S4158 (s4158-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4158 (s4158-il) Reynolds number: 50,000 Max Cl/Cd: 32.66 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4158-il-50000-n5.txt Download as CSV file: xf-s4158-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4158
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3642 0.11437 0.10803 -0.0347 1.0000 0.1103
-9.000 -0.3724 0.11254 0.10627 -0.0333 1.0000 0.1113
-8.750 -0.3813 0.11063 0.10443 -0.0321 1.0000 0.1118
-8.500 -0.2892 0.09301 0.08703 -0.0466 0.9812 0.0593
-8.250 -0.3935 0.09940 0.09319 -0.0422 0.9908 0.0605
-8.000 -0.3828 0.09574 0.08953 -0.0425 0.9873 0.0577
-7.750 -0.3806 0.09195 0.08576 -0.0453 0.9828 0.0555
-7.250 -0.3897 0.07963 0.07332 -0.0593 0.9692 0.0485
-7.000 -0.3844 0.07609 0.06975 -0.0603 0.9645 0.0479
-6.750 -0.3755 0.07200 0.06558 -0.0628 0.9601 0.0472
-6.500 -0.3701 0.06807 0.06153 -0.0644 0.9554 0.0466
-6.250 -0.3638 0.06406 0.05735 -0.0659 0.9502 0.0459
-6.000 -0.3511 0.05954 0.05256 -0.0684 0.9460 0.0454
-5.750 -0.3431 0.05586 0.04860 -0.0687 0.9411 0.0449
-5.500 -0.3302 0.05214 0.04451 -0.0694 0.9363 0.0447
-5.250 -0.3103 0.04850 0.04037 -0.0707 0.9326 0.0454
-5.000 -0.2943 0.04546 0.03678 -0.0703 0.9283 0.0470
-4.750 -0.2758 0.04285 0.03356 -0.0698 0.9237 0.0482
-4.500 -0.2513 0.04031 0.03051 -0.0701 0.9202 0.0495
-4.250 -0.2227 0.03810 0.02797 -0.0710 0.9174 0.0509
-4.000 -0.2053 0.03660 0.02619 -0.0695 0.9125 0.0524
-3.750 -0.1798 0.03513 0.02440 -0.0692 0.9085 0.0548
-3.500 -0.1494 0.03386 0.02276 -0.0696 0.9053 0.0593
-3.250 -0.1231 0.03285 0.02159 -0.0695 0.9015 0.0661
-3.000 -0.1008 0.03200 0.02050 -0.0684 0.8967 0.0735
-2.750 -0.0712 0.03121 0.01958 -0.0688 0.8928 0.0886
-2.500 -0.0380 0.03039 0.01876 -0.0700 0.8897 0.1168
-2.250 -0.0195 0.02968 0.01822 -0.0687 0.8841 0.1563
-2.000 0.0067 0.02861 0.01778 -0.0691 0.8797 0.2671
-1.750 0.0298 0.02726 0.01784 -0.0681 0.8762 0.5668
-1.500 0.1117 0.02670 0.01776 -0.0769 0.8762 1.0000
-1.250 0.1260 0.02702 0.01775 -0.0749 0.8689 1.0000
-1.000 0.1539 0.02735 0.01773 -0.0753 0.8636 1.0000
-0.750 0.1758 0.02771 0.01781 -0.0746 0.8574 1.0000
-0.500 0.1986 0.02807 0.01790 -0.0741 0.8508 1.0000
-0.250 0.2334 0.02843 0.01800 -0.0755 0.8465 1.0000
0.000 0.2452 0.02883 0.01823 -0.0731 0.8377 1.0000
0.250 0.2794 0.02919 0.01838 -0.0744 0.8330 1.0000
0.500 0.2929 0.02962 0.01866 -0.0723 0.8240 1.0000
0.750 0.3264 0.02996 0.01885 -0.0735 0.8189 1.0000
1.000 0.3410 0.03041 0.01919 -0.0715 0.8097 1.0000
1.250 0.3750 0.03072 0.01938 -0.0727 0.8044 1.0000
1.750 0.4244 0.03145 0.01995 -0.0720 0.7895 1.0000
2.000 0.4376 0.03193 0.02038 -0.0699 0.7791 1.0000
2.250 0.4665 0.03224 0.02064 -0.0701 0.7724 1.0000
2.500 0.4869 0.03263 0.02101 -0.0691 0.7632 1.0000
2.750 0.5061 0.03306 0.02142 -0.0680 0.7539 1.0000
