S4233-136-84 (s4233-il)
S4233-136-84 - Selig S4233 low Reynolds number airfoil
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(s4233-il) S4233-136-84 Selig S4233 low Reynolds number airfoil Max thickness 13.6% at 34.9% chord. Max camber 2.7% at 48.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S4233-136-84 1.00000 0.0 0.99650 0.00042 0.98618 0.00186 0.96949 0.00461 0.94698 0.00881 0.91927 0.01444 0.88703 0.02138 0.85089 0.02939 0.81146 0.03817 0.76933 0.04740 0.72503 0.05674 0.67908 0.06585 0.63196 0.07443 0.58414 0.08218 0.53609 0.08881 0.48820 0.09405 0.44078 0.09770 0.39411 0.09969 0.34856 0.10001 0.30450 0.09867 0.26227 0.09570 0.22218 0.09118 0.18457 0.08523 0.14971 0.07798 0.11788 0.06963 0.08934 0.06040 0.06437 0.05055 0.04319 0.04033 0.02602 0.02999 0.01300 0.01986 0.00433 0.01032 0.00017 0.00183 0.00156 -0.00488 0.00916 -0.01058 0.02237 -0.01621 0.04069 -0.02144 0.06388 -0.02609 0.09171 -0.03003 0.12392 -0.03321 0.16018 -0.03559 0.20013 -0.03714 0.24338 -0.03782 0.28950 -0.03768 0.33802 -0.03672 0.38846 -0.03497 0.44032 -0.03249 0.49308 -0.02934 0.54626 -0.02558 0.59939 -0.02139 0.65200 -0.01703 0.70342 -0.01286 0.75290 -0.00910 0.79967 -0.00592 0.84300 -0.00337 0.88220 -0.00149 0.91665 -0.00026 0.94576 0.00040 0.96905 0.00058 0.98608 0.00043 0.99650 0.00014 1.00001 -0.00000 |
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Polars for S4233-136-84 (s4233-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4233-il | 50,000 | 9 | 22.6 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 50,000 | 5 | 26.1 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4233-il | 100,000 | 9 | 52.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 100,000 | 5 | 54.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4233-il | 200,000 | 9 | 77.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 200,000 | 5 | 77 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4233-il | 500,000 | 9 | 111.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 500,000 | 5 | 104.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4233-il | 1,000,000 | 9 | 136 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 1,000,000 | 5 | 121.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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