stanislavz
Well-Known Member
Hi ! As i did mentioned before - i am "toying" with composide software. Firstly - to anwer my self of some composite design questions - most of them in style of do we on tail section of fuselage more tahn three layers of fibre (minimum to handle "pencil load at hangar") and at which orientation. Same for wing - nose/skin/ribs. I do have all sort of books and excel spreadsheets to calculate at various aircraft parts. But as more i go deeper, as more it feels like speak with some of our local designer - you calculate it first or second time, and just know the numbers.
But ! As more i got into it, as more i see it for classic topology (non canard/tandem wing) - its goes to matrix like this.
For EU countries, you have mtow of 475 kg and max speed of ~150 km/h (tractor/pusher dirty airframe V strut wing), ~200 km/h (struted fabric wing, faired fuselage, icarus c42, skyranger) 250-300 km/h - perfectly faired high/low wing with rigid shell, strut less.
Same for 600 kg mtow plus ~ 400km/h dive speed - Tailwinds/ glasair etc - retractable landing gear, perfect aerodynamic.
Could others post their data and suggest minimum set of loads ?
But ! As more i got into it, as more i see it for classic topology (non canard/tandem wing) - its goes to matrix like this.
For EU countries, you have mtow of 475 kg and max speed of ~150 km/h (tractor/pusher dirty airframe V strut wing), ~200 km/h (struted fabric wing, faired fuselage, icarus c42, skyranger) 250-300 km/h - perfectly faired high/low wing with rigid shell, strut less.
Same for 600 kg mtow plus ~ 400km/h dive speed - Tailwinds/ glasair etc - retractable landing gear, perfect aerodynamic.
Could others post their data and suggest minimum set of loads ?
