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JN-153 AIRFOIL (jn153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: JN-153 AIRFOIL (jn153-il)
Reynolds number: 1,000,000
Max Cl/Cd: 165.93 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-jn153-il-1000000-n5.txt
Download as CSV file: xf-jn153-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.1612   0.09653   0.09210  -0.0980   0.4615   0.0102
  -9.750   0.1697   0.09408   0.08966  -0.0990   0.4615   0.0102
  -9.500   0.1742   0.09078   0.08637  -0.1004   0.4613   0.0103
  -9.250   0.1814   0.08810   0.08370  -0.1014   0.4611   0.0103
  -9.000   0.1888   0.08549   0.08110  -0.1024   0.4611   0.0103
  -8.750   0.1981   0.08352   0.07915  -0.1029   0.4609   0.0105
  -8.500   0.2063   0.08128   0.07692  -0.1037   0.4607   0.0106
  -8.250   0.2157   0.07931   0.07496  -0.1045   0.4606   0.0107
  -8.000   0.2202   0.07639   0.07207  -0.1056   0.4605   0.0107
  -7.750   0.2228   0.07315   0.06885  -0.1069   0.4603   0.0106
  -7.500   0.2345   0.07185   0.06757  -0.1072   0.4602   0.0108
  -7.250   0.2427   0.06989   0.06562  -0.1079   0.4600   0.0110
  -7.000   0.2710   0.05491   0.05091  -0.1008   0.4593   0.0118
  -6.500   0.1294   0.02283   0.01774  -0.1448   0.4600   0.0078
  -6.250   0.1525   0.01891   0.01321  -0.1471   0.4597   0.0079
  -6.000   0.1796   0.01726   0.01125  -0.1480   0.4593   0.0080
  -5.750   0.2078   0.01644   0.01026  -0.1485   0.4589   0.0081
  -5.500   0.2365   0.01586   0.00956  -0.1489   0.4587   0.0082
  -5.250   0.2653   0.01542   0.00904  -0.1492   0.4584   0.0084
  -5.000   0.2943   0.01506   0.00859  -0.1495   0.4581   0.0085
  -4.750   0.3235   0.01469   0.00815  -0.1498   0.4580   0.0086
  -4.500   0.3528   0.01436   0.00776  -0.1500   0.4579   0.0088
  -4.250   0.3821   0.01405   0.00738  -0.1503   0.4579   0.0090
  -4.000   0.4116   0.01375   0.00702  -0.1506   0.4578   0.0092
  -3.750   0.4411   0.01349   0.00671  -0.1508   0.4577   0.0095
  -3.500   0.4707   0.01325   0.00643  -0.1511   0.4576   0.0097
  -3.250   0.5003   0.01305   0.00618  -0.1514   0.4574   0.0099
  -3.000   0.5300   0.01285   0.00595  -0.1516   0.4572   0.0101
  -2.750   0.5596   0.01267   0.00574  -0.1519   0.4569   0.0102
  -2.500   0.5893   0.01250   0.00555  -0.1522   0.4567   0.0103
  -2.250   0.6192   0.01228   0.00531  -0.1525   0.4564   0.0106
  -2.000   0.6490   0.01215   0.00516  -0.1528   0.4561   0.0109
  -1.750   0.6787   0.01205   0.00505  -0.1531   0.4559   0.0111
  -1.500   0.7084   0.01196   0.00496  -0.1534   0.4555   0.0114
  -1.250   0.7381   0.01189   0.00488  -0.1536   0.4552   0.0119
  -1.000   0.7677   0.01184   0.00483  -0.1539   0.4548   0.0125
  -0.750   0.7973   0.01180   0.00479  -0.1542   0.4545   0.0130
  -0.500   0.8270   0.01172   0.00471  -0.1545   0.4540   0.0139
  -0.250   0.8565   0.01166   0.00465  -0.1547   0.4533   0.0151
   0.000   0.8861   0.01160   0.00459  -0.1550   0.4526   0.0174
   0.250   0.9157   0.01154   0.00455  -0.1553   0.4520   0.0224
   0.500   0.9452   0.01149   0.00453  -0.1556   0.4513   0.0334
   0.750   0.9749   0.01141   0.00452  -0.1559   0.4507   0.0579
   1.000   1.0047   0.01128   0.00453  -0.1564   0.4501   0.1122
   1.250   1.0357   0.01093   0.00458  -0.1574   0.4495   0.2828
   1.500   1.0656   0.01079   0.00466  -0.1580   0.4490   0.3792
   1.750   1.0953   0.01072   0.00474  -0.1584   0.4485   0.4467
   2.000   1.1249   0.01066   0.00482  -0.1589   0.4481   0.5133
   2.250   1.1543   0.01063   0.00490  -0.1593   0.4476   0.5676
   2.500   1.1836   0.01061   0.00496  -0.1596   0.4471   0.6129
