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CLARK YM-18 AIRFOIL (clarym18-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: CLARK YM-18 AIRFOIL (clarym18-il)
Reynolds number: 100,000
Max Cl/Cd: 43.38 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarym18-il-100000.txt
Download as CSV file: xf-clarym18-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK YM-18 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.7303   0.07117   0.06589  -0.0474   1.0000   0.1070
  -9.500  -0.7636   0.06691   0.06142  -0.0439   0.9998   0.1058
  -9.250  -0.7651   0.06057   0.05470  -0.0465   0.9933   0.1052
  -9.000  -0.7659   0.05498   0.04862  -0.0475   0.9859   0.1052
  -8.750  -0.7589   0.04998   0.04288  -0.0489   0.9794   0.1062
  -8.500  -0.7416   0.04720   0.03994  -0.0493   0.9724   0.1079
  -8.250  -0.7072   0.04583   0.03861  -0.0516   0.9673   0.1105
  -8.000  -0.6892   0.04363   0.03610  -0.0516   0.9600   0.1126
  -7.750  -0.6655   0.04114   0.03312  -0.0525   0.9537   0.1153
  -7.500  -0.6422   0.03909   0.03061  -0.0529   0.9476   0.1186
  -7.250  -0.6150   0.03812   0.02974  -0.0536   0.9406   0.1224
  -7.000  -0.5789   0.03680   0.02810  -0.0557   0.9357   0.1278
  -6.750  -0.5587   0.03556   0.02670  -0.0550   0.9281   0.1319
  -6.500  -0.5271   0.03485   0.02600  -0.0562   0.9220   0.1379
  -6.250  -0.4867   0.03375   0.02472  -0.0589   0.9179   0.1456
  -6.000  -0.4702   0.03333   0.02434  -0.0573   0.9087   0.1514
  -5.750  -0.4353   0.03252   0.02341  -0.0589   0.9032   0.1600
  -5.500  -0.3925   0.03202   0.02282  -0.0618   0.8996   0.1711
  -5.250  -0.3814   0.03167   0.02258  -0.0593   0.8894   0.1773
  -5.000  -0.3434   0.03114   0.02197  -0.0612   0.8842   0.1897
  -4.750  -0.3156   0.03089   0.02181  -0.0615   0.8777   0.2010
  -4.500  -0.2930   0.03062   0.02160  -0.0609   0.8697   0.2123
  -4.250  -0.2534   0.03014   0.02118  -0.0630   0.8651   0.2301
  -4.000  -0.2328   0.03002   0.02110  -0.0620   0.8569   0.2463
  -3.750  -0.2054   0.02977   0.02094  -0.0621   0.8499   0.2683
  -3.500  -0.1652   0.02926   0.02050  -0.0641   0.8458   0.3004
  -3.250  -0.1502   0.02925   0.02061  -0.0622   0.8359   0.3230
  -3.000  -0.1133   0.02872   0.02017  -0.0635   0.8292   0.3555
  -2.750  -0.0613   0.02778   0.01941  -0.0670   0.8256   0.3916
  -2.500  -0.0492   0.02774   0.01945  -0.0642   0.8121   0.4133
  -2.250   0.0044   0.02660   0.01849  -0.0676   0.8080   0.4523
  -2.000   0.0195   0.02657   0.01856  -0.0652   0.7960   0.4805
  -1.750   0.0607   0.02574   0.01800  -0.0666   0.7913   0.5261
  -1.500   0.1030   0.02479   0.01739  -0.0679   0.7882   0.5905
  -1.250   0.1103   0.02504   0.01798  -0.0641   0.7761   0.6503
  -1.000   0.1457   0.02437   0.01770  -0.0631   0.7718   0.7500
  -0.750   0.1903   0.02388   0.01736  -0.0632   0.7688   0.8337
  -0.500   0.2163   0.02446   0.01798  -0.0617   0.7575   0.8848
  -0.250   0.2901   0.02411   0.01748  -0.0678   0.7537   0.9219
   0.000   0.3792   0.02352   0.01669  -0.0773   0.7506   0.9440
   0.250   0.4500   0.02339   0.01644  -0.0848   0.7416   0.9634
   0.500   0.5297   0.02265   0.01555  -0.0937   0.7338   0.9788
   0.750   0.6044   0.02197   0.01474  -0.1024   0.7241   0.9932
   1.000   0.6516   0.02138   0.01402  -0.1061   0.7136   1.0000
   1.250   0.6653   0.02132   0.01390  -0.1039   0.7015   1.0000
   1.500   0.6923   0.02083   0.01326  -0.1035   0.6922   1.0000
   1.750   0.7038   0.02087   0.01327  -0.1008   0.6783   1.0000
   2.000   0.7232   0.02069   0.01299  -0.0992   0.6659   1.0000
   2.250   0.7494   0.02033   0.01248  -0.0985   0.6542   1.0000
   2.500   0.7627   0.02036   0.01245  -0.0958   0.6389   1.0000
   2.750   0.7795   0.02034   0.01235  -0.0937   0.6241   1.0000
