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NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M9 AIRFOIL (m9-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.65 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m9-il-1000000-n5.txt
Download as CSV file: xf-m9-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M9 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4286   0.08130   0.07850  -0.0156   0.6443   0.0089
  -9.750  -0.4561   0.07483   0.07201  -0.0190   0.6403   0.0090
  -9.500  -0.4625   0.06895   0.06607  -0.0242   0.6347   0.0091
  -9.250  -0.4645   0.06231   0.05936  -0.0309   0.6309   0.0092
  -9.000  -0.4633   0.05380   0.05072  -0.0399   0.6255   0.0095
  -8.750  -0.4644   0.03631   0.03272  -0.0581   0.6226   0.0096
  -8.500  -0.4534   0.02485   0.02061  -0.0660   0.6172   0.0098
  -8.250  -0.4301   0.02164   0.01712  -0.0675   0.6090   0.0101
  -8.000  -0.4051   0.01967   0.01493  -0.0681   0.5992   0.0105
  -7.750  -0.3794   0.01813   0.01318  -0.0684   0.5878   0.0109
  -7.500  -0.3531   0.01697   0.01184  -0.0685   0.5755   0.0112
  -7.250  -0.3266   0.01599   0.01067  -0.0684   0.5628   0.0116
  -7.000  -0.2999   0.01501   0.00953  -0.0683   0.5503   0.0122
  -6.750  -0.2730   0.01418   0.00857  -0.0681   0.5397   0.0130
  -6.500  -0.2458   0.01355   0.00782  -0.0679   0.5295   0.0139
  -6.250  -0.2183   0.01305   0.00720  -0.0676   0.5195   0.0147
  -6.000  -0.1908   0.01252   0.00657  -0.0673   0.5103   0.0159
  -5.750  -0.1631   0.01210   0.00607  -0.0670   0.5004   0.0173
  -5.500  -0.1352   0.01177   0.00565  -0.0667   0.4921   0.0186
  -5.250  -0.1074   0.01145   0.00527  -0.0664   0.4835   0.0205
  -5.000  -0.0793   0.01121   0.00496  -0.0660   0.4768   0.0222
  -4.750  -0.0512   0.01097   0.00467  -0.0657   0.4700   0.0241
  -4.250   0.0053   0.01064   0.00422  -0.0650   0.4580   0.0273
  -4.000   0.0335   0.01043   0.00397  -0.0647   0.4522   0.0291
  -3.750   0.0617   0.01030   0.00379  -0.0644   0.4458   0.0309
  -3.500   0.0900   0.01017   0.00362  -0.0641   0.4394   0.0324
  -3.250   0.1183   0.01005   0.00343  -0.0638   0.4324   0.0338
  -3.000   0.1466   0.00992   0.00327  -0.0635   0.4260   0.0358
  -2.750   0.1749   0.00982   0.00313  -0.0632   0.4190   0.0378
  -2.500   0.2032   0.00976   0.00301  -0.0629   0.4130   0.0393
  -2.250   0.2316   0.00963   0.00285  -0.0626   0.4094   0.0415
  -2.000   0.2599   0.00952   0.00273  -0.0623   0.4051   0.0438
  -1.750   0.2883   0.00945   0.00263  -0.0620   0.3998   0.0462
  -1.500   0.3166   0.00942   0.00254  -0.0617   0.3949   0.0477
  -1.250   0.3450   0.00931   0.00243  -0.0615   0.3918   0.0510
  -1.000   0.3733   0.00924   0.00235  -0.0612   0.3883   0.0544
  -0.750   0.4016   0.00920   0.00229  -0.0609   0.3839   0.0573
  -0.250   0.4580   0.00911   0.00218  -0.0604   0.3739   0.0678
   0.000   0.4862   0.00907   0.00214  -0.0601   0.3684   0.0741
   0.250   0.5143   0.00906   0.00212  -0.0599   0.3636   0.0803
   0.500   0.5424   0.00903   0.00210  -0.0596   0.3600   0.0863
   0.750   0.5705   0.00901   0.00208  -0.0594   0.3562   0.0927
   1.000   0.5986   0.00903   0.00208  -0.0591   0.3509   0.0962
   1.250   0.6264   0.00903   0.00207  -0.0588   0.3451   0.1031
   1.500   0.6544   0.00903   0.00206  -0.0586   0.3407   0.1079
   1.750   0.6822   0.00905   0.00207  -0.0583   0.3338   0.1137
   2.000   0.7097   0.00907   0.00207  -0.0581   0.3270   0.1231
   2.250   0.7367   0.00900   0.00212  -0.0577   0.3195   0.1721
   2.500   0.7656   0.00935   0.00249  -0.0577   0.3113   0.2096
   2.750   0.7936   0.00950   0.00259  -0.0575   0.3021   0.2160
   3.000   0.8212   0.00969   0.00272  -0.0573   0.2907   0.2188
   3.250   0.8487   0.01000   0.00296  -0.0571   0.2736   0.2205
   3.500   0.8752   0.01037   0.00320  -0.0568   0.2494   0.2221