   2.750   1.2127   0.01060   0.00503  -0.1599   0.4465   0.6557
   3.000   1.2416   0.01062   0.00513  -0.1602   0.4458   0.7002
   3.250   1.2703   0.01066   0.00526  -0.1604   0.4451   0.7488
   3.750   1.3230   0.01062   0.00552  -0.1599   0.4441   0.8827
   4.000   1.3457   0.01050   0.00553  -0.1587   0.4437   1.0000
   4.250   1.3744   0.01056   0.00560  -0.1590   0.4431   1.0000
   4.500   1.4030   0.01062   0.00566  -0.1593   0.4424   1.0000
   4.750   1.4316   0.01068   0.00573  -0.1595   0.4415   1.0000
   5.000   1.4601   0.01075   0.00580  -0.1598   0.4406   1.0000
   5.250   1.4885   0.01082   0.00589  -0.1601   0.4397   1.0000
   5.500   1.5168   0.01088   0.00596  -0.1603   0.4388   1.0000
   5.750   1.5451   0.01095   0.00603  -0.1606   0.4378   1.0000
   6.000   1.5733   0.01100   0.00609  -0.1609   0.4368   1.0000
   6.250   1.6016   0.01103   0.00613  -0.1611   0.4358   1.0000
   6.500   1.6297   0.01105   0.00616  -0.1614   0.4347   1.0000
   6.750   1.6577   0.01107   0.00618  -0.1616   0.4336   1.0000
   7.000   1.6854   0.01112   0.00623  -0.1618   0.4326   1.0000
   7.250   1.7130   0.01119   0.00632  -0.1620   0.4315   1.0000
   7.500   1.7405   0.01130   0.00647  -0.1623   0.4300   1.0000
   7.750   1.7681   0.01138   0.00661  -0.1625   0.4278   1.0000
   8.000   1.7956   0.01143   0.00669  -0.1627   0.4251   1.0000
   8.250   1.8231   0.01142   0.00670  -0.1630   0.4221   1.0000
   8.500   1.8504   0.01141   0.00669  -0.1631   0.4185   1.0000
   8.750   1.8774   0.01143   0.00673  -0.1633   0.4122   1.0000
   9.000   1.9032   0.01147   0.00674  -0.1633   0.4051   1.0000
   9.250   1.9273   0.01164   0.00687  -0.1630   0.3967   1.0000
   9.500   1.9504   0.01190   0.00712  -0.1626   0.3889   1.0000
   9.750   1.9715   0.01228   0.00746  -0.1619   0.3811   1.0000
  10.000   1.9937   0.01260   0.00779  -0.1614   0.3748   1.0000
  10.500   2.0355   0.01334   0.00854  -0.1600   0.3644   1.0000
  10.750   2.0544   0.01377   0.00898  -0.1590   0.3585   1.0000
  11.000   2.0722   0.01423   0.00944  -0.1578   0.3533   1.0000
  11.250   2.0901   0.01464   0.00989  -0.1567   0.3483   1.0000
  11.500   2.1028   0.01517   0.01043  -0.1547   0.3436   1.0000
  11.750   2.1145   0.01566   0.01095  -0.1524   0.3398   1.0000
  12.000   2.1265   0.01616   0.01150  -0.1504   0.3358   1.0000
  12.250   2.1332   0.01687   0.01224  -0.1476   0.3312   1.0000
  12.500   2.1358   0.01778   0.01318  -0.1445   0.3269   1.0000
  12.750   2.1403   0.01868   0.01414  -0.1418   0.3225   1.0000
  13.000   2.1352   0.02014   0.01566  -0.1385   0.3180   1.0000
  13.250   2.1112   0.02318   0.01877  -0.1344   0.3136   1.0000
  13.500   2.0859   0.02763   0.02336  -0.1325   0.3095   1.0000
  13.750   1.9835   0.04046   0.03638  -0.1291   0.3018   1.0000
  14.000   1.9237   0.04866   0.04467  -0.1267   0.2960   1.0000
  14.250   1.8883   0.05462   0.05068  -0.1253   0.2897   1.0000
  14.500   1.8645   0.05979   0.05588  -0.1246   0.2840   1.0000
  14.750   1.8582   0.06324   0.05936  -0.1243   0.2785   1.0000
  15.000   1.8408   0.06804   0.06416  -0.1240   0.2715   1.0000
  15.250   1.8397   0.07104   0.06720  -0.1240   0.2656   1.0000
  15.500   1.8304   0.07503   0.07117  -0.1240   0.2580   1.0000
  15.750   1.8294   0.07812   0.07427  -0.1241   0.2514   1.0000
  16.000   1.8188   0.08246   0.07860  -0.1242   0.2439   1.0000
  16.250   1.8215   0.08514   0.08130  -0.1244   0.2376   1.0000
  16.500   1.8148   0.08906   0.08520  -0.1247   0.2299   1.0000
  16.750   1.8117   0.09261   0.08877  -0.1250   0.2228   1.0000
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