SpainCub
Registered User
Hi all, I am in the mist of starting a new project, this will be a scratch build of a 2+2 and I have begun the undertaking of understanding fully the PA-12/14 design. In this quest, I´d go outside the box and experiment both mathematically and physically (like building and testing stuff) to validate some hypothesis that could lead into deviating from the original plans.
Currently, I am quantifying the structural design of the original wood wing, with the intention to later validate several possibilities and understand how they would influence the end product before the build. Stuff like new spars or changing chord lengths or airfoil like the Riblett 613.5, what happens when you add the VG´s… Yes, many have done this already, and the plane flies, but in avoiding fish tales and deadly mosquito bites out on the water, I prefer quantitative data. Yes, it could all fail, but I´ll take my chances on paper before getting in the air.
Ok, so in calculating the moment of inertia (I) for the wing, and integrating this into the EI of each spar, I am pondering if someone know either:
How to calculate the pitching moment (T) for the NACA 35B Airfoil and how to obtain a ration of distribution over the front spar and the rear spar of the wing?
Or, what is the load ratio of the front spar and the rear spar for this airfoil?
If understand correctly, the distance between the spars is maintained along the PA-18-12-14, meaning that the arm will be the same for the pitching moment.
Regards, Hi all, I am in the mist of starting a new project, this will be a scratch build of a 2+2 and I have begun the undertaking of understanding fully the PA-12/14 design. In this quest, I´d go outside the box and experiment both mathematically and physically (like building and testing stuff) to validate some hypothesis that could lead into deviating from the original plans.
Currently, I am quantifying the structural design of the original wood wing, with the intention to later validate several possibilities and understand how they would influence the end product before the build. Stuff like new spars or changing chord lengths or airfoil like the Riblett 613.5, what happens when you add the VG´s… Yes, many have done this already, and the plane flies, but in avoiding fish tales and deadly mosquito bites out on the water, I prefer quantitative data. Yes, it could all fail, but I´ll take my chances on paper before getting in the air.
Ok, so in calculating the moment of inertia (I) for the wing, and integrating this into the EI of each spar, I am pondering if someone know either:
How to calculate the pitching moment (T) for the NACA 35B Airfoil and how to obtain a ration of distribution over the front spar and the rear spar of the wing?
Or, what is the load ratio of the front spar and the rear spar for this airfoil or wing?
If understand correctly, the distance between the spars is maintained along the PA-18-12-14, meaning that the arm will be the same for the pitching moment.
Regards,
Currently, I am quantifying the structural design of the original wood wing, with the intention to later validate several possibilities and understand how they would influence the end product before the build. Stuff like new spars or changing chord lengths or airfoil like the Riblett 613.5, what happens when you add the VG´s… Yes, many have done this already, and the plane flies, but in avoiding fish tales and deadly mosquito bites out on the water, I prefer quantitative data. Yes, it could all fail, but I´ll take my chances on paper before getting in the air.
Ok, so in calculating the moment of inertia (I) for the wing, and integrating this into the EI of each spar, I am pondering if someone know either:
How to calculate the pitching moment (T) for the NACA 35B Airfoil and how to obtain a ration of distribution over the front spar and the rear spar of the wing?
Or, what is the load ratio of the front spar and the rear spar for this airfoil?
If understand correctly, the distance between the spars is maintained along the PA-18-12-14, meaning that the arm will be the same for the pitching moment.
Regards, Hi all, I am in the mist of starting a new project, this will be a scratch build of a 2+2 and I have begun the undertaking of understanding fully the PA-12/14 design. In this quest, I´d go outside the box and experiment both mathematically and physically (like building and testing stuff) to validate some hypothesis that could lead into deviating from the original plans.
Currently, I am quantifying the structural design of the original wood wing, with the intention to later validate several possibilities and understand how they would influence the end product before the build. Stuff like new spars or changing chord lengths or airfoil like the Riblett 613.5, what happens when you add the VG´s… Yes, many have done this already, and the plane flies, but in avoiding fish tales and deadly mosquito bites out on the water, I prefer quantitative data. Yes, it could all fail, but I´ll take my chances on paper before getting in the air.
Ok, so in calculating the moment of inertia (I) for the wing, and integrating this into the EI of each spar, I am pondering if someone know either:
How to calculate the pitching moment (T) for the NACA 35B Airfoil and how to obtain a ration of distribution over the front spar and the rear spar of the wing?
Or, what is the load ratio of the front spar and the rear spar for this airfoil or wing?
If understand correctly, the distance between the spars is maintained along the PA-18-12-14, meaning that the arm will be the same for the pitching moment.
Regards,
