FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-158 AIRFOIL (fx63158-il) Reynolds number: 100,000 Max Cl/Cd: 47.53 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63158-il-100000.txt Download as CSV file: xf-fx63158-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-158 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3037 0.10531 0.10096 -0.0455 1.0000 0.1106
-9.250 -0.3149 0.10258 0.09834 -0.0459 1.0000 0.1147
-9.000 -0.3589 0.09959 0.09557 -0.0484 1.0000 0.1165
-8.750 -0.3286 0.09786 0.09386 -0.0430 1.0000 0.1212
-8.500 -0.3481 0.09676 0.09293 -0.0402 1.0000 0.1242
-8.250 -0.3933 0.09148 0.08781 -0.0510 0.9912 0.1276
-8.000 -0.3626 0.08743 0.08377 -0.0548 0.9843 0.1387
-7.750 -0.3355 0.08328 0.07961 -0.0585 0.9748 0.1497
-7.500 -0.3281 0.07759 0.07392 -0.0663 0.9600 0.1621
-6.000 -0.1919 0.03719 0.03008 -0.1103 0.8861 0.0713
-5.750 -0.1472 0.03343 0.02564 -0.1129 0.8786 0.0615
-5.500 -0.0982 0.03008 0.02200 -0.1167 0.8741 0.0602
-5.250 -0.0666 0.02799 0.01969 -0.1169 0.8618 0.0582
-5.000 -0.0262 0.02593 0.01729 -0.1178 0.8536 0.0551
-4.750 0.0095 0.02453 0.01576 -0.1181 0.8438 0.0542
-4.500 0.0401 0.02339 0.01463 -0.1177 0.8336 0.0545
-4.250 0.0733 0.02233 0.01363 -0.1181 0.8248 0.0559
-4.000 0.0975 0.02173 0.01299 -0.1174 0.8139 0.0582
-3.750 0.1323 0.02097 0.01207 -0.1188 0.8061 0.0628
-3.500 0.1557 0.02054 0.01160 -0.1183 0.7959 0.0728
-3.250 0.1788 0.01833 0.01179 -0.1188 0.7890 0.5183
-3.000 0.1838 0.02187 0.01545 -0.1087 0.7798 0.6728
-2.750 0.1961 0.02353 0.01699 -0.1015 0.7730 0.6983
-2.500 0.2110 0.02449 0.01783 -0.0969 0.7659 0.7193
-2.250 0.2263 0.02513 0.01836 -0.0928 0.7586 0.7367
-2.000 0.2516 0.02548 0.01851 -0.0905 0.7533 0.7524
-1.750 0.2601 0.02588 0.01889 -0.0858 0.7454 0.7675
-1.500 0.2813 0.02604 0.01892 -0.0832 0.7392 0.7840
-1.250 0.3041 0.02606 0.01880 -0.0816 0.7334 0.7976
-1.000 0.3149 0.02618 0.01888 -0.0787 0.7257 0.8102
-0.750 0.3397 0.02616 0.01872 -0.0776 0.7206 0.8238
-0.500 0.3599 0.02612 0.01862 -0.0756 0.7156 0.8358
-0.250 0.3675 0.02624 0.01873 -0.0724 0.7087 0.8461
0.000 0.3924 0.02615 0.01852 -0.0718 0.7035 0.8570
0.250 0.4130 0.02605 0.01836 -0.0705 0.6978 0.8649
0.500 0.4220 0.02618 0.01849 -0.0678 0.6907 0.8725
0.750 0.4513 0.02595 0.01814 -0.0683 0.6855 0.8789
1.000 0.4647 0.02606 0.01824 -0.0662 0.6790 0.8843
1.250 0.4800 0.02615 0.01831 -0.0648 0.6724 0.8889
1.500 0.5162 0.02592 0.01793 -0.0666 0.6671 0.8923
1.750 0.5193 0.02619 0.01827 -0.0631 0.6593 0.8965
2.000 0.5507 0.02588 0.01787 -0.0638 0.6523 0.9004
2.250 0.5728 0.02587 0.01782 -0.0632 0.6452 0.9045
2.500 0.5911 0.02595 0.01789 -0.0622 0.6374 0.9080
2.750 0.6347 0.02541 0.01719 -0.0647 0.6313 0.9110
3.000 0.6372 0.02579 0.01769 -0.0612 0.6229 0.9147
3.250 0.6741 0.02545 0.01726 -0.0629 0.6167 0.9170
3.500 0.6927 0.02567 0.01750 -0.0621 0.6096 0.9194
3.750 0.7175 0.02573 0.01757 -0.0622 0.6025 0.9215
4.000 0.7583 0.02547 0.01723 -0.0646 0.5977 0.9239
4.250 0.7638 0.02602 0.01793 -0.0618 0.5904 0.9275
4.500 0.7879 0.02608 0.01802 -0.0616 0.5847 0.9314
4.750 0.8250 0.02596 0.01785 -0.0634 0.5808 0.9344
