FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 38-153 AIRFOIL (fx38153-il) Reynolds number: 100,000 Max Cl/Cd: 46.92 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx38153-il-100000.txt Download as CSV file: xf-fx38153-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 38-153 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5767 0.10152 0.09721 -0.0376 1.0001 0.1304
-9.000 -0.6151 0.09699 0.09271 -0.0379 1.0001 0.1308
-8.750 -0.6502 0.09374 0.08947 -0.0356 1.0001 0.1309
-8.500 -0.6838 0.09109 0.08682 -0.0320 1.0001 0.1308
-8.250 -0.7212 0.08810 0.08372 -0.0292 1.0001 0.1314
-8.000 -0.7636 0.08585 0.08117 -0.0257 1.0001 0.1323
-5.750 -0.6944 0.04448 0.03607 -0.0112 1.0001 0.0567
-5.500 -0.6742 0.04068 0.03225 -0.0105 1.0001 0.0541
-5.250 -0.6516 0.03794 0.02910 -0.0094 1.0001 0.0508
-5.000 -0.6270 0.03622 0.02672 -0.0079 1.0001 0.0479
-4.750 -0.6044 0.03486 0.02513 -0.0068 1.0001 0.0474
-4.500 -0.5820 0.03335 0.02350 -0.0057 1.0001 0.0473
-4.250 -0.5599 0.03209 0.02214 -0.0044 1.0001 0.0476
-4.000 -0.5388 0.03074 0.02086 -0.0032 1.0001 0.0487
-3.750 -0.5178 0.02980 0.02000 -0.0021 1.0001 0.0506
-3.500 -0.4963 0.02903 0.01926 -0.0013 1.0001 0.0536
-3.250 -0.4738 0.02820 0.01847 -0.0010 1.0001 0.0595
-3.000 -0.4488 0.02735 0.01767 -0.0013 1.0001 0.0742
-2.750 -0.4348 0.02462 0.01868 0.0024 1.0001 0.6358
-2.500 -0.4346 0.02694 0.02098 0.0109 1.0001 0.7706
-2.250 -0.4365 0.02859 0.02257 0.0193 1.0001 0.8025
-2.000 -0.4400 0.03003 0.02395 0.0280 1.0001 0.8325
-1.750 -0.4455 0.03115 0.02504 0.0374 1.0001 0.8624
-1.500 -0.4463 0.03192 0.02572 0.0459 1.0001 0.8930
-1.250 -0.2614 0.03595 0.02915 0.0218 1.0001 0.9587
-1.000 -0.2095 0.03630 0.02931 0.0158 1.0001 0.9703
-0.750 -0.1606 0.03667 0.02951 0.0099 0.9958 0.9759
-0.500 -0.0832 0.03740 0.03005 -0.0015 0.9829 0.9796
-0.250 -0.0257 0.03771 0.03021 -0.0089 0.9699 0.9828
0.000 0.0246 0.03775 0.03015 -0.0147 0.9571 0.9855
0.250 0.0723 0.03777 0.03009 -0.0201 0.9455 0.9885
0.500 0.1213 0.03800 0.03026 -0.0256 0.9376 0.9915
0.750 0.1620 0.03797 0.03019 -0.0295 0.9273 0.9945
1.000 0.2082 0.03788 0.03008 -0.0343 0.9158 0.9974
1.250 0.2687 0.03792 0.03009 -0.0416 0.9094 0.9999
1.500 0.2918 0.03769 0.02986 -0.0417 0.8963 0.9999
1.750 0.3145 0.03756 0.02975 -0.0418 0.8842 0.9999
2.000 0.3436 0.03738 0.02958 -0.0429 0.8734 0.9999
2.250 0.3883 0.03697 0.02919 -0.0465 0.8655 0.9999
2.500 0.4129 0.03659 0.02884 -0.0465 0.8527 0.9999
2.750 0.4385 0.03620 0.02849 -0.0466 0.8403 0.9999
3.000 0.4683 0.03574 0.02809 -0.0473 0.8295 0.9999
3.250 0.5121 0.03495 0.02735 -0.0502 0.8219 0.9999
3.500 0.5381 0.03426 0.02673 -0.0499 0.8088 0.9999
3.750 0.5671 0.03343 0.02598 -0.0499 0.7960 0.9999
