   0.6860   0.0304
  -4.250   0.0350   0.01114   0.00558  -0.0969   0.6727   0.0309
  -4.000   0.0630   0.01079   0.00513  -0.0967   0.6584   0.0315
  -3.750   0.0910   0.01047   0.00470  -0.0965   0.6418   0.0321
  -3.500   0.1190   0.01018   0.00429  -0.0964   0.6225   0.0328
  -3.250   0.1469   0.01001   0.00399  -0.0962   0.5994   0.0336
  -3.000   0.1748   0.00984   0.00368  -0.0960   0.5761   0.0341
  -2.750   0.2027   0.00968   0.00340  -0.0958   0.5552   0.0345
  -2.500   0.2306   0.00937   0.00296  -0.0956   0.5364   0.0350
  -2.250   0.2585   0.00904   0.00253  -0.0955   0.5195   0.0362
  -2.000   0.2866   0.00892   0.00234  -0.0953   0.5038   0.0373
  -1.750   0.3148   0.00886   0.00220  -0.0952   0.4884   0.0385
  -1.500   0.3429   0.00881   0.00208  -0.0951   0.4725   0.0399
  -1.250   0.3710   0.00881   0.00200  -0.0949   0.4555   0.0412
  -1.000   0.3991   0.00872   0.00181  -0.0948   0.4370   0.0432
  -0.750   0.4271   0.00871   0.00173  -0.0946   0.4169   0.0462
  -0.500   0.4550   0.00877   0.00170  -0.0945   0.3950   0.0494
  -0.250   0.4828   0.00880   0.00165  -0.0943   0.3734   0.0564
   0.000   0.5106   0.00886   0.00164  -0.0941   0.3546   0.0647
   0.250   0.5384   0.00895   0.00166  -0.0940   0.3386   0.0718
   0.750   0.5941   0.00897   0.00167  -0.0938   0.3136   0.1060
   1.000   0.6219   0.00898   0.00175  -0.0937   0.3038   0.1557
   1.250   0.6496   0.00905   0.00181  -0.0936   0.2942   0.1777
   1.500   0.6776   0.00905   0.00188  -0.0935   0.2872   0.2107
   1.750   0.7051   0.00906   0.00199  -0.0934   0.2791   0.2777
   2.000   0.7327   0.00889   0.00213  -0.0934   0.2736   0.4094
   2.250   0.7599   0.00881   0.00226  -0.0933   0.2676   0.5236
   2.500   0.7868   0.00796   0.00240  -0.0931   0.2622   1.0000
   2.750   0.8147   0.00807   0.00247  -0.0929   0.2589   1.0000
   3.000   0.8424   0.00821   0.00256  -0.0928   0.2552   1.0000
   3.250   0.8698   0.00837   0.00267  -0.0926   0.2511   1.0000
   3.500   0.8973   0.00854   0.00280  -0.0924   0.2476   1.0000
   3.750   0.9250   0.00865   0.00291  -0.0923   0.2460   1.0000
   4.000   0.9526   0.00878   0.00302  -0.0921   0.2442   1.0000
   4.250   0.9801   0.00891   0.00315  -0.0920   0.2423   1.0000
   4.500   1.0075   0.00906   0.00328  -0.0918   0.2405   1.0000
   4.750   1.0348   0.00922   0.00343  -0.0916   0.2386   1.0000
   5.000   1.0618   0.00941   0.00360  -0.0914   0.2363   1.0000
   5.250   1.0884   0.00964   0.00381  -0.0912   0.2331   1.0000
   5.500   1.1158   0.00976   0.00394  -0.0910   0.2321   1.0000
   5.750   1.1431   0.00988   0.00408  -0.0909   0.2307   1.0000
   6.000   1.1703   0.01002   0.00424  -0.0907   0.2293   1.0000
   6.250   1.1973   0.01016   0.00439  -0.0905   0.2272   1.0000
   6.500   1.2242   0.01032   0.00455  -0.0904   0.2245   1.0000
   6.750   1.2505   0.01055   0.00476  -0.0901   0.2206   1.0000
   7.000   1.2771   0.01072   0.00494  -0.0899   0.2176   1.0000
   7.250   1.3043   0.01081   0.00507  -0.0898   0.2148   1.0000
   7.500   1.3310   0.01096   0.00524  -0.0896   0.2113   1.0000
   7.750   1.3571   0.01118   0.00545  -0.0893   0.2070   1.0000
   8.000   1.3833   0.01137   0.00566  -0.0891   0.2030   1.0000
   8.250   1.4099   0.01151   0.00581  -0.0889   0.1971   1.0000
   8.500   1.4355   0.01177   0.00605  -0.0886   0.1884   1.0000
   8.750   1.4595   0.01219   0.00633  -0.0882   0.1629   1.0000
   9.000   1.4725   0.01393   0.00765  -0.0864   0.0963   1.0000
   9.250   1.4874   0.01540   0.00881  -0.0848   0.0512   1.0000
   9.500   1.5084   0.01609   0.00950  -0.0839   0.0415   1.0000
   9.750   1.5295   0.01674   0.01012  -0.0831   0.0339   1.0000
  10.000   1.5497   0.01743   0.01078  -0.0821   0.0267   1.0000
  10.250   1.5698   0.01811   0.01145  -0.0812   0.0221   1.0000
  10.500   1.5895   0.01877   0.01215  -0.0801   0.0194   1.0000
  10.750   1.6083   0.01947   0.01286  -0.0790   0.0175   1.0000
  11.000   1.6257   0.02026   0.01370  -0.0777   0.0160   1.0000
  11.250   1.6439   0.02091   0.01440  -0.0765   0.0151   1.0000
  11.500   1.6600   0.02167   0.01522  -0.0751   0.0143   1.0000
  11.750   1.6724   0.02266   0.01626  -0.0732   0.0134   1.0000
  12.000   1.6790   0.02377   0.01746  -0.0704   0.0128   1.0000
  12.250   1.6889   0.02465   0.01841  -0.0682   0.0125   1.0000
  12.500   1.6965   0.02572   0.01956  -0.0660   0.0121   1.0000
  12.750   1.7026   0.02699   0.02091  -0.0639   0.0118   1.0000
  13.000   1.7070   0.02848   0.02249  -0.0620   0.0114   1.0000
  13.250   1.7097   0.03029   0.02439  -0.0605   0.0111   1.0000
  13.500   1.7094   0.03261   0.02680  -0.0593   0.0108   1.0000
  13.750   1.7041   0.03580   0.03011  -0.0588   0.0105   1.0000
  14.000   1.6928   0.04015   0.03460  -0.0592   0.0103   1.0000
  14.250   1.6775   0.04533   0.03994  -0.0601   0.0101   1.0000
  14.500   1.6721   0.04934   0.04407  -0.0609   0.0100   1.0000
  14.750   1.6626   0.05405   0.04891  -0.0620   0.0099   1.0000
  15.000   1.6491   0.05945   0.05444  -0.0634   0.0098   1.0000
  15.250   1.6313   0.06551   0.06063  -0.0650   0.0098   1.0000
  15.500   1.6118   0.07187   0.06713  -0.0667   0.0097   1.0000
  15.750   1.5909   0.07848   0.07386  -0.0685   0.0097   1.0000
  16.000   1.5700   0.08528   0.08079  -0.0704   0.0097   1.0000
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