CESSNA 172 With Wipline 2350 Floats Assignment

I have a project that i created, i attached wipline 2350 floats to cessna 172. I have done some modifications on floats assembly - mainly for the weight. I need to calculate take off and landing distances up to 15 m obstacle. after that I have to check strength calculations of nodes: there are a few places that has to be checked, if the whole construction will withstand. I have a 3D Solidworks assembly that can be shared for the assignment.

I need all the necessary calculations for take-off and landing distances. All the forces that affect the final value must be calculated and presented in the final file with explanations.

There are some data for the calculation, there are more values here than may be needed for the calculations

Weight - 1036.5 kg
Wing area – 16.2 m2
Lift coefficient CL

There is CD drag coefficient, and CL for comparison.

Generated thrust.

I know that take off distance from water should be approx 730meters. landing distance about 409meters. And it is landing/take off over 15 meters obstacle. I need to show those calculations and all in between.

strength calculations of nodes: there are a few places that has to be checked, if the whole construction will withstand. I have a 3D Solidworks assembly that can be shared for the assignment. calculations to be carried out in accordance with CS23

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