JN-153 AIRFOIL (jn153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: JN-153 AIRFOIL (jn153-il) Reynolds number: 1,000,000 Max Cl/Cd: 163.27 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-jn153-il-1000000.txt Download as CSV file: xf-jn153-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.1782 0.09272 0.08853 -0.1013 0.4800 0.0130
-9.250 0.1847 0.08982 0.08565 -0.1025 0.4798 0.0130
-9.000 0.1918 0.08706 0.08291 -0.1032 0.4798 0.0131
-8.750 0.2051 0.08540 0.08125 -0.1034 0.4796 0.0133
-8.500 0.2143 0.08329 0.07916 -0.1041 0.4794 0.0134
-8.250 0.2236 0.08127 0.07716 -0.1048 0.4794 0.0136
-8.000 0.2314 0.07901 0.07492 -0.1057 0.4792 0.0137
-7.750 0.2392 0.07678 0.07271 -0.1065 0.4790 0.0138
-7.500 0.2467 0.07458 0.07053 -0.1073 0.4789 0.0141
-7.250 0.2536 0.07230 0.06828 -0.1082 0.4787 0.0144
-7.000 0.2598 0.06993 0.06593 -0.1091 0.4785 0.0147
-6.750 0.2641 0.06730 0.06333 -0.1100 0.4784 0.0151
-6.500 0.2666 0.06459 0.06066 -0.1109 0.4782 0.0154
-6.250 0.2553 0.06079 0.05692 -0.1123 0.4781 0.0158
-6.000 0.2582 0.05680 0.05296 -0.1161 0.4778 0.0158
-5.750 0.2672 0.05244 0.04861 -0.1216 0.4774 0.0159
-5.500 0.2748 0.04696 0.04312 -0.1285 0.4772 0.0161
-5.250 0.2915 0.04275 0.03885 -0.1337 0.4770 0.0162
-5.000 0.3102 0.03920 0.03520 -0.1375 0.4768 0.0163
-4.750 0.3313 0.03641 0.03231 -0.1403 0.4764 0.0165
-4.500 0.3545 0.03365 0.02940 -0.1427 0.4760 0.0168
-4.250 0.3795 0.03090 0.02647 -0.1449 0.4755 0.0173
-4.000 0.4091 0.02461 0.01942 -0.1485 0.4751 0.0192
-3.750 0.4362 0.02355 0.01832 -0.1492 0.4748 0.0195
-3.500 0.4695 0.01723 0.01098 -0.1510 0.4744 0.0132
-3.250 0.4986 0.01663 0.01024 -0.1514 0.4738 0.0132
-3.000 0.5266 0.01624 0.00977 -0.1516 0.4728 0.0133
-2.750 0.5557 0.01588 0.00938 -0.1519 0.4724 0.0137
-2.500 0.5852 0.01558 0.00905 -0.1522 0.4722 0.0142
-2.250 0.6147 0.01534 0.00879 -0.1524 0.4720 0.0147
-2.000 0.6443 0.01512 0.00853 -0.1527 0.4718 0.0152
-1.750 0.6740 0.01490 0.00828 -0.1529 0.4715 0.0155
-1.500 0.7037 0.01474 0.00810 -0.1532 0.4711 0.0158
-1.250 0.7338 0.01440 0.00774 -0.1537 0.4706 0.0162
-1.000 0.7637 0.01422 0.00756 -0.1540 0.4700 0.0167
-0.750 0.7934 0.01411 0.00746 -0.1543 0.4694 0.0175
-0.500 0.8230 0.01404 0.00738 -0.1546 0.4688 0.0185
-0.250 0.8529 0.01391 0.00724 -0.1549 0.4680 0.0198
0.000 0.8826 0.01383 0.00716 -0.1552 0.4673 0.0220
0.250 0.9126 0.01371 0.00707 -0.1556 0.4666 0.0329
0.500 0.9431 0.01344 0.00705 -0.1563 0.4659 0.1213
0.750 0.9740 0.01305 0.00711 -0.1573 0.4652 0.3052
1.000 1.0036 0.01295 0.00718 -0.1577 0.4645 0.3829
1.250 1.0333 0.01287 0.00726 -0.1582 0.4639 0.4556
1.500 1.0629 0.01281 0.00736 -0.1586 0.4633 0.5312
1.750 1.0926 0.01272 0.00748 -0.1591 0.4627 0.6237
2.000 1.1217 0.01258 0.00760 -0.1594 0.4621 0.7400
2.250 1.1471 0.01242 0.00771 -0.1588 0.4614 0.8633
2.500 1.1680 0.01228 0.00770 -0.1571 0.4607 1.0000
2.750 1.1974 0.01247 0.00783 -0.1575 0.4599 1.0000
3.000 1.2254 0.01297 0.00829 -0.1577 0.4587 1.0000
3.250 1.2531 0.01328 0.00861 -0.1579 0.4578 1.0000
