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Sunday, December 6, 2020 | History

4 edition of Wing pressure distributions from subsonic tests of a high-wing transport model found in the catalog.

Wing pressure distributions from subsonic tests of a high-wing transport model

Zachary T. Applin

Wing pressure distributions from subsonic tests of a high-wing transport model

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Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va .
Written in English


Edition Notes

StatementZachary T. Applin and Carl L. Gentry, Jr., M.A. Takallu.
SeriesNASA technical memorandum -- 4583.
ContributionsGentry, Carl L., Takallu, M. A., Langley Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17788775M
OCLC/WorldCa32865600

Enhancement of Aircraft Cabin Design Guidelines - eLib. 1 Technical Paper Wing Pressure Distributions From Subsonic Tests of a High-Wing Transport Model Applin, Zachary T., Gentry, Garl L., Jr., Takallu, M.A. .


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Wing pressure distributions from subsonic tests of a high-wing transport model by Zachary T. Applin Download PDF EPUB FB2

A wind tunnel investigation was conducted on a generic, high-wing transport model in the Langley by Foot Subsonic Tunnel. This re-port contains pressure data that document effects of various model con-figurations and free-stream conditions on wing pressure distributions.

The untwisted wing incorporated a full-span, leading-edge Krueger flap. Get this from a library. Wing pressure distributions from subsonic tests of a high-wing transport model. [Zachary T Applin; Carl L Gentry; M A Takallu; Langley Research Center.]. wing configurations selected for the study were a low wing cantilever installation, a high wing cantilever, a strut-braced wing, and a single jury TBW.

The mission that was used for this study was a passenger transport aircraft with a design range of 2, nautical miles at the design payload, flown at a cruise Mach number of When it's hot, and you're waiting in line for fuel, or if your plane isn't hangared, you can stand in the shade under a high wing.

If you want to walk from fore of the wing to aft of the wing, to get the oil rag you forgot, with a high wing, you duck a bit and walk straight, with a low wing, you walk all the way around the wing.

Twice. slide 8 2/21/11 Ocean Engineering Aerospace and Example of Constraint Lines (approximate examples, be able to derive your own) Note: convert T/W to M=0, h=0 values, W/S to takeoff values N is number of engines, CGR is the climb gradient, q implies best altitude, Mach, and L/D should be for correct flight condition.

Takeoff:File Size: KB. Low-speed wind-tunnel tests of an advanced eight-bladed propeller [microform] / Paul L. Coe, Jr., Carl L Wing pressure distributions from subsonic tests of a high-wing transport model [microform] / Zachary T.

Genealogical and heraldic history of the landed gentry of Ireland. Edited by L. Pine. Low wing models can be tricky to hand launch, (unless experienced). The range goes from, - high wing, - shoulder wing (resting on/in the top of a box fuselage), - mid-wing, (some of the scale models, and many fully aerobatic jobs), - to low wing.

The results consist of detailed pressure distributions over a wide range of Reynolds numbers ( x 10(exp 6) to x 10(exp 6)) and angles of attack (20 to 90 deg).

Truncated cone in supersonic flight at zero angle of attack: surface pressure coefficients, drag coefficients, and shock front configurations / (Urbana, Ill.: Mechanical Engineering Dept., Engineering Experiment Station, University of Illinois, Jan.

), by W. Chow, C.C. Tsung, Helmut Hans Korst, and University of Illinois (Urbana. A Flow Control for a High Subsonic Regional Aircraft Exploiting a Variable Camber Wing with Hybrid Laminar Flow Control () Wseas/Iasme Transactions.

If the plane flies straight in the glide tests, but turns Left under power, you'll need to add a little right thrust to the motor to compensate and if the plane stalls under power, you need to add a little more down thrust (or add a bit of clay on the nose to move the CG slightly forward).

Effects of spanwise blowing on the surface pressure distributions and vortex-lift characteristics of a trapezoidal wing-strake configuration / ([Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, ), by James F.

Campbell and Gary E. Erickson (page images at HathiTrust). Other articles where High wing is discussed: wing: positioned above the fuselage (high wings), wings provide an unrestricted view below and good lateral stability.

Parasol wings, placed on struts high above the fuselage of seaplanes, help keep the engine from water spray. The flow solver OVERFLOW is based on this approach and Rogers et al., have applied it to obtain flow simulations for several high-lift configurations including an early design version of the Boeinga high wing transport with externally blown flaps, a simplified 3D high-lift wing, and a Boeing Most impressive is their effort.

A high-wing airplane design, contributes to the lateral stability, whereas a low wing placement has a destabilizing effect in roll. However, this effect may be counteracted by including more dihedral to improve the overall lateral stability.

Wing sweep will help promote lateral stability. This wing was designed with subsonic methods, which were essentially all that was available at the time.

Note that the isobars are tending to unsweep. On the upper right-hand side of the figure we see that at subsonic speed the pressure distributions at the 30% and 70% span stations lie on top of each other, the isobars are good.

From Summary: "Lateral-stability flight tests were made over the Mach number range from to of models of three airplane configurations having 45 degree sweptback wings. One model had a high wing; one, a low wing; and one, a high wing with cathedral.

The models were otherwise identical. The lateral oscillations of the models resulting from intermittent yawing disturbances were. X-Plane is the world’s most comprehensive and powerful flight simulator for personal computers, and it offers the most realistic flight model available. X-Plane is not a game, but an engineering tool that can be used to predict the flying qualities of fixed- and rotary-wing aircraft with incredible accuracy.

