Parametric Investigation of STOL Aircraft
Parametric Investigation of STOL Aircraft
- New search for: G. Gabrielli
- New search for: G. Gabrielli
The parametric investigation consists of the evaluation of the minimum take-off and landing lengths, as affected by some parameters (wing loading, maximum lift coefficient, engine thrust to aircraft A.U.W. ratio, thrust deflection angle), for a jet propelled STOL aircraft capable of complying with any other requirement of G.O.R. 2 (including mission profile, military loads, etc.). The take-off performances are evaluated under the basic assumptions that the take-off from the ground is obtained mainly through the aerodynamic lift of a wing provided with high lift devices and that the aircraft is mainly controlled during take-off by conventional aerodynamic means. Aircraft with geometrically similar wings are considered (that is, having identical wing sections, planform, sweep-back angle, etc.). The wing shape was selected. Aircraft powered by two different propulsion systems are considered and compared. The first propulsion system consists of a single high by-pass and medium compression ratio turbofan engine provided with swivelling propelling nozzles. The alternate is a composite system, consisting of a single medium by-pass and high compression ratio turbojet engine giving horizontal thrust and of two, or more, booster turbojets, to be used during take-off only, having a low compression ratio and provided with propelling nozzles which may be deflected downwards at different angles. Furthermore, in the most significant instances, the investigation covers the climb paths and the high speed manoeuvre boundaries and evaluates safety and operational flexibility factors. Author)
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Parametric Investigation of STOL Aircraft
1960
73 pages
Report
No indication
English