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AH 93-W-215 (ah93w215-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AH 93-W-215 (ah93w215-il)
Reynolds number: 50,000
Max Cl/Cd: 6.39 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah93w215-il-50000-n5.txt
Download as CSV file: xf-ah93w215-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 93-W-215                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3836   0.10665   0.09895  -0.0627   1.0000   0.1196
 -12.500  -0.5044   0.08272   0.07493  -0.0749   1.0000   0.1222
 -12.250  -0.6019   0.06995   0.06202  -0.0793   1.0000   0.1220
 -12.000  -0.6461   0.06197   0.05375  -0.0835   0.9626   0.1230
 -11.750  -0.6501   0.05758   0.04909  -0.0870   0.9377   0.1254
 -11.500  -0.6195   0.05574   0.04721  -0.0902   0.9224   0.1293
 -11.250  -0.6115   0.05225   0.04338  -0.0936   0.9074   0.1332
 -11.000  -0.6110   0.04852   0.03909  -0.0962   0.8933   0.1370
 -10.750  -0.5679   0.04724   0.03787  -0.0998   0.8830   0.1420
 -10.500  -0.5442   0.04502   0.03535  -0.1025   0.8726   0.1476
 -10.250  -0.5284   0.04318   0.03322  -0.1033   0.8600   0.1525
 -10.000  -0.4934   0.04197   0.03194  -0.1059   0.8514   0.1588
  -9.750  -0.4834   0.04061   0.03028  -0.1051   0.8401   0.1644
  -9.500  -0.4500   0.03950   0.02913  -0.1070   0.8328   0.1711
  -9.250  -0.4376   0.03865   0.02815  -0.1058   0.8232   0.1775
  -9.000  -0.4156   0.03766   0.02702  -0.1059   0.8155   0.1847
  -8.750  -0.3955   0.03696   0.02626  -0.1055   0.8083   0.1925
  -8.500  -0.3824   0.03624   0.02542  -0.1040   0.8004   0.2002
  -8.250  -0.3584   0.03559   0.02476  -0.1040   0.7943   0.2093
  -8.000  -0.3422   0.03497   0.02406  -0.1028   0.7882   0.2187
  -7.750  -0.3287   0.03454   0.02365  -0.1011   0.7813   0.2281
  -7.500  -0.3111   0.03399   0.02309  -0.1000   0.7755   0.2392
  -7.250  -0.2912   0.03340   0.02240  -0.0993   0.7707   0.2527
  -7.000  -0.2836   0.03318   0.02233  -0.0965   0.7640   0.2633
  -6.750  -0.2715   0.03284   0.02203  -0.0944   0.7584   0.2770
  -6.500  -0.2552   0.03243   0.02165  -0.0930   0.7537   0.2935
  -6.250  -0.2398   0.03210   0.02137  -0.0914   0.7493   0.3118
  -5.750  -0.2281   0.03197   0.02147  -0.0849   0.7375   0.3484
  -5.500  -0.2118   0.03184   0.02146  -0.0830   0.7332   0.3724
  -5.250  -0.1927   0.03176   0.02143  -0.0816   0.7297   0.4000
  -5.000  -0.1963   0.03217   0.02197  -0.0766   0.7232   0.4194
  -4.750  -0.1889   0.03240   0.02225  -0.0732   0.7178   0.4437
  -4.500  -0.1702   0.03265   0.02255  -0.0713   0.7136   0.4693
  -4.250  -0.1481   0.03283   0.02268  -0.0700   0.7103   0.4956
  -4.000  -0.1509   0.03346   0.02337  -0.0650   0.7043   0.5128
  -3.750  -0.1471   0.03399   0.02391  -0.0611   0.6986   0.5314
  -3.500  -0.1309   0.03434   0.02423  -0.0588   0.6942   0.5516
  -3.250  -0.1068   0.03462   0.02444  -0.0577   0.6908   0.5720
  -3.000  -0.1027   0.03517   0.02497  -0.0538   0.6858   0.5881
  -2.750  -0.1154   0.03591   0.02573  -0.0479   0.6788   0.6024
  -2.500  -0.0966   0.03643   0.02624  -0.0459   0.6744   0.6182
  -2.250  -0.0702   0.03675   0.02650  -0.0450   0.6711   0.6348
  -2.000  -0.0401   0.03698   0.02664  -0.0447   0.6685   0.6518
  -1.750  -0.0840   0.03832   0.02810  -0.0348   0.6584   0.6615
  -1.500  -0.0683   0.03885   0.02861  -0.0326   0.6539   0.6757
  -1.250  -0.0422   0.03910   0.02878  -0.0317   0.6507   0.6920
  -1.000  -0.0130   0.03925   0.02883  -0.0313   0.6483   0.7090
  -0.750  -0.0652   0.04101   0.03076  -0.0207   0.6369   0.7172
