Last edited by Gagar
Thursday, February 6, 2020 | History

1 edition of Application of powered high lift systems to STOL aircraft design found in the catalog.

Application of powered high lift systems to STOL aircraft design

Frederick Donald Ameel

Application of powered high lift systems to STOL aircraft design

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  • 17 Currently reading

Published by Naval Postgraduate School in Monterey, California .
Written in English

    Subjects:
  • Aeronautics

  • Edition Notes

    ContributionsNaval Postgraduate School (U.S.)
    The Physical Object
    Pagination1 v. :
    ID Numbers
    Open LibraryOL25487473M

    See figure 5 Good yaw control can easily be achieved with an "all flying rudder" see again figure 2. A comparison of a large number of quasi-two-dimensional measurement results can therefore only be of qualitative signi- ficance. Modern passenger jet wing designs are optimized for speed and efficiency during the cruise portion of flight, since this is where the aircraft spends the vast majority of its flight time. Comparison of quasi- two-dimensional measurement data on various mechanical high-lift systems.

    The position of the tail above the fuselage, with the direct undisturbed air from the prop, provides excellent and responsive control from the tail sections, compared to the sluggish response a conventional configuration provides at slow flight. Thus a certain amount of tolerance exists for the selection of 8 favorable fineness ratios in the range of large flap angles, which may have an advantageous effect, for example, on the touch- and-go capability of an aircraft attempting to land particularly in the case of powerplant failure. Simple hinged flaps came into common use in the s, along with the arrival of the modern fast monoplane which had higher landing and takeoff speeds than the old biplanes. Contract or Grant No. With all flaps retracted, conventional horizontal flight would be achieved.

    Studies performed by the firm of MBB have shown that a transition to shorter and thicker fuselages becomes necessary for this purpose. Simple hinged flaps came into common use in the s, along with the arrival of the modern fast monoplane which had higher landing and takeoff speeds than the old biplanes. Blown flaps take " bleed air " from the jet engine 's compressor or engine exhaust and blow it over the rear upper surface of the wing and flap, re-energising the boundary layer and allowing the airflow to remain attached at higher angles of attack. Smith, A. Depending upon mode of functioning, all of these high-lift principles can generally be classified in two large groups, the mechanical and the "driven" high-lift systems the abbreviated designation "driven high-lift systems" used here may elicits some criJjicism. However, the aircraft is also designed to be easy and quick to build, and to provide a durable airframe that is well-suited for its utility role.


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Application of powered high lift systems to STOL aircraft design book

The possibil- ities for achieving aerodynamic efficiencies with these high- lift systems are first discussed. Airfoil Angle of Attack The lift coefficient can thus be effectively doubled with relatively simple devices flaps and slats if used on the full span of the wing.

In the transition to wings of finite aspect ratio with a wide variety of sources of disturbance and three-dimensional flow effects, reductions occur in the two-dimensional high lift coefficients which will be referred to collectively as aero- dynamic installation losses.

Mechanical auxiliary high-lift systems produce their lift from airspeed alone. A flap system was likewise combined with a slat. Rebuffet, P. Work Unit No. Mechanism[ edit ] In a conventional blown flap, a small amount of the compressed air produced by the jet engine is "bled" off at the compressor stage and piped to channels running along the rear of the wing.

Whereas a complex triple-slotted flap system on a Boeing produces a coefficient of lift of about 2. Plain flaps; k. Aerodynamic efficiency limits for this simple blown-flap system, driven flap with a,ugra,enta tion at the.

Purpose[ edit ] The size and lifting capacity of a fixed wing is chosen as a compromise between differing requirements. Moreover, no considerations have been given in these studies to the effects of controlability requirements, particularly in case of powerplant failure, upon net lift, nor upon the selec- tion of a suitable high-lift system for a specific aircraft configuration.

Simple systems maximize reliability, while minimizing pilot workload. While tailwheel aircraft have traditionally dominated in off-airport applications, the STOL CH 's tricycle gear offers rough field capability while providing all the advantages of a tricycle-gear aircraft, such as easy ground handling and superior visibility.

Short of building a very large horizontal tail, we need a large negative lift coefficient on the tail. Rudder Control cables from rudder pedals to rudder control horn. This allows the wing to be operated effectively at the higher angles required to produce more lift.

The Future Of Flight: A Congestion

However, with form following function, a study of the unique shapes shows the inherent beauty of these aircraft in their interesting, unique and highly effective aerodynamic and design features. NASw Another advantage of the all-flying vertical tail is that it is physically smaller and shorter than a corresponding conventional fin and rudder vertical tail, and thus lighter; and being a single piece it is easier to construct.

Abbott, I.

Blown flap

Another evaluation criterion is installation weight. Another approach is to use the airflow from the engines directly, by placing a flap so that it deploys into the path of the exhaust.

Extensive wind-tunnel studies become necessary in order to keep these unavoidable flow losses low to satisfy a high lift requirement. Modern blind rivet fasteners have greatly simplified all-metal kit aircraft construction; — Malleability: easy to form into many shapes, with almost no limit to the shapes it can be formed into; — Environmentally friendly: no health hazards to worry about when working with sheet metal; recyclable; — Easy to inspect: construction or materials flaws are easily detected, as are defective parts and damage.

A noticeable drawback is a relatively small low drag range, which means a narrow economical cruise speed range, but the overall configuration provides the best wing design for a STOL aircraft. The most efficient application of cyclic pitch control was deemed to result if a tail rotor system were called upon to provide some of the lift during the hover and transition phases.

This requirement for maximum lift lies within a range of values which approaches the upper limit of maximum lift coefficients which can be achieved with mechanical auxiliary lift systems.the overall configuration provides the best wing design for a STOL aircraft.

Thus, I have chosen this fixed slat configuration for the two-seat STOL CH and the new four-seat STOL CH The wing is lightweight, yet yields a very high lift coefficient, making it a very reliable, simple, and a low-cost high lift device for these two designs.

efficient, all-around V/STOL aircraft. One possible solution to this issue is the channel wing design, first conceived by Willard Custer during the s’.

Design, Build and Fly Ultralight Aircraft By Yourself . . !!

Custer proposed that it is the speed of the air flowing over the wing that creates lift, and not the speed of the wing through the air. Hence, he came up with the idea of the “channel. The need is to develop design technology that will produce high-lift systems that provide high L/D in climb-out, high lift coefficient during landing approach, acceptable performance in icing conditions, and acceptable levels of airframe noise, and that are also amendable.

Powered-lift aircraft can change the direction of their propulsion system’s thrust in flight. They characteristically have the airframe and propulsion system closely integrated so that the propulsion system exhaust flow influences the aerodynamics of the airframe.

They encompass a number of types. "The International Powered Lift Conference (IPLC) is the premier event for engineers, technologists and managers to discuss the latest developments in Vertical and/or Short Take-Off and Landing (V/STOL) aircraft research, concepts and programmes.

Aug 29,  · HIgh Speed STOL airfoil selection - HELP! Hey guys and on other aspects of the design as well. thats exactly one of my concerns with this concept imagine the aircraft flying at very low airspeed, at high angle of attack (slow sustained high alpha flight) for whatever reason- landing, or just for fun - do you think the deflected prop.