3.000 0.5374 0.03326 0.02162 -0.0684 0.7473 1.0000
3.250 0.5530 0.03373 0.02210 -0.0668 0.7364 1.0000
3.500 0.5763 0.03406 0.02245 -0.0661 0.7277 1.0000
3.750 0.6040 0.03423 0.02268 -0.0660 0.7196 1.0000
4.000 0.6209 0.03467 0.02316 -0.0645 0.7084 1.0000
4.250 0.6421 0.03499 0.02353 -0.0635 0.6981 1.0000
4.500 0.6748 0.03488 0.02351 -0.0638 0.6910 1.0000
4.750 0.6926 0.03525 0.02398 -0.0624 0.6790 1.0000
5.000 0.7127 0.03552 0.02433 -0.0612 0.6671 1.0000
5.250 0.7357 0.03561 0.02452 -0.0602 0.6558 1.0000
5.500 0.7727 0.03492 0.02397 -0.0603 0.6485 1.0000
5.750 0.7938 0.03492 0.02413 -0.0589 0.6355 1.0000
6.000 0.8163 0.03480 0.02414 -0.0576 0.6224 1.0000
6.250 0.8397 0.03459 0.02407 -0.0562 0.6092 1.0000
6.500 0.8647 0.03428 0.02391 -0.0549 0.5957 1.0000
6.750 0.8904 0.03390 0.02374 -0.0537 0.5816 1.0000
7.000 0.9168 0.03345 0.02346 -0.0524 0.5665 1.0000
7.250 0.9449 0.03289 0.02307 -0.0512 0.5503 1.0000
7.500 0.9713 0.03245 0.02278 -0.0498 0.5315 1.0000
7.750 0.9929 0.03234 0.02284 -0.0481 0.5090 1.0000
8.000 1.0161 0.03212 0.02272 -0.0465 0.4836 1.0000
8.250 1.0367 0.03207 0.02271 -0.0445 0.4536 1.0000
8.500 1.0539 0.03227 0.02285 -0.0423 0.4195 1.0000
8.750 1.0647 0.03298 0.02348 -0.0399 0.3839 1.0000
9.000 1.0729 0.03397 0.02439 -0.0374 0.3484 1.0000
9.250 1.0788 0.03521 0.02551 -0.0350 0.3138 1.0000
9.500 1.0828 0.03670 0.02688 -0.0327 0.2801 1.0000
9.750 1.0860 0.03837 0.02841 -0.0306 0.2492 1.0000
10.000 1.0881 0.04025 0.03015 -0.0286 0.2203 1.0000
10.250 1.0904 0.04225 0.03205 -0.0268 0.1947 1.0000
10.500 1.0923 0.04440 0.03407 -0.0251 0.1728 1.0000
10.750 1.0960 0.04656 0.03621 -0.0237 0.1531 1.0000
11.000 1.0996 0.04878 0.03843 -0.0223 0.1369 1.0000
11.250 1.1036 0.05104 0.04068 -0.0211 0.1228 1.0000
11.500 1.1105 0.05320 0.04288 -0.0199 0.1116 1.0000
11.750 1.1181 0.05537 0.04509 -0.0188 0.1021 1.0000
12.000 1.1240 0.05760 0.04730 -0.0178 0.0939 1.0000
12.250 1.1354 0.05973 0.04968 -0.0168 0.0862 1.0000
12.500 1.1469 0.06180 0.05173 -0.0159 0.0801 1.0000
12.750 1.1548 0.06435 0.05461 -0.0151 0.0743 1.0000
13.000 1.1642 0.06659 0.05688 -0.0144 0.0695 1.0000
13.250 1.1726 0.06965 0.06029 -0.0136 0.0658 1.0000
13.500 1.1733 0.07305 0.06400 -0.0132 0.0624 1.0000
13.750 1.1739 0.07623 0.06733 -0.0129 0.0595 1.0000
14.000 1.1783 0.07935 0.07048 -0.0126 0.0567 1.0000
14.250 1.1677 0.08427 0.07580 -0.0131 0.0556 1.0000
14.500 1.1542 0.08967 0.08155 -0.0141 0.0547 1.0000
14.750 1.1371 0.09577 0.08796 -0.0159 0.0542 1.0000
15.000 1.1169 0.10271 0.09517 -0.0187 0.0539 1.0000
15.250 1.0939 0.11070 0.10340 -0.0226 0.0540 1.0000
15.500 1.0674 0.12016 0.11305 -0.0278 0.0543 1.0000
15.750 1.0400 0.13096 0.12399 -0.0343 0.0550 1.0000
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Polar data table (+)
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