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Tuesday, July 28, 2020 | History

3 edition of In-flight aerodynamic measurements of an iced horizontal tailplane found in the catalog.

In-flight aerodynamic measurements of an iced horizontal tailplane

In-flight aerodynamic measurements of an iced horizontal tailplane

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  • 30 Currently reading

Published by National Aeronautics and Space Administration, Lewis Research Center, National Technical Information Service, distributor in [Cleveland, Ohio], [Springfield, Va .
Written in English

    Subjects:
  • Aerodynamic characteristics.,
  • Horizontal tail surfaces.,
  • Flight characteristics.,
  • Aerodynamics.,
  • Wind tunnel tests.,
  • Aircraft icing.

  • Edition Notes

    Other titlesIn flight aerodynamic measurements of an iced horizontal tailplane.
    StatementThomas P. Ratvasky, Judith Foss Van Zante.
    SeriesNASA/TM -- 1999-208902., NASA technical memorandum -- 208902.
    ContributionsVan Zante, Judith Foss., Lewis Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18134755M

      Effect of Ice Accretion on Aircraft Flight Dynamics measured on natural and simulated iced aircraft is presented. A review of earlier computational methods is also included. Then, the aircraft models for an iced accretion attached to the horizontal and vertical tail was determined, Purpose – The purpose of this paper is to maintain safe flight and to improve existing deicing (in‐flight removal of ice) and anti‐icing (prevention of ice accretion) systems under in‐flight icing conditions. Design/methodology/approach – A recent academic research on aircraft icing phenomenon is presented. Several wind tunnel tests of an experimental aircraft provided by NASA are

    Cloud type or structure is determined by whether the air is stable or unstable within the layer forced upward. When stable air is forced upward, the air tends to retain horizontal flow and any cloudiness is flat and stratified. When unstable air is forced upward, the disturbance grows, and resulting cloudiness shows "heaped" or cumulus ://   Flight Gear (present version ) Graphics Sky Clouds Main Scenery Devices Audio Joystick Flight Dynamics Module FDM Weather Flight Dynamics Module Smart Icing Systems NASA Review, June , Flight Gear FDM JSBsim LaRCsim  › 百度文库 › 行业资料.

    Full text of "[Tail Plane Icing]" which occurs due to increased angle-of-attack of the horizontal tailplane resulting in tailplane stall. Typically, this phenomenon occurs when lowering the flaps during final approach while operating in or recently departing from icing conditions. These tests resulted in a database of the aerodynamic   No ice was found on the aircraft during a post-flight inspection but analysis by the manufacturer concluded that, from the start of the flight until the latter stages of the descent, the airflow over the horizontal tailplane and elevator was disrupted by ice ://?bookId=


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In-flight aerodynamic measurements of an iced horizontal tailplane Download PDF EPUB FB2

In-Flight Aerodynamic Measurements of an Iced Horizontal Tailplane Thomas P. Ratvasky Lewis Research Center, Cleveland, Ohio Judith Foss Van Zante Dynacs Engineering Company, Inc., Brook Park, Ohio Prepared for the 37th Aerospace Sciences Meeting and Exhibit sponsored by the American Institute of Aeronautics and Astronautics Reno, Nevada   In-flight aerodynamic measurements of an iced horizontal tailplane.

Experimental Investigation of the Influence of the Shape of Ice Outgrowths on the Aerodynamic Characteristics of the Wing. 30 April | Journal of Engineering Physics and Thermophysics, Vol. 92, No. 2 Investigation of dynamic flight maneuvers with an iced :// Get this from a library.

In-flight aerodynamic measurements of In-flight aerodynamic measurements of an iced horizontal tailplane book iced horizontal tailplane. [Thomas P Ratvasky; Judith Foss Van Zante; Lewis Research Center.] In-Flight Aerodynamic Measurements of an Iced Horizontal Tailplane dynamic flight maneuvers were performed over the full range of angles of attack and wing flap settings with each iced tailplane configuration.

This paper presents results from the quasi-steady state flight conditions and describes the range of flow fields at the horizontal   NASA/FAA Tailplane Icing Program overview. Thomas Ratvasky, Parameter Identification of Tailplane Iced Aircraft Based on Maximum Likelihood Method.

