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GeForce7
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Hello everyone. I'm currently doing a research on aircraft performance for my school project, which require me to design an airfoil to suit a specific mission. I'm not very familiar with the formulas used for calculating the aircraft performance and I would like to seek help from the forum.
Using the NASA FoilSim, I came out with an airfoil profile with a maximum coefficient of lift of 1.888. Using the lift equation, I calculated the minimum speed which I must fulfill in order to gain enough lift to counter the weight which is approximately 39.18 m/s.
Here are some requirements that my aircraft must fulfill:
Using the NASA FoilSim, I came out with an airfoil profile with a maximum coefficient of lift of 1.888. Using the lift equation, I calculated the minimum speed which I must fulfill in order to gain enough lift to counter the weight which is approximately 39.18 m/s.
V_stall=√(W/(CL_max×0.5×ρ×S))
V_stall=√(39240/(1.888×0.5×1.225×22.1))
V_stall=√(1535.425122)
V_stall=39.18 m∕s or 141.10 km/h
Assuming that the runway distance is 1800 m, how do I calculate the minimum runway distance in order for the aircraft to take-off? What can I do to reduce the distance needed to take-off while keeping the final velocity at 39.18 m/s? Is there a way to increase the acceleration of the aircraft while keeping the same final velocity?V_stall=√(39240/(1.888×0.5×1.225×22.1))
V_stall=√(1535.425122)
V_stall=39.18 m∕s or 141.10 km/h
Here are some requirements that my aircraft must fulfill:
- Maximum take-off weight of 4000 kg (39240 N)
- Take-off must take place at 1.25 times the stall speed, but less than 200 km/h
- Landing must take place at 1.3 times the stall speed, but less than 180 km/h
- Aircraft must take-off and land at a runway with a distance of 1800 m or less