Published 1989 by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .
Written in EnglishRead online
|Statement||John R. Carlson and Milton Lamb.|
|Series||NASA technical paper -- 2877.|
|Contributions||Lamb, Milton., United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.|
|The Physical Object|
Download Integration effects of pylon geometry on a high-wing transport plane
Get this from a library. Integration effects of pylon geometry on a high-wing transport plane. [John R Carlson; Milton Lamb; United States.
National Aeronautics and Space Administration. Scientific and Technical Information Division.]. propulsion integration that can bc studied in order to reduce the drag penalty associated with engine in-stallation are the proximity of the engine nacelle to the wing, the spanwise location of the engine-pylon combination, pylon geometry, and the type of instal-lation (i.e., under the wing, over thc wing, or fuselage mounted).
Integration effects of pylon geometry on a high-wing transport plane / By John R. Carlson, Milton. Lamb and United States. National Aeronautics and Space Administration. Office of Management.
Abstract "February "es bibliographical. Results of a wind-tunnel study of the effect of pylon cross-sectional shape and tow angle on airplane drag and an aft-mounted nacelle are presented. The 1/scale wide-body high-wing transport model was tested in the Langley Foot Transonic Tunnel at free-stream Mach and angles of attack from -3 to 4 : Milton Lamb and John R.
Carlson. A high-wing transport model was tested in the Langley l6-Foot Transonic Tunnel to investigate the installation effects associated with pylons having var- ious cross-sectional shapes.
The tunnel is an atmo- spheric transonic single-return type with continuous air exchange and is. Integration Effects of Pylon Geometry on a High-Wing Transport Airplane,” (). Interference Effects of Very High Bypass Ratio Nacelle Installations on a Low-Wing Transport,”.
the integration effects of D-shaped, underwing, aft- mounted, separate-flow, flow-through nacelles on a high-wing, transonic transport configuration.
The results are summarized as follows: 1. The aft-mounted nacelle/pylon produced an in- crease in lift over that of the wing-body config. aircraft by reducing drag (and hence fuel consumption) through improved aerodynamic integration of the wing, pylon, and nacelle.
Installation of the pylon and nacelle on a transonic aircraft wing has signiﬁcant effect on chordwise and spanwise load distributions, shock position, and the viscous layer on the surface, and, therefore, Size: KB.
At present the layout of wing-mounted engine is generally used at the large transport aircraft. This kind of layout has numerous merits, but large interference drag is probably caused between the wing/pylon/nacelle and the aerodynamic performance is affected by: Aerospace Science and Technology Aerodynamic Aspects of Engine-Aircraft Integration of Transport Aircraft Fig.
13 c. - Fan exit, Mach number distribution in cruise with distortion. Calculated thrust vectors under takeoff conditions are in agreement with experiments carried out on the real engine .Cited by: Aerospace researchers have conducted a number of studies to compare conventional and compression pylon designs for an underwing nacelle.
These two designs were compared, to produce an environmentally friendly aircraft by reducing drag through improved aerodynamic integration of the wing, pylon, and nacelle. Rossow C.-C. Godard J.-L. Hoheisel H. Schmitt V.: Investigations Integration effects of pylon geometry on a high-wing transport plane book Propulsion Integration Interference Effects on a Transport Aircraft Conßguration.
AIAA PaperAIAA PaperCited by: 3. The 1/scale wide-body high-wing transport model was tested in the Langley Foot Transonic Tunnel at free-stream Mach and angles of attack from -3 to 4 degrees.
Pylon Design for a Short Range Transport Aircraft with Over-the-Wing Mounted UHBR Engines show that the unconventional pylon geometry, This paper shows the aerodynamic integration effects. SUMMARY As part of a propulsion/airframe integration program at Langley Research Center, tests have been conducted in the Langley Foot Transonic Tunnel to determine the longitudinal aerodynamic effects of installing flow-through mixed-flow enqine na- celles in the aft underwing position of a high-wing transonic transport airplane.
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Soda A., Tefy T. () Numerical Investigation of Wing-Nacelle Interference Effects at Transonic Flow Conditions for a Generic Transport Aircraft Configuration. In: Breitsamter C., Laschka B., Heinemann HJ., Hilbig R.
(eds) New Results in Numerical and Experimental Fluid Mechanics by: 1. A 'read' is counted each time someone views a publication summary (such as the title, abstract, and list of authors), clicks on a figure, or views or downloads the full-text.
influence the design of other aircraft components including aircraft tail design, landing gear design, and center of gravity. In principle, there are four options for the vertical location of the wing.
They are: 1. High wing 2. Mid wing 3. Low wing 4. Parasol wing a. High wing b. A "compression" pylon 10 for an aircraft with a wing-mounted engine, that does not cause supersonic airflow to occur within the fuselage-wing-pylon-nacelle channel The chord length of the pylon 10 is greater than the local chord length of the wing 12 to which it is attached.
The maximum thickness 45 of the pylon 10 occurs at a point corresponding to the local trailing edge 32 of the wing Computers t Structures Vol.
45, No. 5/6, pp.Printed in Great Britain. /92 $+ 5 Pergamon Press Ltd A STRUCTURAL DYNAMICS STUDY OF A WING-PYLON-TILTROTOR SYSTEM N.
KHADER and R. ABU-MALLOUH Mechanical Engineering Department, Jordan University of Science and Technology, P.O. BoxIrbid, Jordan (Received 23 April ) Abstract Author: N. Khader, R. Abu-Mallouh. High-lift systems have a major influence on the sizing, economics, and safety of most transport airplane configurations.
The combination of complexity in flow physics, geometry, and system support and actuation has historically led to a lengthy and experiment intensive development by: Tank is interconnected by an above-fuselage pylon and the tail plane.