3.500 1.2822 0.01328 0.00860 -0.1582 0.4574 1.0000
3.750 1.3111 0.01330 0.00860 -0.1585 0.4568 1.0000
4.000 1.3399 0.01330 0.00861 -0.1588 0.4561 1.0000
4.250 1.3686 0.01332 0.00862 -0.1590 0.4553 1.0000
4.500 1.3972 0.01335 0.00865 -0.1593 0.4544 1.0000
4.750 1.4257 0.01339 0.00869 -0.1595 0.4534 1.0000
5.000 1.4540 0.01344 0.00875 -0.1598 0.4525 1.0000
5.250 1.4823 0.01349 0.00880 -0.1600 0.4516 1.0000
5.500 1.5106 0.01352 0.00883 -0.1603 0.4507 1.0000
5.750 1.5391 0.01354 0.00885 -0.1605 0.4498 1.0000
6.000 1.5677 0.01354 0.00883 -0.1609 0.4490 1.0000
6.250 1.5966 0.01352 0.00880 -0.1612 0.4481 1.0000
6.500 1.6254 0.01350 0.00876 -0.1616 0.4473 1.0000
6.750 1.6543 0.01353 0.00877 -0.1620 0.4464 1.0000
7.000 1.6827 0.01366 0.00888 -0.1624 0.4454 1.0000
7.250 1.7098 0.01386 0.00910 -0.1625 0.4442 1.0000
7.500 1.7365 0.01380 0.00909 -0.1626 0.4433 1.0000
7.750 1.7632 0.01374 0.00908 -0.1626 0.4420 1.0000
8.000 1.7901 0.01366 0.00905 -0.1627 0.4405 1.0000
8.250 1.8174 0.01357 0.00899 -0.1628 0.4388 1.0000
8.500 1.8451 0.01341 0.00885 -0.1630 0.4371 1.0000
8.750 1.8731 0.01320 0.00864 -0.1632 0.4354 1.0000
9.000 1.9008 0.01302 0.00845 -0.1635 0.4338 1.0000
9.250 1.9279 0.01293 0.00835 -0.1636 0.4320 1.0000
9.500 1.9536 0.01292 0.00844 -0.1636 0.4296 1.0000
9.750 1.9799 0.01290 0.00848 -0.1636 0.4264 1.0000
10.000 2.0064 0.01285 0.00847 -0.1637 0.4235 1.0000
10.250 2.0327 0.01279 0.00843 -0.1638 0.4210 1.0000
10.500 2.0583 0.01284 0.00852 -0.1638 0.4175 1.0000
10.750 2.0837 0.01289 0.00861 -0.1638 0.4129 1.0000
11.000 2.1078 0.01291 0.00863 -0.1635 0.4083 1.0000
11.250 2.1312 0.01308 0.00883 -0.1632 0.4030 1.0000
11.500 2.1524 0.01330 0.00904 -0.1625 0.3974 1.0000
11.750 2.1724 0.01360 0.00936 -0.1617 0.3920 1.0000
12.000 2.1902 0.01397 0.00974 -0.1606 0.3860 1.0000
12.250 2.2056 0.01443 0.01020 -0.1590 0.3805 1.0000
12.500 2.2189 0.01487 0.01068 -0.1571 0.3748 1.0000
13.000 2.2360 0.01601 0.01187 -0.1518 0.3647 1.0000
13.250 2.2417 0.01672 0.01262 -0.1489 0.3597 1.0000
13.500 2.2409 0.01773 0.01365 -0.1453 0.3549 1.0000
13.750 2.2454 0.01864 0.01463 -0.1428 0.3504 1.0000
14.000 2.2361 0.02032 0.01636 -0.1390 0.3454 1.0000
14.250 2.2149 0.02317 0.01928 -0.1353 0.3405 1.0000
14.500 2.1897 0.02734 0.02356 -0.1330 0.3351 1.0000
14.750 2.0976 0.03873 0.03508 -0.1296 0.3267 1.0000
15.000 2.0366 0.04708 0.04353 -0.1273 0.3193 1.0000
15.250 1.9893 0.05414 0.05061 -0.1256 0.3121 1.0000
15.500 1.9703 0.05882 0.05535 -0.1250 0.3060 1.0000
15.750 1.9502 0.06367 0.06017 -0.1246 0.2993 1.0000
16.000 1.9439 0.06724 0.06382 -0.1245 0.2939 1.0000
16.250 1.9294 0.07174 0.06830 -0.1244 0.2865 1.0000
16.500 1.9250 0.07520 0.07181 -0.1244 0.2803 1.0000
16.750 1.9164 0.07912 0.07571 -0.1245 0.2726 1.0000
17.000 1.9114 0.08275 0.07937 -0.1247 0.2656 1.0000
17.250 1.9007 0.08708 0.08367 -0.1250 0.2572 1.0000
17.500 1.9009 0.09011 0.08673 -0.1253 0.2499 1.0000
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Polar data table (+)
Polar graphs
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