1 July | Applied Mechanics and Materials, Vol. In-flight aerodynamic measurements of an iced horizontal :// Thomas P. Ratvasky has written: 'In-flight aerodynamic measurements of an iced horizontal tailplane' -- subject(s): Flight characteristics, Aircraft icing, Aerodynamics, Wind tunnel tests   Iced Aircraft Flight Data for Flight Simulator Validation NASA/TM— instrumentation for cloud physics and flight dynamics measurements and 2) NASA owns and operates the rudder, and wing flaps.

The horizontal tailplane has a fixed stabilizer with an elevator and trim tab. INSTRUMENTATION SYSTEMS The research data acquisition The tailplane stall has received very little attention in aviation training venues, and because of this, it is not well understood by most pilots.

But before we explore the aerodynamics of the tailplane stall, we first have to know that the term means. A “tailplane stall” refers to the stalling of an airplane’s horizontal It was postulated that the extension of full flaps could cause an iced-up stabilizer to stall. Flight Tests.

Armed with this theory, NASA and the Airline Pilots Association decided to conduct flight tests to investigate whether full flaps on a high-wing airplane with an iced-up stabilizer could cause a tailplane   Aerodynamics of Flight Chapter 3. Figure Vector components of lift, drag, and weight (gravity).

a Lift Thrust Vertical Weight Flightpath a a Horizontal Drag Aircraft angle Forces of Flight There are four forces that act upon an aircraft during straight-and-level flight.

They are lift, gravity, thrust, and drag. Lift counters gravity Aircraft flight characteristics in icing conditions. In-flight aerodynamic measurements of an iced horizontal tailplane, AIAA PaperGoogle Scholar A.H.

RonaldHelicopter flight characteristics in icing conditions. Aeronaut. J., () (), pp. Google Scholar Based on the detailed aerodynamic measurements taken on iced airfoils and wings sinceand primarily sincethis section presents the current understanding of these flowfields. This discussion is divided into four parts based on representative ice geometries: (1) roughness, (2) horn ice, (3) streamwise ice, and (4) spanwise-ridge :// Numerical simulations are conducted on the DHC-6 Twin Otter wing and horizontal tailplane to explore the aerodynamic penalties that affect airfoil performance in heavy rain :// Airfoil Ice-Accretion Aerodynamic Simulation.

and “iced flight baseline” (IFB). In-Flight Aerodynamic Measurements of an Iced Horizontal Tailplane. :// /_Airfoil_Ice-Accretion_Aerodynamic_Simulation.

significant trim change between the united and iced horizontal stabilizer. Such a trim change can pro- vide one part of a method for detecting horizontal stabilzer icing. Flight Test The NASA Lewis twin otter Icing Research Aircraft was used to conduct flight tests with different cases of tailplane ://.

In the simulations, the longitudinal and lateral dynamics of an Airbus A aircraft model are considered, and the stability derivatives affected by icing are identified.

The simulation results show the successful NN identification of the icing parameters and the reconfigured flight dynamics having the   Secondly, in respect of tailplane stall due to ice build-up on the undersurface of the horizontal stabilizer and elevator (whether asymmetric or not).

Note that Q does not have a variable incidence tailplane: The problem is that wing and tailplane stalls have opposite recovery   Flap deflection of 0, 8, 20 and 40 degrees were tested with the clean and iced tail to investigate the effect of wing downwash on the aerodynamic performance of the clean and iced contaminated tailplane.

In general, tail stall occurred progressively earlier as the flap deflection was increased from 0 to 40 :// Розроблено методологію розрахунку параметрів пневматичної протиобледенювальної системи   The basic design was tested with the tailplane set at + 1 deg, -- 1 deg and -- 5 deg to the fuselage horizontal datum, and with the tailplane removed, but the tests on the modified designs included only the cases with the tailplane set at -- 1 deg and with the tailplane.

Aerodynamic Effects – Tail. The lower surface of the horizontal tailplane is as aerodynamically critical as the upper surface of the wing.

Contamination near the leading edge of the tailplane’s lower surface can cause a pitch upset. Contamination in tail-elevator gap could restrict your ability to maneuver the aircraft.

Further Information  The horizontal stabiliser, or tailplane, of an aircraft is an aerofoil that provides a downward force to overcome the aircraft's normal nose-down pitching moment.

The further forward the Centre of Gravity is from the Center of Pressure, the greater the nose down moment and, thus, the greater the amount of down-force that must be generated by This paper addresses the effects of propeller installation on the aerodynamic performance of a tailplane featuring tip-mounted propellers.

A model of a low aspect ratio tailplane equipped with an elevator and a tip-mounted propeller was installed in a low-speed ://