JN-153 AIRFOIL (jn153-il)
JN-153 AIRFOIL - Narramore JN153 airfoil
| Details | Dat file | Parser | |
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(jn153-il) JN-153 AIRFOIL Narramore JN153 airfoil Max thickness 17.6% at 28.2% chord. Max camber 8.4% at 38.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
JN-153 AIRFOIL
66.0 55.0
0.0000000 0.0000000
0.0023478 0.0140157
0.0048772 0.0210059
0.0082966 0.0283462
0.0126160 0.0359566
0.0178253 0.0437770
0.0239147 0.0517375
0.0308640 0.0597981
0.0386633 0.0678788
0.0473026 0.0759595
0.0567520 0.0839603
0.0670013 0.0918412
0.0780207 0.0995421
0.0897900 0.1070132
0.1023195 0.1141842
0.1156189 0.1210354
0.1296683 0.1275665
0.1444078 0.1337778
0.1598074 0.1396091
0.1758069 0.1450405
0.1923665 0.1500419
0.2094461 0.1545733
0.2269858 0.1585748
0.2449555 0.1620163
0.2633153 0.1648079
0.2821152 0.1669495
0.3012951 0.1684411
0.3207950 0.1692927
0.3405550 0.1694744
0.3605051 0.1689361
0.3805552 0.1675978
0.4006254 0.1653795
0.4205357 0.1618912
0.4410162 0.1565829
0.4621668 0.1501547
0.4856274 0.1432666
0.5092680 0.1360686
0.5335387 0.1287307
0.5582593 0.1213228
0.5832899 0.1139449
0.6084706 0.1066470
0.6336913 0.0994591
0.6588019 0.0924412
0.6837024 0.0856033
0.7082430 0.0789754
0.7323436 0.0725774
0.7558842 0.0664294
0.7787746 0.0605414
0.8008952 0.0549132
0.8221756 0.0495550
0.8425361 0.0444767
0.8618765 0.0396684
0.8801369 0.0351299
0.8972373 0.0308713
0.9131376 0.0268627
0.9277580 0.0231239
0.9410683 0.0196250
0.9530086 0.0163660
0.9635389 0.0133169
0.9726491 0.0104177
0.9804294 0.0076184
0.9870196 0.0050289
0.9924098 0.0028394
0.9964999 0.0012297
0.9991000 0.0002899
1.0000000 0.0000000
0.0000000 0.0000000
0.0002448 -.0039587
0.0014097 -.0085644
0.0037100 -.0118342
0.0077802 -.0139739
0.0138803 -.0155934
0.0217205 -.0168227
0.0311905 -.0177319
0.0422306 -.0183310
0.0547706 -.0186599
0.0687607 -.0187488
0.0841207 -.0186075
0.1008206 -.0182660
0.1187706 -.0177345
0.1379206 -.0170229
0.1581905 -.0161412
0.1795105 -.0151094
0.2018104 -.0139275
0.2250103 -.0125855
0.2490302 -.0110935
0.2737901 -.0093814
0.2992899 -.0073792
0.3256098 -.0051770
0.3526796 -.0028747
0.3803894 -.0005424
0.4086592 0.0017600
0.4373591 0.0040024
0.4664090 0.0061549
0.4956888 0.0081774
0.5250887 0.0100399
0.5545086 0.0117423
0.5838385 0.0132448
0.6129584 0.0145373
0.6417583 0.0156197
0.6701383 0.0164721
0.6979983 0.0170845
0.7252083 0.0174668
0.7516882 0.0175990
0.7773083 0.0175112
0.8019983 0.0171833
0.8256284 0.0166453
0.8481285 0.0158872
0.8693987 0.0149390
0.8893387 0.0138207
0.9078789 0.0125422
0.9249290 0.0111337
0.9404091 0.0096150
0.9542593 0.0080361
0.9663894 0.0064072
0.9767196 0.0047680
0.9851497 0.0032387
0.9916798 0.0019193
0.9963199 0.0008897
0.9990800 0.0002299
1.0000000 0.0000000
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Polars for JN-153 AIRFOIL (jn153-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| jn153-il | 50,000 | 9 | 4.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 50,000 | 5 | 6.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 100,000 | 9 | 5.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 100,000 | 5 | 18.1 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 200,000 | 9 | 16.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 200,000 | 5 | 44.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 500,000 | 9 | 98.8 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 500,000 | 5 | 112.6 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 1,000,000 | 9 | 163.3 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 1,000,000 | 5 | 165.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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