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JN-153 AIRFOIL (jn153-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: JN-153 AIRFOIL (jn153-il)
Reynolds number: 200,000
Max Cl/Cd: 44.62 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-jn153-il-200000-n5.txt
Download as CSV file: xf-jn153-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: JN-153 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.1241   0.11529   0.10874  -0.0860   0.5041   0.0254
 -10.500   0.1295   0.11270   0.10617  -0.0876   0.5039   0.0257
 -10.250   0.1332   0.11025   0.10375  -0.0894   0.5036   0.0259
 -10.000   0.1442   0.10749   0.10103  -0.0900   0.5033   0.0261
  -9.750   0.1547   0.10512   0.09868  -0.0907   0.5031   0.0263
  -9.500   0.1662   0.10303   0.09661  -0.0911   0.5028   0.0279
  -9.250   0.1739   0.10065   0.09427  -0.0922   0.5025   0.0286
  -9.000   0.1792   0.09824   0.09189  -0.0937   0.5024   0.0294
  -8.750   0.1815   0.09577   0.08946  -0.0956   0.5021   0.0297
  -8.500   0.1838   0.09320   0.08694  -0.0974   0.5019   0.0298
  -8.250   0.1931   0.09066   0.08444  -0.0980   0.5017   0.0300
  -8.000   0.2058   0.08847   0.08229  -0.0980   0.5014   0.0302
  -7.750   0.2156   0.08635   0.08020  -0.0984   0.5010   0.0306
  -7.500   0.2239   0.08419   0.07808  -0.0990   0.5008   0.0310
  -7.250   0.2313   0.08200   0.07593  -0.0998   0.5004   0.0314
  -7.000   0.2379   0.07977   0.07375  -0.1006   0.5000   0.0320
  -6.750   0.2431   0.07741   0.07144  -0.1015   0.4994   0.0327
  -6.500   0.2468   0.07501   0.06910  -0.1026   0.4989   0.0333
  -6.250   0.2419   0.07236   0.06653  -0.1042   0.4985   0.0339
  -6.000   0.2383   0.06960   0.06384  -0.1067   0.4982   0.0340
  -5.750   0.2438   0.06640   0.06069  -0.1104   0.4977   0.0341
  -4.750   0.2906   0.04445   0.03837  -0.1312   0.4960   0.0189
  -4.500   0.3119   0.04154   0.03528  -0.1340   0.4953   0.0187
  -4.250   0.3359   0.03831   0.03178  -0.1367   0.4946   0.0185
  -4.000   0.3626   0.03510   0.02819  -0.1392   0.4939   0.0183
  -3.750   0.3912   0.03223   0.02486  -0.1412   0.4934   0.0182
  -3.500   0.4207   0.02997   0.02212  -0.1425   0.4928   0.0184
  -3.250   0.4502   0.02839   0.02011  -0.1434   0.4923   0.0187
  -3.000   0.4786   0.02759   0.01910  -0.1439   0.4917   0.0194
  -2.750   0.5065   0.02721   0.01863  -0.1442   0.4910   0.0204
  -2.500   0.5355   0.02655   0.01773  -0.1445   0.4904   0.0216
  -2.250   0.5645   0.02590   0.01685  -0.1447   0.4897   0.0220
  -2.000   0.5931   0.02542   0.01622  -0.1448   0.4891   0.0223
  -1.750   0.6212   0.02511   0.01589  -0.1451   0.4885   0.0229
  -1.500   0.6490   0.02497   0.01571  -0.1452   0.4880   0.0236
  -1.250   0.6749   0.02490   0.01569  -0.1451   0.4870   0.0244
  -1.000   0.7008   0.02490   0.01572  -0.1450   0.4857   0.0255
  -0.750   0.7270   0.02495   0.01583  -0.1451   0.4844   0.0269
  -0.500   0.7534   0.02508   0.01596  -0.1451   0.4831   0.0291
  -0.250   0.7801   0.02521   0.01612  -0.1452   0.4818   0.0336
   0.000   0.8074   0.02529   0.01622  -0.1453   0.4805   0.0404
   0.250   0.8353   0.02531   0.01629  -0.1456   0.4794   0.0580
   0.500   0.8645   0.02502   0.01644  -0.1465   0.4783   0.1898
   0.750   0.8932   0.02474   0.01677  -0.1472   0.4773   0.4054
   1.000   0.9206   0.02469   0.01700  -0.1473   0.4763   0.5167
   1.250   0.9461   0.02457   0.01723  -0.1469   0.4755   0.6475
   1.500   0.9656   0.02439   0.01738  -0.1449   0.4747   0.7827
   1.750   0.9828   0.02418   0.01731  -0.1422   0.4740   1.0000
   2.000   1.0124   0.02443   0.01739  -0.1427   0.4732   1.0000
   2.250   1.0384   0.02489   0.01778  -0.1427   0.4721   1.0000
   2.500   1.0519   0.02614   0.01917  -0.1414   0.4688   1.0000
   2.750   1.0726   0.02688   0.01992  -0.1409   0.4666   1.0000
   3.000   1.0966   0.02736   0.02035  -0.1407   0.4648   1.0000
   3.250   1.1221   0.02770   0.02064  -0.1406   0.4635   1.0000
   3.500   1.1479   0.02802   0.02090  -0.1406   0.4623   1.0000
   3.750   1.1743   0.02830   0.02112  -0.1406   0.4613   1.0000
   4.000   1.2014   0.02852   0.02128  -0.1406   0.4605   1.0000
   4.250   1.2294   0.02868   0.02136  -0.1408   0.4597   1.0000
   4.500   1.2583   0.02877   0.02138  -0.1411   0.4590   1.0000
   4.750   1.2877   0.02886   0.02139  -0.1414   0.4583   1.0000
   5.250   1.0837   0.04707   0.04059  -0.1247   0.4289   1.0000
   5.500   1.1206   0.04597   0.03941  -0.1246   0.4299   1.0000
   5.750   1.1551   0.04505   0.03843  -0.1243   0.4306   1.0000
   6.000   1.1880   0.04424   0.03757  -0.1241   0.4311   1.0000
   6.250   1.2199   0.04350   0.03677  -0.1237   0.4315   1.0000
   6.500   1.2521   0.04274   0.03597  -0.1235   0.4318   1.0000
  10.000   1.2787   0.07712   0.07057  -0.1194   0.3691   1.0000
  10.500   1.2744   0.08391   0.07743  -0.1195   0.3572   1.0000
  11.000   1.2742   0.09051   0.08414  -0.1198   0.3458   1.0000
  11.250   1.2957   0.09077   0.08439  -0.1197   0.3447   1.0000
  11.500   1.3194   0.09072   0.08435  -0.1196   0.3438   1.0000
  11.750   1.3441   0.09051   0.08416  -0.1194   0.3430   1.0000
  12.000   1.3691   0.09025   0.08392  -0.1193   0.3424   1.0000
  12.500   1.3637   0.09774   0.09151  -0.1199   0.3301   1.0000
  15.000   1.5020   0.11101   0.10518  -0.1214   0.2987   1.0000
  15.500   1.5025   0.11782   0.11214  -0.1227   0.2869   1.0000
  15.750   1.5300   0.11692   0.11126  -0.1225   0.2859   1.0000
  16.250   1.5241   0.12482   0.11931  -0.1242   0.2731   1.0000
  16.500   1.5359   0.12640   0.12093  -0.1246   0.2694   1.0000
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