   3.750   0.9017   0.01067   0.00340  -0.0565   0.2321   0.2233
   4.000   0.9284   0.01090   0.00357  -0.0563   0.2218   0.2243
   4.250   0.9554   0.01107   0.00372  -0.0560   0.2154   0.2254
   4.500   0.9821   0.01128   0.00388  -0.0557   0.2085   0.2266
   4.750   1.0087   0.01149   0.00406  -0.0555   0.2021   0.2275
   5.000   1.0356   0.01163   0.00419  -0.0553   0.1981   0.2278
   5.250   1.0621   0.01177   0.00433  -0.0550   0.1938   0.2284
   5.500   1.0884   0.01199   0.00454  -0.0547   0.1886   0.2291
   5.750   1.1150   0.01213   0.00470  -0.0545   0.1858   0.2295
   6.000   1.1416   0.01225   0.00484  -0.0542   0.1839   0.2298
   6.250   1.1681   0.01240   0.00501  -0.0540   0.1815   0.2303
   6.500   1.1944   0.01259   0.00522  -0.0537   0.1790   0.2314
   6.750   1.2203   0.01277   0.00541  -0.0535   0.1763   0.2319
   7.000   1.2460   0.01296   0.00561  -0.0532   0.1735   0.2321
   7.250   1.2717   0.01313   0.00581  -0.0528   0.1710   0.2322
   7.500   1.2975   0.01327   0.00598  -0.0526   0.1698   0.2324
   7.750   1.3231   0.01343   0.00618  -0.0523   0.1681   0.2325
   8.000   1.3485   0.01360   0.00638  -0.0519   0.1661   0.2327
   8.250   1.3735   0.01380   0.00660  -0.0516   0.1638   0.2330
   8.500   1.3981   0.01403   0.00685  -0.0512   0.1610   0.2332
   8.750   1.4223   0.01429   0.00713  -0.0508   0.1577   0.2334
   9.000   1.4465   0.01453   0.00739  -0.0504   0.1531   0.2337
   9.250   1.4695   0.01486   0.00770  -0.0499   0.1461   0.2339
   9.500   1.4923   0.01519   0.00803  -0.0493   0.1407   0.2342
   9.750   1.5139   0.01561   0.00842  -0.0486   0.1320   0.2345
  10.000   1.5343   0.01609   0.00887  -0.0479   0.1222   0.2350
  10.250   1.5349   0.01798   0.01042  -0.0450   0.0754   0.2352
  10.500   1.5429   0.01910   0.01148  -0.0428   0.0605   0.2355
  10.750   1.5568   0.01973   0.01214  -0.0412   0.0573   0.2358
  11.000   1.5632   0.02041   0.01285  -0.0384   0.0547   0.2360
  11.250   1.5660   0.02139   0.01387  -0.0356   0.0514   0.2361
  11.500   1.5731   0.02235   0.01488  -0.0338   0.0495   0.2362
  11.750   1.5811   0.02341   0.01599  -0.0324   0.0482   0.2366
  12.000   1.5868   0.02476   0.01739  -0.0312   0.0457   0.2368
  12.250   1.5882   0.02661   0.01927  -0.0300   0.0423   0.2370
  12.500   1.5922   0.02834   0.02104  -0.0291   0.0392   0.2370
  12.750   1.5880   0.03088   0.02358  -0.0282   0.0316   0.2372
  13.000   1.5685   0.03500   0.02766  -0.0274   0.0171   0.2372
  13.250   1.5613   0.03815   0.03088  -0.0270   0.0136   0.2372
  13.500   1.5605   0.04077   0.03357  -0.0268   0.0124   0.2373
  13.750   1.5593   0.04351   0.03640  -0.0268   0.0116   0.2374
  14.000   1.5550   0.04671   0.03968  -0.0269   0.0106   0.2376
  14.500   1.5480   0.05321   0.04633  -0.0277   0.0094   0.2378
  14.750   1.5456   0.05651   0.04972  -0.0283   0.0092   0.2379
  15.000   1.5406   0.06023   0.05354  -0.0290   0.0086   0.2383
  15.250   1.5359   0.06404   0.05743  -0.0300   0.0082   0.2384
  15.500   1.5297   0.06811   0.06158  -0.0310   0.0079   0.2386
  15.750   1.5213   0.07262   0.06619  -0.0324   0.0075   0.2386
  16.000   1.5148   0.07697   0.07062  -0.0337   0.0073   0.2388
  16.250   1.5094   0.08119   0.07494  -0.0351   0.0070   0.2391
  16.500   1.5032   0.08566   0.07949  -0.0366   0.0069   0.2393
  16.750   1.4960   0.09035   0.08429  -0.0383   0.0067   0.2394
  17.000   1.4880   0.09528   0.08930  -0.0402   0.0065   0.2395
  17.250   1.4791   0.10044   0.09455  -0.0422   0.0062   0.2397
  17.500   1.4713   0.10549   0.09971  -0.0443   0.0061   0.2399
  17.750   1.4611   0.11105   0.10536  -0.0466   0.0060   0.2401
  18.000   1.4507   0.11676   0.11116  -0.0491   0.0057   0.2402
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