4.000 0.6199 0.03190 0.02455 -0.0536 0.7898 0.9999
4.250 0.6474 0.03096 0.02370 -0.0531 0.7772 0.9999
4.500 0.6719 0.03008 0.02292 -0.0520 0.7641 0.9999
4.750 0.7004 0.02897 0.02192 -0.0514 0.7520 0.9999
5.000 0.7514 0.02700 0.02010 -0.0542 0.7459 0.9999
5.250 0.7818 0.02574 0.01894 -0.0537 0.7315 0.9999
5.500 0.8184 0.02441 0.01772 -0.0543 0.7159 0.9999
5.750 0.8546 0.02325 0.01667 -0.0549 0.6952 0.9999
6.000 0.9109 0.02186 0.01532 -0.0590 0.6661 0.9999
6.250 0.9498 0.02129 0.01472 -0.0606 0.6273 0.9999
6.500 0.9841 0.02111 0.01437 -0.0614 0.5822 0.9999
6.750 0.9995 0.02130 0.01434 -0.0589 0.5398 0.9999
7.000 0.9988 0.02165 0.01455 -0.0536 0.5041 0.9999
7.250 0.9967 0.02204 0.01478 -0.0481 0.4705 0.9999
7.500 0.9920 0.02247 0.01506 -0.0423 0.4396 0.9999
7.750 0.9877 0.02292 0.01535 -0.0368 0.4113 0.9999
8.000 0.9822 0.02337 0.01570 -0.0311 0.3847 0.9999
8.250 0.9772 0.02382 0.01606 -0.0256 0.3605 0.9999
8.500 0.9738 0.02430 0.01643 -0.0205 0.3386 0.9999
8.750 0.9716 0.02478 0.01683 -0.0157 0.3183 0.9999
9.000 0.9699 0.02524 0.01727 -0.0111 0.2995 0.9999
9.250 0.9705 0.02576 0.01772 -0.0070 0.2822 0.9999
9.500 0.9740 0.02636 0.01830 -0.0036 0.2647 0.9999
9.750 0.9807 0.02705 0.01898 -0.0010 0.2474 0.9999
10.000 0.9898 0.02788 0.01977 0.0010 0.2305 0.9999
10.250 1.0010 0.02881 0.02069 0.0026 0.2140 0.9999
10.500 1.0134 0.02979 0.02170 0.0038 0.1985 0.9999
10.750 1.0254 0.03086 0.02278 0.0050 0.1838 0.9999
11.000 1.0376 0.03204 0.02400 0.0060 0.1691 0.9999
11.250 1.0476 0.03332 0.02536 0.0072 0.1542 0.9999
11.500 1.0557 0.03470 0.02678 0.0084 0.1399 0.9999
11.750 1.0638 0.03628 0.02838 0.0095 0.1258 0.9999
12.000 1.0711 0.03804 0.03020 0.0107 0.1117 0.9999
12.250 1.0788 0.03990 0.03211 0.0117 0.0996 0.9999
12.500 1.0889 0.04193 0.03418 0.0126 0.0892 0.9999
12.750 1.1046 0.04400 0.03619 0.0129 0.0811 0.9999
13.000 1.1183 0.04604 0.03847 0.0134 0.0753 0.9999
13.250 1.1457 0.04809 0.04034 0.0127 0.0706 0.9999
13.500 1.1593 0.05052 0.04315 0.0132 0.0683 0.9999
13.750 1.1724 0.05317 0.04610 0.0136 0.0663 0.9999
14.000 1.1817 0.05603 0.04926 0.0141 0.0648 0.9999
14.250 1.1867 0.05910 0.05261 0.0147 0.0638 0.9999
14.500 1.1874 0.06243 0.05623 0.0154 0.0630 0.9999
14.750 1.1838 0.06597 0.06004 0.0161 0.0624 0.9999
15.000 1.1771 0.06976 0.06408 0.0165 0.0618 0.9999
15.250 1.1682 0.07380 0.06836 0.0167 0.0613 0.9999
15.500 1.1540 0.07840 0.07321 0.0165 0.0609 0.9999
15.750 1.1283 0.08413 0.07927 0.0156 0.0611 0.9999
16.000 1.0761 0.09363 0.08924 0.0122 0.0625 0.9999
16.250 0.9787 0.11302 0.10911 0.0006 0.0661 0.9999
16.500 0.8992 0.13550 0.13169 -0.0140 0.0690 0.9999
16.750 0.8762 0.14748 0.14365 -0.0207 0.0703 0.9999
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