  -0.500  -0.0495   0.04143   0.03113  -0.0187   0.6327   0.7327
  -0.250  -0.0224   0.04155   0.03116  -0.0181   0.6298   0.7486
   0.000  -0.0348   0.04298   0.03265  -0.0132   0.6220   0.7598
   0.250  -0.0377   0.04391   0.03357  -0.0097   0.6153   0.7738
   0.500  -0.0147   0.04418   0.03379  -0.0087   0.6115   0.7870
   0.750   0.0174   0.04424   0.03376  -0.0089   0.6090   0.7989
   1.250   0.0067   0.04660   0.03615  -0.0023   0.5942   0.8264
   1.500   0.0363   0.04678   0.03627  -0.0025   0.5909   0.8390
   1.750   0.0689   0.04673   0.03615  -0.0028   0.5885   0.8527
   2.000   0.0463   0.04886   0.03835   0.0010   0.5777   0.8690
   2.250   0.0782   0.04938   0.03884  -0.0003   0.5735   0.8817
   2.500   0.1176   0.04961   0.03901  -0.0022   0.5706   0.8945
   2.750   0.1239   0.05136   0.04081  -0.0023   0.5622   0.9100
   3.000   0.1537   0.05237   0.04180  -0.0045   0.5565   0.9238
   3.250   0.2010   0.05292   0.04231  -0.0085   0.5530   0.9345
   3.500   0.2539   0.05323   0.04256  -0.0129   0.5505   0.9444
   3.750   0.2616   0.05602   0.04542  -0.0154   0.5395   0.9578
   4.000   0.3073   0.05671   0.04609  -0.0195   0.5353   0.9686
   4.250   0.3579   0.05701   0.04635  -0.0237   0.5326   0.9801
   4.500   0.3536   0.05979   0.04915  -0.0244   0.5221   1.0000
   4.750   0.3515   0.05986   0.04913  -0.0210   0.5176   1.0000
   5.000   0.3666   0.05973   0.04889  -0.0193   0.5146   1.0000
   5.250   0.3393   0.06195   0.05104  -0.0154   0.5046   1.0000
   5.500   0.3528   0.06251   0.05152  -0.0142   0.4998   1.0000
   5.750   0.3763   0.06272   0.05164  -0.0136   0.4968   1.0000
   6.000   0.3604   0.06518   0.05407  -0.0113   0.4870   1.0000
   6.250   0.3769   0.06594   0.05476  -0.0106   0.4822   1.0000
   6.500   0.4026   0.06623   0.05499  -0.0103   0.4791   1.0000
   6.750   0.3893   0.06893   0.05769  -0.0086   0.4694   1.0000
   7.000   0.4072   0.06974   0.05845  -0.0081   0.4645   1.0000
   7.250   0.4336   0.07005   0.05871  -0.0079   0.4615   1.0000
   7.500   0.4207   0.07300   0.06168  -0.0066   0.4516   1.0000
   7.750   0.4395   0.07384   0.06249  -0.0062   0.4469   1.0000
   8.000   0.4669   0.07409   0.06270  -0.0060   0.4439   1.0000
   8.250   0.4528   0.07735   0.06598  -0.0050   0.4336   1.0000
   8.500   0.4731   0.07812   0.06675  -0.0047   0.4292   1.0000
   8.750   0.5009   0.07834   0.06695  -0.0045   0.4264   1.0000
   9.000   0.4847   0.08198   0.07063  -0.0038   0.4155   1.0000
   9.250   0.5063   0.08271   0.07135  -0.0036   0.4115   1.0000
   9.500   0.5313   0.08314   0.07177  -0.0034   0.4083   1.0000
   9.750   0.5161   0.08691   0.07560  -0.0030   0.3975   1.0000
  10.000   0.5392   0.08750   0.07618  -0.0028   0.3937   1.0000
  10.250   0.5356   0.09046   0.07918  -0.0026   0.3856   1.0000
  10.500   0.5473   0.09204   0.08079  -0.0024   0.3794   1.0000
  10.750   0.5720   0.09244   0.08121  -0.0021   0.3760   1.0000
  11.000   0.5613   0.09622   0.08503  -0.0022   0.3666   1.0000
  11.250   0.5776   0.09743   0.08626  -0.0021   0.3614   1.0000
  11.500   0.6040   0.09758   0.08645  -0.0018   0.3582   1.0000
  11.750   0.5881   0.10207   0.09099  -0.0022   0.3478   1.0000
  12.000   0.6080   0.10290   0.09185  -0.0020   0.3434   1.0000
  12.250   0.6304   0.10348   0.09246  -0.0018   0.3400   1.0000
  12.500   0.6145   0.10816   0.09720  -0.0025   0.3295   1.0000
  12.750   0.6361   0.10880   0.09788  -0.0023   0.3257   1.0000
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