JN-153 AIRFOIL (jn153-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: JN-153 AIRFOIL (jn153-il) Reynolds number: 500,000 Max Cl/Cd: 112.57 at α=10.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-jn153-il-500000-n5.txt Download as CSV file: xf-jn153-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.1832 0.09404 0.08881 -0.0964 0.4744 0.0152
-9.000 0.1867 0.09094 0.08572 -0.0982 0.4744 0.0157
-8.750 0.1882 0.08769 0.08250 -0.1001 0.4742 0.0158
-8.250 0.2013 0.08227 0.07712 -0.1023 0.4736 0.0159
-8.000 0.2077 0.07962 0.07448 -0.1034 0.4733 0.0159
-7.750 0.2168 0.07756 0.07245 -0.1039 0.4729 0.0160
-7.500 0.2300 0.07625 0.07115 -0.1038 0.4727 0.0163
-7.250 0.2397 0.07448 0.06940 -0.1043 0.4725 0.0167
-7.000 0.2475 0.07238 0.06733 -0.1051 0.4724 0.0171
-6.750 0.2529 0.06992 0.06490 -0.1059 0.4723 0.0174
-6.500 0.2576 0.06749 0.06252 -0.1068 0.4722 0.0174
-6.250 0.2601 0.06502 0.06009 -0.1074 0.4722 0.0175
-5.750 0.2451 0.05371 0.04886 -0.1164 0.4720 0.0129
-5.500 0.2582 0.05087 0.04603 -0.1201 0.4718 0.0127
-5.250 0.2741 0.04660 0.04173 -0.1262 0.4717 0.0125
-5.000 0.2837 0.02407 0.01776 -0.1446 0.4716 0.0106
-4.750 0.3116 0.02215 0.01550 -0.1458 0.4714 0.0107
-4.500 0.3400 0.02099 0.01412 -0.1465 0.4712 0.0109
-4.250 0.3688 0.02003 0.01297 -0.1471 0.4709 0.0111
-4.000 0.3978 0.01921 0.01197 -0.1475 0.4705 0.0113
-3.750 0.4268 0.01854 0.01115 -0.1479 0.4701 0.0116
-3.500 0.4560 0.01797 0.01044 -0.1482 0.4698 0.0120
-3.250 0.4852 0.01749 0.00984 -0.1485 0.4695 0.0123
-3.000 0.5144 0.01708 0.00934 -0.1487 0.4690 0.0126
-2.750 0.5436 0.01676 0.00895 -0.1490 0.4685 0.0129
-2.500 0.5729 0.01645 0.00859 -0.1492 0.4680 0.0131
-2.250 0.6021 0.01622 0.00835 -0.1496 0.4677 0.0135
-2.000 0.6312 0.01612 0.00824 -0.1498 0.4672 0.0141
-1.750 0.6605 0.01599 0.00810 -0.1501 0.4667 0.0148
-1.500 0.6898 0.01587 0.00795 -0.1503 0.4661 0.0155
-1.250 0.7192 0.01574 0.00780 -0.1506 0.4656 0.0159
-1.000 0.7488 0.01561 0.00766 -0.1510 0.4651 0.0165
-0.750 0.7782 0.01556 0.00760 -0.1512 0.4646 0.0173
-0.500 0.8076 0.01551 0.00753 -0.1515 0.4641 0.0186
-0.250 0.8370 0.01545 0.00746 -0.1518 0.4634 0.0207
0.000 0.8664 0.01540 0.00740 -0.1521 0.4628 0.0247
0.250 0.8959 0.01536 0.00737 -0.1524 0.4621 0.0345
0.500 0.9256 0.01526 0.00736 -0.1528 0.4615 0.0688
0.750 0.9562 0.01494 0.00740 -0.1537 0.4608 0.2039
1.000 0.9866 0.01470 0.00752 -0.1546 0.4602 0.3630
1.250 1.0161 0.01468 0.00764 -0.1550 0.4595 0.4359
1.500 1.0455 0.01469 0.00784 -0.1555 0.4588 0.5217
1.750 1.0742 0.01474 0.00811 -0.1558 0.4580 0.6105
2.000 1.1022 0.01469 0.00824 -0.1559 0.4574 0.6757
2.250 1.1294 0.01467 0.00838 -0.1558 0.4567 0.7355
2.500 1.1548 0.01464 0.00854 -0.1553 0.4559 0.8035
2.750 1.1739 0.01455 0.00865 -0.1533 0.4551 0.8952
3.000 1.1996 0.01459 0.00873 -0.1529 0.4543 1.0000
3.250 1.2277 0.01475 0.00887 -0.1530 0.4534 1.0000
3.500 1.2557 0.01489 0.00900 -0.1532 0.4525 1.0000
3.750 1.2838 0.01501 0.00911 -0.1534 0.4515 1.0000
4.000 1.3118 0.01512 0.00921 -0.1536 0.4505 1.0000
