3 edition of Experimental effects of wing location on wing-body pressures at supersonic speeds found in the catalog.
Experimental effects of wing location on wing-body pressures at supersonic speeds
Jerry M. Allen
by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, National Technical Information Service, distributor] in [Washington, DC], [Springfield, Va
Written in English
|Statement||Jerry M. Allen and Carolyn B. Watson.|
|Series||NASA technical memorandum -- 4434., NASA technical memorandum -- 4434.|
|Contributions||Watson, Carolyn B., United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.|
|The Physical Object|
Authors have been studying an aerodynamic feasibility of supersonic biplanes based on the concept of the Busemann biplane. In this paper, the three dimensional effect of wing geometries on their wave drags, including wing tip effects and the interference effects between the wing and a body (Wing-Body configurations) are investigated, using CFD. 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.
1 Performance 6. Airfoils and Wings The primary lifting surface of an aircraft is its wing. The wing has a finite length called its wing span. If the wing is sliced with . Effects of wing leading-edge radius and Reynolds number on longitudinal aerodynamic characteristics of highly swept wing-body configurations at subsonic speeds (NASA technical note ; NASA TN D) [William P Henderson] on awordathought.com *FREE* shipping on qualifying awordathought.com: William P Henderson.
Delta wing airplanes. See also what's at your library, or elsewhere. Broader terms: Airplanes -- Wings, Triangular Flight test and analysis of the rolling motions of a 79 ̊clipped delta configuration with wing-tip fins at supersonic speeds / (Washington, D.C.: Effects of . theory to a slender wing-body combination is considered and a numerical example is given with comparison to experimental data and other prediction methods. 1 Introduction Piston theory  has long been used to predict surface pressures on wings and on panels in supersonic ﬂows. Classical piston theory (CPT) is deﬁned by modelling.
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CiteSeerX - Document Details (Isaac Councill, Lee Giles, Pradeep Teregowda): An experimental study has been performed at supersonic speeds to measure wing and body spanwise pressure distributions on an axisymmetricbody delta wing model on which the wing vertical location on the body was systematically varied from low- to high-mounted positions.
Get this from a library. Experimental effects of wing location on wing-body pressures at supersonic speeds. [Jerry M Allen; Carolyn B Watson; United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.]. Get this from a library. Experimental effects of wing location on wing-body pressures at supersonic speeds.
[Jerry M Allen; Carolyn B Watson; Langley Research Center.; United States. National Aeronautics and Space Administration. Scientific and Technical Information Program,]. COMPARISONS OF THEORETICAL AND EXPERIMENTAL PRESSURE DISTRIBUTIONS OVER A WING-BODY MODEL AT HIGH SUPERSONIC SPEEDS by Lloyd S.
Jernell Lungley Research Center Hdmpt0~2, Va. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. SEPTEMBER The linear-theory methods used to predict the wing pressures are in. At supersonic speeds, some laborious methods were developed for computing the interference effects of the body on the load distribution of the wing and tail.
Another investigation to study the effects of the wing on the tail flow field in subsonic flow is that of Sliverstein, Sliverstein and awordathought.com by: 2.
The author provides solutions for three-dimensional compressible Navier-Stokes layer subsonic and supersonic. (source: Nielsen Book Data) Experimental effects of wing location on wing-body pressures at supersonic speeds Wind-tunnel investigation at supersonic speeds of a remote-controlled canard missile with a free-rolling-tail brake.
THEORY OF WING-BODY DRAG AT SUPERSOMC SPEEDS* By ROBERTT. JONES SUMMARY TLe relation of Whitcomb’8 “area rule” to thelirwarformulu-s for wave drag at slig~y supersonic speeds is discussed. By adopting an awordathought.comwn between the source strength and the geometry of a wing-body combination, tlw wuvednzgCited by: Oct 22, · From Summary: "A method is presented for calculating the lift and centers of pressure of wing-body and wing-body-tail combinations at subsonic, transonic, and supersonic speeds.
A set of design charts and a computing table are presented which reduce the computations to routine operations. Comparison between the estimated and experimental characteristics for a number of wing-body and Cited by: Sep 17, · is made between the estimated and experimental characteristics for a large number of wing-body and wing-body-tail combinations.
Generally speaking, the lifts were estimated to within 10 percent and the centers of pressure were estimated to within of the body length.
The effect of wing deflection on wing-tail interference at supersonic speedsCited by: 4. Aerodynamic Characteristics of Bodies of Revolution at Near-Sonic Speeds of the aerodynamics about configurations at near-sonic or low-supersonic speeds. The validity of the wind-tunnel test.
This report is part of the RAND Corporation research memorandum series. The Research Memorandum was a product of the RAND Corporation from to that represented working papers meant to report current results of RAND research to appropriate audiences.
and low supersonic speeds the normal-pressure drag at zero lift is mainly confined to the wing root and hence that modifications to the wing-body junction only, could bring about reductions in drag.
Among the desirable junction pressure distributions considered in Ref. 2 are constant pressure. Supersonic Wing─Body Two-Level Wave Drag Optimization Using Extended Far-Field Composite-Element Methodology waves on each location.
The wing thickness constraints. A Free-Flight Investigation of Wing-Body Junction Design for a Transonic Swept-Wing Aircraft G.
Hunt, awordathought.com(Eng.), awordathought.comS. 13 while cruising at low supersonic speeds. This ratio is higher than had The principles on which wing-body junotion designs must be based, if they are to be.
Experimental Study of the Subsonic Aerodynamics of a Blended Wing Body Air Vehicle with a Focus on Rapid Technology Assessment [David A. Gebbie, Air Force Institute of Technology (U.S.] on awordathought.com *FREE* shipping on qualifying offers.
The subsonic aerodynamic performance of a blended wing body aircraft constructed using selective laser sintering was assessed in the AFIT low-speed Cited by: 3. OBTAINING HIGH LIFT-DRAG RATIOS AT SUPERSONIC SPEEDS 30 1 effect is of the same order as that to be obtained by wing warp, regardless of the base drag.
We see then that 6 per cent gain in (L/D), is of the order of the increase to be anticipated from sonic-edged wings by =. This banner text can have markup. web; books; video; audio; software; images; Toggle navigation.
Oct 22, · Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex awordathought.com Edition: 1.
wing flows, and the dynamic hysteresis of flows yields the damping moments sustaining the oscillations. KEYWORDS: Wing rock, Asymmetric forebody vortices, Wing body, High angle of attack, Wind tunnel test. Experimental Investigation on Limit Cycle Wing Rock Effect on Wing Body Configuration Induced by Forebody VorticesAuthor: Zhen Rong, Xueying Deng, Baofeng Ma, Bing Wang.
Aerodynamic Lift On Wing-Body Combinations At Small Angles Of Attack In Supersonic Flow (MISLIFT) Two separate and distinct theories are incorporated in this computer program to estimate the lift-induced pressures existent on a wing-body combination.
These are. An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds.
The wing aspect ratio was 3, taper ratio wasand quarter-chord-line sweepback was deg. with 3-percent.A flying wing is a tailless fixed-wing aircraft that has no definite fuselage. The crew, payload, fuel, and equipment are typically housed inside the main wing structure, although a flying wing may have various small protuberances such as pods, nacelles, blisters, booms, or vertical stabilizers.Jul 14, · W12SC3 applies linear theory panel methods to compute solutions for a wing-body configuration.
The programs are not restricted to supersonic maneuvering cases, but are useful for many design, analysis, and optimization applications.