AIRFOIL 3024 9.84% (s3024-il)
AIRFOIL 3024 9.84% - Selig S3024 low Reynolds number airfoil
| Details | Dat file | Parser | |
|
(s3024-il) AIRFOIL 3024 9.84% Selig S3024 low Reynolds number airfoil Max thickness 9.8% at 30.7% chord. Max camber 3% at 44.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AIRFOIL 3024 9.84% 1.00000 0.0 0.99662 0.00036 0.98664 0.00162 0.97044 0.00407 0.94859 0.00787 0.92168 0.01299 0.89037 0.01929 0.85527 0.02649 0.81693 0.03428 0.77588 0.04230 0.73258 0.05022 0.68743 0.05770 0.64084 0.06450 0.59316 0.07038 0.54473 0.07523 0.49598 0.07903 0.44741 0.08173 0.39947 0.08324 0.35259 0.08353 0.30720 0.08260 0.26372 0.08047 0.22258 0.07719 0.18416 0.07278 0.14880 0.06727 0.11676 0.06075 0.08828 0.05334 0.06357 0.04520 0.04278 0.03651 0.02601 0.02751 0.01334 0.01848 0.00476 0.00982 0.00032 0.00221 0.00111 -0.00352 0.00783 -0.00794 0.02011 -0.01179 0.03773 -0.01487 0.06053 -0.01715 0.08834 -0.01862 0.12093 -0.01933 0.15799 -0.01936 0.19918 -0.01879 0.24406 -0.01774 0.29214 -0.01636 0.34284 -0.01475 0.39555 -0.01303 0.44962 -0.01127 0.50439 -0.00955 0.55919 -0.00790 0.61333 -0.00639 0.66617 -0.00503 0.71704 -0.00385 0.76531 -0.00285 0.81040 -0.00201 0.85176 -0.00134 0.88886 -0.00083 0.92122 -0.00041 0.94852 -0.00003 0.97047 0.00023 0.98666 0.00026 0.99663 0.00011 1.00001 0.00000 |
Dat file parser warnings
|
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for AIRFOIL 3024 9.84% (s3024-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s3024-il | 50,000 | 9 | 34.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 50,000 | 5 | 38.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 100,000 | 9 | 57.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 100,000 | 5 | 57.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 200,000 | 9 | 80.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 200,000 | 5 | 76.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 500,000 | 9 | 110.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 500,000 | 5 | 96.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 1,000,000 | 9 | 129 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 1,000,000 | 5 | 110.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||