5.000 0.8342 0.02672 0.01879 -0.0616 0.5737 0.9368
5.250 0.8609 0.02699 0.01911 -0.0622 0.5681 0.9387
5.500 0.8991 0.02697 0.01909 -0.0644 0.5642 0.9403
5.750 0.9107 0.02772 0.01999 -0.0629 0.5573 0.9427
6.000 0.9367 0.02792 0.02029 -0.0633 0.5512 0.9450
6.250 0.9781 0.02759 0.01995 -0.0656 0.5469 0.9476
6.500 0.9859 0.02852 0.02107 -0.0636 0.5391 0.9514
6.750 1.0177 0.02849 0.02112 -0.0647 0.5328 0.9542
7.000 1.0613 0.02798 0.02060 -0.0672 0.5274 0.9564
7.250 1.0687 0.02872 0.02155 -0.0651 0.5177 0.9602
7.500 1.1190 0.02779 0.02060 -0.0683 0.5118 0.9627
7.750 1.1238 0.02874 0.02180 -0.0660 0.5023 0.9675
8.000 1.1669 0.02822 0.02133 -0.0684 0.4964 0.9709
8.250 1.1820 0.02891 0.02225 -0.0676 0.4879 0.9773
8.500 1.2209 0.02859 0.02202 -0.0696 0.4808 0.9867
8.750 1.2448 0.02896 0.02258 -0.0700 0.4726 1.0000
9.000 1.2748 0.02898 0.02274 -0.0709 0.4640 1.0000
9.250 1.2963 0.02930 0.02323 -0.0707 0.4543 1.0000
9.500 1.3346 0.02868 0.02268 -0.0724 0.4443 1.0000
9.750 1.3419 0.02929 0.02352 -0.0703 0.4324 1.0000
10.000 1.3624 0.02932 0.02369 -0.0698 0.4201 1.0000
10.250 1.3868 0.02922 0.02368 -0.0698 0.4069 1.0000
10.500 1.4040 0.02954 0.02411 -0.0690 0.3924 1.0000
10.750 1.4089 0.03058 0.02533 -0.0672 0.3764 1.0000
11.000 1.4158 0.03162 0.02649 -0.0659 0.3591 1.0000
11.250 1.4227 0.03288 0.02781 -0.0648 0.3402 1.0000
11.500 1.4189 0.03511 0.03017 -0.0635 0.3183 1.0000
11.750 1.4159 0.03745 0.03243 -0.0624 0.2938 1.0000
12.000 1.4081 0.04052 0.03538 -0.0616 0.2681 1.0000
12.250 1.3942 0.04455 0.03936 -0.0613 0.2409 1.0000
12.500 1.3810 0.04873 0.04335 -0.0611 0.2166 1.0000
12.750 1.3669 0.05337 0.04791 -0.0614 0.1919 1.0000
13.000 1.3557 0.05763 0.05187 -0.0615 0.1748 1.0000
13.250 1.3499 0.06163 0.05583 -0.0618 0.1560 1.0000
13.500 1.3465 0.06555 0.05970 -0.0625 0.1423 1.0000
13.750 1.3483 0.06866 0.06260 -0.0627 0.1311 1.0000
14.000 1.3569 0.07104 0.06487 -0.0625 0.1193 1.0000
14.250 1.3641 0.07386 0.06776 -0.0629 0.1104 1.0000
14.500 1.3709 0.07673 0.07065 -0.0635 0.1036 1.0000
14.750 1.3799 0.07921 0.07302 -0.0642 0.0977 1.0000
15.000 1.3912 0.08152 0.07535 -0.0645 0.0916 1.0000
15.250 1.4090 0.08312 0.07691 -0.0643 0.0857 1.0000
15.500 1.4334 0.08403 0.07768 -0.0639 0.0797 1.0000
15.750 1.4306 0.08820 0.08222 -0.0652 0.0771 1.0000
16.000 1.4369 0.09124 0.08542 -0.0661 0.0738 1.0000
16.250 1.4435 0.09421 0.08850 -0.0670 0.0708 1.0000
16.500 1.4424 0.09824 0.09279 -0.0685 0.0684 1.0000
16.750 1.4505 0.10082 0.09539 -0.0695 0.0657 1.0000
17.000 1.4562 0.10401 0.09873 -0.0705 0.0635 1.0000
17.250 1.4553 0.10809 0.10305 -0.0721 0.0616 1.0000
17.500 1.4816 0.10833 0.10308 -0.0716 0.0578 1.0000
17.750 1.4665 0.11435 0.10949 -0.0744 0.0568 1.0000
18.000 1.4542 0.12018 0.11564 -0.0773 0.0554 1.0000
18.250 1.4724 0.12141 0.11670 -0.0773 0.0507 1.0000
18.500 1.4503 0.12863 0.12429 -0.0815 0.0500 1.0000
18.750 1.4287 0.13623 0.13223 -0.0861 0.0494 1.0000
19.000 1.4070 0.14427 0.14058 -0.0913 0.0490 1.0000
19.250 1.3843 0.15295 0.14955 -0.0971 0.0488 1.0000
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