Three different concepts have been shown in Fig. 16 which explains the different configuration of aircraft for LH 2 storage.
In Fig. 15 (a) and (b) hydrogen tank storage has been shown at the top and the end of fuselage, whereas in Fig. 15 (c) it is proposed that hydrogen is Cited by: Introduction The installation of engine nacelles on the wing, fuselage, or tail of an airplane has a decided effect on the aerodynamic performance of the airplane.
The difficulties of reducing interference drag for conven- tional, forward, underwing pylon-mounted nacelles on supercritical wings have been shown (ref. the main parts of an aircraft. A knowledge of the basic stresses on aircraft structures will help you understand why aircraft are built the way they are.
The fuselage of an aircraft is subject the fives types of stress—torsion, bending, tension, shear, and compression. Torsional stress in a File Size: 1MB. The plane was powered by four pylon mounted GE J engines, making it an extremely loud airplane.
One of the curious features was the use of a “double bubble” attached pod below the fuselage. The outer pod carried fuel and was jettisoned when empty. The inner pod was in fact the nuclear bomb. The Boeing transport was the first of the long-range and, for its day, high-passenger-capacity aircraft that marked the real beginning of the revolutionary jet age in air transportation.
Even today, many people consider the terms and jet transport to be synonymous. The amount of lift generated by a wing depends on how much the flow is turned, which depends on the shape of the object. The lift is, in general, a very complex function of the shape. Aerodynamicists model the effect by a lift coefficient which is normally determined through wind tunnel testing.
The Wright brothers built a wind tunnel in to determine the best shape for their wings. 40 Fig ure 2 3. Isolator and combustion chamber schematic and pylon geometry. The fuel was transversely injected into the supersonic crossflow from a 1mm diameter orifice located at 10 H upstream of t he step, i.e.
in the isolator. The pylon is mm high and mm wide at the base. Effects of leading-edge sweep on flutter characteristics of some delta-planform surfaces at a Mach number of / (Washington, D.C.: National Aeronautics and Space Administration: [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia ], ), by Robert C.
Goetz, Langley Research Center. Osprey (Transport plane) Filed under: V Osprey (Transport plane) The V Osprey: costs, capabilities, and challenges: hearing before the Committee on Oversight and Government Reform, House of Representatives, One Hundred Eleventh Congress, first session, J Next, they secured the tank dolly straps to the tank and removed the rear nut that secured the aft portion of the tank to the aircraft last step is to rotate the manual release handle on the pylon.
2 M - Transformation Geometry The Euclidean Plane E2 Consider the Euclidean plane (or two-dimensional space) E2 as studied in high school geometry. Note: It is customary to assign diﬀerent meanings to the terms set and space. Intuitively, a space is expected to possess a kind of arrangement or order that is not required of a Size: KB.
The effects of the aerodynamic load and the interference due to the engine-nacelle installation over the wing were studied as well.
The result showed that the effects are small for this OTWEM configuration. Further-more, the engine-pylon vibration characteristics influence the flutter char-acteristics. Constructive Geometry of Plane Curves With Numerous Examples [MA T. EAGLES] on *FREE* shipping on qualifying offers.
This work has been selected by scholars as being culturally important, and is part of the knowledge base of civilization as we know it. This work was reproduced from the original artifact.
The wing configuration of a fixed-wing aircraft (including both gliders and powered aeroplanes) is its arrangement of lifting and related surfaces. Aircraft designs are often classified by their wing configuration.
For example, the Supermarine Spitfire is a conventional low wing cantilever monoplane of straight elliptical planform with moderate aspect ratio and slight dihedral. The Lockheed F Starfighter is an American single-engine, supersonic interceptor aircraft which became widely used as a fighter-bomber during the Cold lly a day fighter, it was developed into an all-weather fighter in the late s.
It was originally developed by Lockheed for the United States Air Force (USAF), but was later produced by several other nations, seeing widespread Manufacturer: Lockheed.
Ideal for users who may have little previous experience with abstraction and proof, this book provides a rigorous and unified—yet straightforward and accessible—exposition of the foundations of Euclidean, hyperbolic, and spherical in approach, it combines an extended theme—the study of a generalized absolute plane from axioms through classification into the three Cited by: 2.
without the nacelle/pylon group. The horizontal tail is robustly designed for dive Mach number conditions and is suitably sized for typical stability and control requirements.
The fuselage is representative of a wide/body commercial transport aircraft; it includes a wing-body fairing, as well as a scrubbing seal for the horizontal tail. GROUND VIBRATION TESTING OF AIRPLANE PYLON-STORE DYNAMICS USING LASER DOPPLER VIBROMETER AND ACCELEROMETER TECHNIQUES By Joseph Dupuis May Chair: Dr.
Richard C. Lind Major Department: Mechanical and Aerospace Engineering Ground vibration testing is the process of determining a structure’s dynamic re-sponse to a force input. The F Tomcat is a plane that employs variable-sweep technology.
For slower speeds and landing, especially on small runways like aircraft carriers, the F Tomcat’s wings extend to be nearly perpendicular to the fuselage. For faster, supersonic speeds, the wings contract to .Math Journal - Chapter 7 - Plane Geometry The extension for this lesson () will show you how to create points using Microsoft Word.
This skill will teach you advanced Word Integration with School-wide Focus: Improve mathematics computation and problem solving. Related Activities: There are. Size: 1MB.Aviation Stack Exchange is a question and answer site for aircraft pilots, mechanics, and enthusiasts.
promoting a book on amazon is not really ok. $\endgroup$ – Federico Do high-wing aircraft represent more difficult engineering challenges than low-wing aircraft?