   3.000   0.8003   0.02028   0.01216  -0.0922   0.6100   1.0000
   3.250   0.8261   0.02017   0.01186  -0.0915   0.5965   1.0000
   3.500   0.8405   0.02035   0.01197  -0.0890   0.5807   1.0000
   3.750   0.8557   0.02058   0.01211  -0.0866   0.5657   1.0000
   4.000   0.8739   0.02080   0.01222  -0.0848   0.5520   1.0000
   4.250   0.9001   0.02093   0.01214  -0.0843   0.5403   1.0000
   4.500   0.9120   0.02135   0.01256  -0.0815   0.5275   1.0000
   4.750   0.9319   0.02172   0.01284  -0.0800   0.5173   1.0000
   5.000   0.9517   0.02208   0.01311  -0.0786   0.5073   1.0000
   5.250   0.9698   0.02254   0.01351  -0.0769   0.4982   1.0000
   5.500   0.9893   0.02294   0.01386  -0.0755   0.4894   1.0000
   5.750   1.0118   0.02341   0.01424  -0.0746   0.4821   1.0000
   6.000   1.0256   0.02397   0.01484  -0.0722   0.4742   1.0000
   6.250   1.0550   0.02432   0.01505  -0.0725   0.4676   1.0000
   6.500   1.0660   0.02501   0.01582  -0.0698   0.4604   1.0000
   6.750   1.0858   0.02552   0.01632  -0.0685   0.4536   1.0000
   7.000   1.1173   0.02593   0.01659  -0.0692   0.4477   1.0000
   7.250   1.1239   0.02672   0.01754  -0.0658   0.4409   1.0000
   7.500   1.1456   0.02722   0.01803  -0.0649   0.4346   1.0000
   7.750   1.1764   0.02771   0.01840  -0.0655   0.4290   1.0000
   8.000   1.1821   0.02859   0.01946  -0.0621   0.4227   1.0000
   8.250   1.2030   0.02915   0.02002  -0.0611   0.4167   1.0000
   8.500   1.2372   0.02962   0.02035  -0.0623   0.4111   1.0000
   8.750   1.2383   0.03061   0.02157  -0.0584   0.4048   1.0000
   9.000   1.2604   0.03103   0.02196  -0.0575   0.3978   1.0000
   9.250   1.2836   0.03155   0.02243  -0.0569   0.3906   1.0000
   9.500   1.2897   0.03229   0.02330  -0.0538   0.3832   1.0000
   9.750   1.3329   0.03237   0.02311  -0.0561   0.3754   1.0000
  10.000   1.3253   0.03350   0.02452  -0.0510   0.3692   1.0000
  10.250   1.3420   0.03410   0.02515  -0.0496   0.3625   1.0000
  10.500   1.3746   0.03459   0.02553  -0.0505   0.3558   1.0000
  10.750   1.3672   0.03579   0.02697  -0.0457   0.3496   1.0000
  11.000   1.3921   0.03620   0.02732  -0.0454   0.3426   1.0000
  11.250   1.4074   0.03708   0.02824  -0.0439   0.3361   1.0000
  11.500   1.3980   0.03826   0.02960  -0.0389   0.3299   1.0000
  11.750   1.4541   0.03818   0.02925  -0.0430   0.3213   1.0000
  12.000   1.4239   0.03986   0.03124  -0.0354   0.3162   1.0000
  12.250   1.4225   0.04095   0.03244  -0.0320   0.3094   1.0000
  12.500   1.4575   0.04112   0.03248  -0.0329   0.3015   1.0000
  12.750   1.4287   0.04325   0.03489  -0.0268   0.2955   1.0000
  13.000   1.4668   0.04290   0.03435  -0.0278   0.2871   1.0000
  13.250   1.4425   0.04523   0.03692  -0.0228   0.2811   1.0000
  13.500   1.4315   0.04702   0.03885  -0.0194   0.2743   1.0000
  13.750   1.4582   0.04708   0.03879  -0.0192   0.2664   1.0000
  14.000   1.4211   0.05064   0.04265  -0.0147   0.2604   1.0000
  14.250   1.4725   0.04897   0.04067  -0.0159   0.2517   1.0000
  14.500   1.4177   0.05410   0.04621  -0.0111   0.2466   1.0000
  14.750   1.4191   0.05561   0.04774  -0.0097   0.2396   1.0000
  15.000   1.4226   0.05722   0.04936  -0.0085   0.2331   1.0000
  15.250   1.3807   0.06285   0.05526  -0.0065   0.2275   1.0000
  15.500   1.4435   0.05936   0.05144  -0.0068   0.2201   1.0000
  15.750   1.3719   0.06820   0.06073  -0.0050   0.2161   1.0000
  16.000   1.3053   0.07824   0.07107  -0.0055   0.2114   1.0000
  16.250   1.4136   0.06869   0.06107  -0.0040   0.2048   1.0000
  16.500   0.8403   0.17206   0.16524  -0.0442   0.1875   1.0000
  16.750   0.8407   0.17740   0.17061  -0.0465   0.1888   1.0000
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