4.250 1.3399 0.01524 0.00931 -0.1538 0.4496 1.0000
4.500 1.3680 0.01536 0.00941 -0.1540 0.4488 1.0000
4.750 1.3962 0.01547 0.00950 -0.1542 0.4480 1.0000
5.000 1.4244 0.01556 0.00958 -0.1544 0.4473 1.0000
5.250 1.4527 0.01564 0.00964 -0.1547 0.4465 1.0000
5.500 1.4811 0.01571 0.00968 -0.1550 0.4458 1.0000
5.750 1.5095 0.01580 0.00974 -0.1553 0.4450 1.0000
6.000 1.5362 0.01597 0.00993 -0.1553 0.4440 1.0000
6.250 1.5612 0.01618 0.01023 -0.1551 0.4427 1.0000
6.500 1.5865 0.01638 0.01049 -0.1550 0.4412 1.0000
6.750 1.6122 0.01655 0.01071 -0.1549 0.4397 1.0000
7.000 1.6381 0.01667 0.01087 -0.1549 0.4382 1.0000
7.250 1.6644 0.01674 0.01098 -0.1549 0.4367 1.0000
7.500 1.6910 0.01678 0.01104 -0.1549 0.4354 1.0000
7.750 1.7177 0.01680 0.01108 -0.1550 0.4342 1.0000
8.000 1.7444 0.01683 0.01112 -0.1551 0.4332 1.0000
8.250 1.7710 0.01684 0.01115 -0.1551 0.4322 1.0000
8.500 1.7941 0.01711 0.01151 -0.1548 0.4300 1.0000
8.750 1.8167 0.01737 0.01188 -0.1543 0.4269 1.0000
9.000 1.8410 0.01747 0.01204 -0.1541 0.4241 1.0000
9.250 1.8661 0.01747 0.01207 -0.1539 0.4218 1.0000
9.500 1.8917 0.01737 0.01199 -0.1538 0.4194 1.0000
9.750 1.9134 0.01764 0.01236 -0.1533 0.4144 1.0000
10.000 1.9376 0.01758 0.01233 -0.1530 0.4102 1.0000
10.250 1.9609 0.01755 0.01231 -0.1526 0.4067 1.0000
10.500 1.9818 0.01772 0.01252 -0.1518 0.4016 1.0000
10.750 2.0014 0.01778 0.01256 -0.1508 0.3965 1.0000
11.000 2.0162 0.01807 0.01287 -0.1491 0.3910 1.0000
11.250 2.0264 0.01848 0.01328 -0.1467 0.3857 1.0000
11.500 2.0341 0.01903 0.01384 -0.1440 0.3812 1.0000
11.750 2.0408 0.01977 0.01464 -0.1415 0.3764 1.0000
12.000 2.0403 0.02081 0.01571 -0.1382 0.3713 1.0000
12.250 2.0352 0.02228 0.01723 -0.1349 0.3665 1.0000
12.500 2.0179 0.02487 0.01990 -0.1315 0.3605 1.0000
12.750 1.9707 0.03104 0.02617 -0.1286 0.3536 1.0000
13.000 1.8880 0.04169 0.03692 -0.1260 0.3429 1.0000
13.250 1.8376 0.04916 0.04446 -0.1242 0.3347 1.0000
13.500 1.8179 0.05348 0.04877 -0.1232 0.3285 1.0000
13.750 1.8001 0.05796 0.05333 -0.1226 0.3227 1.0000
14.000 1.7924 0.06147 0.05686 -0.1222 0.3172 1.0000
14.250 1.7926 0.06413 0.05952 -0.1220 0.3127 1.0000
14.500 1.7848 0.06794 0.06340 -0.1219 0.3071 1.0000
14.750 1.7851 0.07072 0.06618 -0.1218 0.3017 1.0000
15.000 1.7833 0.07386 0.06935 -0.1218 0.2964 1.0000
15.250 1.7810 0.07713 0.07267 -0.1219 0.2906 1.0000
15.500 1.7849 0.07956 0.07508 -0.1220 0.2855 1.0000
15.750 1.7852 0.08258 0.07818 -0.1222 0.2802 1.0000
16.000 1.7833 0.08588 0.08150 -0.1224 0.2741 1.0000
16.250 1.7845 0.08880 0.08444 -0.1226 0.2685 1.0000
16.500 1.7840 0.09198 0.08765 -0.1230 0.2616 1.0000
16.750 1.7845 0.09504 0.09071 -0.1233 0.2553 1.0000
17.000 1.7818 0.09858 0.09428 -0.1237 0.2485 1.0000
17.250 1.7818 0.10173 0.09743 -0.1242 0.2422 1.0000
17.500 1.7817 0.10496 0.10069 -0.1247 0.2353 1.0000
17.750 1.7776 0.10874 0.10447 -0.1253 0.2285 1.0000
18.000 1.7770 0.11208 0.10783 -0.1259 0.2218 1.0000
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Polar data table (+)
Polar graphs
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