US1000ROOT (us1000root-il)
US1000ROOT - Great Planes R/C Ultra-Sport 1000 airfoil
| Details | Dat file | Parser | |
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(us1000root-il) US1000ROOT Great Planes R/C Ultra-Sport 1000 airfoil Max thickness 18.6% at 27.1% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
US1000ROOT 1.000000 0.000048 0.997540 0.000934 0.990700 0.003091 0.980370 0.005675 0.966980 0.008199 0.950440 0.010556 0.930640 0.012925 0.907750 0.015624 0.882020 0.018977 0.853700 0.023180 0.823090 0.028227 0.790480 0.033917 0.756160 0.039949 0.720430 0.046051 0.683590 0.052050 0.645940 0.057871 0.607780 0.063459 0.569370 0.068740 0.530990 0.073629 0.492650 0.078104 0.454350 0.082158 0.416380 0.085731 0.378870 0.088728 0.342040 0.090998 0.306090 0.092399 0.271200 0.092834 0.237600 0.092209 0.205490 0.090384 0.175040 0.087120 0.146480 0.082245 0.119990 0.075919 0.095760 0.068432 0.073950 0.059904 0.054680 0.050077 0.038110 0.039234 0.024330 0.028729 0.013380 0.019477 0.005480 0.010894 0.000980 0.003382 0.000000 0.001306 0.000980 -.003382 0.005480 -.010894 0.013380 -.019477 0.024330 -.028729 0.038110 -.039234 0.054680 -.050077 0.073950 -.059904 0.095760 -.068432 0.119990 -.075919 0.146480 -.082245 0.175040 -.087120 0.205490 -.090384 0.237600 -.092209 0.271200 -.092834 0.306090 -.092399 0.342040 -.090998 0.378870 -.088728 0.416380 -.085731 0.454350 -.082158 0.492650 -.078104 0.530990 -.073629 0.569370 -.068740 0.607780 -.063459 0.645940 -.057871 0.683590 -.052050 0.720430 -.046051 0.756160 -.039949 0.790480 -.033917 0.823090 -.028227 0.853700 -.023180 0.882020 -.018977 0.907750 -.015624 0.930640 -.012925 0.950440 -.010556 0.966980 -.008199 0.980370 -.005675 0.990700 -.003091 0.997540 -.000934 1.000000 -.000048 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for US1000ROOT (us1000root-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| us1000root-il | 50,000 | 9 | 19 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 50,000 | 5 | 24.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 100,000 | 9 | 38.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 100,000 | 5 | 38.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 200,000 | 9 | 49.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 200,000 | 5 | 44.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 500,000 | 9 | 49.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 500,000 | 5 | 43.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 1,000,000 | 9 | 52.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 1,000,000 | 5 | 45.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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