Full text of "NASA Technical Reports Server (NTRS) US and USSR Military Aircraft and Missile Aerodynamics A selected, annotated bibliography, volume 1" See other formats. The effect of wing sweep. In practice the whole wing does not stall at the same instant.

Swept and tapered wings will tend to stall at the tips first because of the high wing loading at the tips. The boundary layer outflow also resulting from wing sweep slows the airflow and reduces the lift near the tips and further worsens the situation. Design Sensitivity Problem Structure Selection Variables Jet Transport Empty Weight Weight Breakdown Wing Structure (Item 10) Fuselage Structure (Item 11) Empennage Structure (Items 12 and 13) Landing Gear Structure (Item 14) Power Plant and Engine Pylons (Items 2 and 15) Systems.

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Full text of "NASA Technical Reports Server (NTRS) Thirty-Ninth Annual Report of the National Advisory Committee for Aeronautics: Administrative Report Including Technical Reports Nos. to " See other formats. Extreme flight conditions usually set design requirements for tail surfaces, as minimum control speed with one engine inoperative or maximum cross-wind capability ().Stability and control must be ensured even in large angles of sideslip as 25°.The design of a vertical tailplane depends mainly on the type of airplane (configuration layout, flow regime, aesthetics, costs), and on engines.

Read NASA's Contributions to Aeronautics, Volume 1, by National Aeronautics & Space Administration. in HTML for FREE. Also available in PDF, ePub and Kindle formats. HTML version, page 3. Library of Congress Cataloging-in-Publication Data (Revised for vol.

8) NASA historical data book. (NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C. Bruno. Vol. 8 in series: The NASA historical data book series. Includes bibliographical references and indexes. A CD for a fuselage added to a high wing _8 - • based on a wing area S • Sq.

and a fueelage frontal area Sw • sq. The corresponding Talue of£\CDIr • z: / • Referring to page A2bll f values as ' as are reported for & high wing. Summary: An analysis of the effect of wing loading on the landing flare (that is, the leveling-off part of the landing) indicated an important effect on landing technique and distance.

In order to check this analysis, flight tests were made with a Martin B airplane loaded to 50 pounds per square foot. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Redesigned Boeing Wing at Mach based on Cp Distributions 57 Figure also displays Redesigned Boeing wing at Mach with Cp distributions.

In the final-design stage it is necessary to predict the loads throughout the flight envelope. As many as. This book focuses on using and implementing Circulation Control (CC) - an active flow control method used to produce increased lift over the traditionally used systems, like flaps, slats, etc.

- to design a new type of fixed-wing unmanned aircraft that are endowed with improved aerodynamic efficiency, enhanced endurance, increased useful payload (fuel capacity, battery cells, on-board sensors. Walter and Myhra discuss photo of flying model (seen in Selinger/Horten Nürflugel, page 24 with 'B 13d' on top of wing), #'s refer to category of the model and contest number given by contest officials [].

Walter: Model tests not very successful because models could not be controlled in. Theoretical Aerodynamics is a user-friendly text for a full course on theoretical aerodynamics. The author systematically introduces aerofoil theory, its design features and performance aspects, beginning with the basics required, and then gradually proceeding to higher level.

Predicted pressure distributions for 20 and 50% thick Rankine constant doublet strength equal to 2 4 Equation can be written as m (tan-'l+tan-' Q =- - 4 iT€ lim E + O E-X €+X v) uy Referring to Figurethe net vertical force, or lift, on the cylinder resulting from the pressure distribution will be L = -jo pR sin BdB In the limit.

On high-wing aircraft, the CG is below the wing, so less dihedral is required (Figure b). Many military aircraft, including fighter jets and transport planes, are utilizing high-wing design.

The main wing structure is connected to the leading and trailing edge flight control surfaces including slats and flaps as shown in Figure Zachary T. Applin, Pressure Distributions From Subsonic Tests of a NACA Semispan Wing Model, NASA TM, Septemberpp. Marshall Smith, Victoria I.

Chung and Debbie Martinez, Transport Delays Associated with the NASA Langley Flight Simulation Facility, NASA TM, Junepp. A high wing has a little more stability than a low wing, but the change in stability is small when compared to Howard Hughâ€&#x;s infamous Spruce the effects of sweeping the wing and.

This banner text can have markup. web; books; video; audio; software; images; Toggle navigation. Reynolds AIRPLANE DRAG 3 to [email protected] flight bers for aircraft in may be million OF EFFECT WING PLANFORM layer is predominately boundary the where The of aerodynamic previous discussion involve may tests model Scale turbulent.

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Fig. Streamwise Pressure Distributions over the Upper of the Main Wing close to the Wing-tip for Different Winglet Configuration (Houghton ). Passenger Compartment For cabin design, passenger compartments (Fig. ) are considered to design a .Watch the wing tufts to see how quickly the airflow reattaches when you release some aft pressure.

The damping you generate in the turn pushes the nose right down. At 2 g’s there’s a Publishing platform for digital magazines, interactive publications and online catalogs. Convert documents to beautiful publications and share them worldwide. Title: (e Book - English - Military) US Army - Field Manual FM 3 04 - Fundamentals Of Flight, Author: Cahiers de la Pensée Mili-Terre, Length: pages, Published: