JN-153 AIRFOIL (jn153-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: JN-153 AIRFOIL (jn153-il) Reynolds number: 500,000 Max Cl/Cd: 98.81 at α=11.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-jn153-il-500000.txt Download as CSV file: xf-jn153-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.1668 0.10396 0.09910 -0.0944 0.5036 0.0180
-9.750 0.1750 0.10153 0.09669 -0.0955 0.5035 0.0183
-9.500 0.1654 0.09782 0.09304 -0.0992 0.5035 0.0190
-9.250 0.1774 0.09532 0.09056 -0.0993 0.5034 0.0191
-9.000 0.1906 0.09316 0.08842 -0.0995 0.5032 0.0192
-8.750 0.2025 0.09118 0.08645 -0.0997 0.5029 0.0195
-8.500 0.2116 0.08906 0.08436 -0.1005 0.5026 0.0198
-8.250 0.2200 0.08688 0.08221 -0.1012 0.5024 0.0202
-8.000 0.2275 0.08463 0.08000 -0.1021 0.5022 0.0204
-7.750 0.2348 0.08239 0.07779 -0.1030 0.5019 0.0208
-7.500 0.2408 0.07999 0.07543 -0.1040 0.5018 0.0215
-7.250 0.2313 0.07569 0.07120 -0.1080 0.5017 0.0223
-7.000 0.2381 0.07323 0.06878 -0.1083 0.5014 0.0224
-6.750 0.2492 0.07161 0.06719 -0.1079 0.5011 0.0226
-6.500 0.2572 0.06973 0.06535 -0.1081 0.5007 0.0228
-6.250 0.2634 0.06786 0.06352 -0.1082 0.5002 0.0231
-6.000 0.2647 0.06621 0.06192 -0.1080 0.4998 0.0234
-5.750 0.2685 0.06414 0.05990 -0.1092 0.4995 0.0236
-5.500 0.2755 0.06162 0.05742 -0.1116 0.4992 0.0241
-5.250 0.2848 0.05861 0.05444 -0.1153 0.4989 0.0247
-5.000 0.2988 0.04610 0.04165 -0.1346 0.4987 0.0260
-4.750 0.3162 0.04480 0.04041 -0.1349 0.4982 0.0262
-4.500 0.3355 0.04329 0.03888 -0.1359 0.4977 0.0265
-4.250 0.3571 0.04132 0.03684 -0.1377 0.4970 0.0271
-4.000 0.3869 0.03554 0.03040 -0.1433 0.4965 0.0300
-3.750 0.4106 0.03409 0.02899 -0.1440 0.4958 0.0304
-3.500 0.4360 0.03293 0.02779 -0.1448 0.4952 0.0310
-3.250 0.4671 0.03051 0.02487 -0.1467 0.4947 0.0346
-3.000 0.4935 0.02940 0.02376 -0.1473 0.4941 0.0352
-2.750 0.5313 0.02391 0.01721 -0.1488 0.4936 0.0227
-2.500 0.5606 0.02289 0.01606 -0.1491 0.4929 0.0217
-2.250 0.5904 0.02198 0.01496 -0.1493 0.4922 0.0216
-2.000 0.6198 0.02141 0.01423 -0.1495 0.4915 0.0219
-1.750 0.6489 0.02104 0.01375 -0.1497 0.4908 0.0221
-1.500 0.6776 0.02077 0.01342 -0.1498 0.4901 0.0225
-1.250 0.7054 0.02075 0.01341 -0.1501 0.4891 0.0236
-1.000 0.7309 0.02130 0.01398 -0.1499 0.4879 0.0249
-0.750 0.7597 0.02102 0.01371 -0.1501 0.4872 0.0256
-0.500 0.7885 0.02074 0.01347 -0.1503 0.4863 0.0265
-0.250 0.8170 0.02062 0.01339 -0.1505 0.4851 0.0282
0.000 0.8456 0.02057 0.01336 -0.1508 0.4839 0.0313
0.250 0.8744 0.02053 0.01336 -0.1510 0.4827 0.0407
0.500 0.9058 0.01991 0.01340 -0.1524 0.4814 0.2630
0.750 0.9353 0.01972 0.01362 -0.1531 0.4803 0.4265
1.000 0.9643 0.01967 0.01378 -0.1534 0.4793 0.5146
1.250 0.9935 0.01958 0.01388 -0.1537 0.4784 0.6004
1.500 1.0219 0.01939 0.01398 -0.1538 0.4775 0.7191
1.750 1.0353 0.01900 0.01402 -0.1503 0.4766 0.9120
2.000 1.0639 0.01905 0.01402 -0.1504 0.4758 1.0000
2.250 1.0933 0.01925 0.01413 -0.1508 0.4751 1.0000
2.500 1.1222 0.01952 0.01432 -0.1512 0.4742 1.0000
2.750 1.1495 0.02012 0.01485 -0.1513 0.4731 1.0000
3.000 1.1742 0.02053 0.01529 -0.1511 0.4716 1.0000
3.250 1.1998 0.02070 0.01549 -0.1509 0.4699 1.0000
3.500 1.2255 0.02097 0.01577 -0.1508 0.4682 1.0000
3.750 1.2520 0.02121 0.01601 -0.1509 0.4667 1.0000
4.000 1.2794 0.02139 0.01618 -0.1510 0.4655 1.0000
4.250 1.3074 0.02152 0.01627 -0.1512 0.4644 1.0000
4.500 1.3363 0.02157 0.01629 -0.1515 0.4634 1.0000
4.750 1.3653 0.02160 0.01627 -0.1518 0.4624 1.0000
5.000 1.3947 0.02159 0.01622 -0.1521 0.4615 1.0000
5.250 1.4242 0.02159 0.01618 -0.1526 0.4607 1.0000
5.500 1.4534 0.02167 0.01621 -0.1530 0.4599 1.0000
5.750 1.4819 0.02188 0.01639 -0.1533 0.4590 1.0000
6.000 1.5066 0.02239 0.01691 -0.1532 0.4576 1.0000
6.250 1.5261 0.02271 0.01735 -0.1522 0.4553 1.0000
6.500 1.5492 0.02296 0.01767 -0.1518 0.4532 1.0000
6.750 1.5752 0.02303 0.01776 -0.1518 0.4516 1.0000
7.000 1.6029 0.02300 0.01772 -0.1520 0.4503 1.0000
7.250 1.6310 0.02293 0.01765 -0.1522 0.4491 1.0000
7.500 1.6597 0.02286 0.01758 -0.1526 0.4482 1.0000
7.750 1.6889 0.02276 0.01746 -0.1530 0.4473 1.0000
8.000 1.7185 0.02264 0.01731 -0.1534 0.4465 1.0000
8.250 1.7485 0.02249 0.01715 -0.1540 0.4457 1.0000
8.500 1.7796 0.02240 0.01700 -0.1547 0.4447 1.0000
8.750 1.7912 0.02289 0.01769 -0.1527 0.4415 1.0000
9.000 1.8115 0.02304 0.01793 -0.1519 0.4389 1.0000
9.250 1.8375 0.02288 0.01780 -0.1518 0.4371 1.0000
9.500 1.8665 0.02249 0.01741 -0.1521 0.4357 1.0000
9.750 1.8965 0.02199 0.01690 -0.1526 0.4344 1.0000
10.000 1.9268 0.02151 0.01641 -0.1531 0.4332 1.0000
10.250 1.9571 0.02114 0.01602 -0.1536 0.4321 1.0000
10.500 1.9655 0.02169 0.01676 -0.1512 0.4282 1.0000
10.750 1.9846 0.02166 0.01681 -0.1501 0.4252 1.0000
11.000 2.0084 0.02140 0.01659 -0.1497 0.4230 1.0000
11.250 2.0333 0.02110 0.01631 -0.1494 0.4212 1.0000
11.500 2.0583 0.02083 0.01605 -0.1492 0.4196 1.0000
11.750 2.0569 0.02160 0.01698 -0.1452 0.4151 1.0000
12.000 2.0695 0.02176 0.01721 -0.1432 0.4118 1.0000
12.250 2.0888 0.02164 0.01710 -0.1422 0.4091 1.0000
12.500 2.0981 0.02207 0.01758 -0.1400 0.4054 1.0000
12.750 2.0990 0.02300 0.01859 -0.1371 0.4008 1.0000
13.000 2.1079 0.02356 0.01916 -0.1354 0.3971 1.0000
13.250 2.0994 0.02537 0.02103 -0.1325 0.3922 1.0000
13.500 2.0781 0.02858 0.02429 -0.1297 0.3860 1.0000
13.750 2.0342 0.03467 0.03044 -0.1274 0.3779 1.0000
14.000 2.0145 0.03880 0.03456 -0.1261 0.3709 1.0000
14.250 1.9481 0.04784 0.04367 -0.1241 0.3602 1.0000
14.500 1.9679 0.04802 0.04380 -0.1238 0.3565 1.0000
14.750 1.9126 0.05629 0.05217 -0.1225 0.3466 1.0000
15.000 1.9323 0.05656 0.05239 -0.1223 0.3430 1.0000
15.250 1.8948 0.06350 0.05944 -0.1219 0.3346 1.0000
15.500 1.9063 0.06480 0.06072 -0.1217 0.3302 1.0000
15.750 1.8971 0.06865 0.06462 -0.1217 0.3242 1.0000
16.000 1.8886 0.07252 0.06852 -0.1217 0.3177 1.0000
16.250 1.9120 0.07234 0.06828 -0.1216 0.3138 1.0000
16.500 1.8798 0.07942 0.07550 -0.1220 0.3052 1.0000
16.750 1.8949 0.08031 0.07635 -0.1220 0.3006 1.0000
17.000 1.8754 0.08593 0.08207 -0.1225 0.2928 1.0000
17.250 1.8834 0.08781 0.08392 -0.1226 0.2871 1.0000
17.500 1.8695 0.09278 0.08898 -0.1232 0.2792 1.0000
17.750 1.8746 0.09509 0.09124 -0.1235 0.2728 1.0000
18.000 1.8660 0.09941 0.09564 -0.1241 0.2652 1.0000
18.250 1.8690 0.10203 0.09821 -0.1244 0.2585 1.0000
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Polar data table (+)
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