2 edition of Development of aerodynamic prediction methods for irregular planform wings found in the catalog.
Development of aerodynamic prediction methods for irregular planform wings
David B. Benepe
1983 by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va .
Written in English
|Statement||David B. Benepe, Sr. ; prepared for Langley Research Center, under contract NAS1-15073.|
|Series||NASA contractor report -- NASA CR-3664.|
|Contributions||United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., Langley Research Center., General Dynamics Corporation.|
|The Physical Object|
|Pagination||xxxiv, 442 p. :|
|Number of Pages||442|
Aileron power is maximized. This wing planform allows the greatest aileron span and area relative to wing area. The sweep moves the aerodynamic center of the wing closer to that of the duct, and the aerodynamic center of the entire configuration towards the correct location relative to . This is a book for those who seek to understand the fundamental principles underlying aircraft aerodynamic design. It won't provide much guidance relating to designing the details of a particular project but it is very illuminating about what general kind of /5(6). The present invention relates generally to aerodynamic prediction methods. More specifically, the present invention relates to improved aerodynamic prediction techniques and corresponding methods employing semiemperical code. The instant application is based on Provisional Patent Application No. 60/,, which was filed on Jan. 5,
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Development of aerodynamic prediction methods for irregular planform wings. Washington, D.C.: National Aeronautics and Space Administration, Scientific and. Energy Research and Development Administration and Lawrence Berkeley Laboratory. Energy and Environment Division (page images at HathiTrust; US access only) Benepe, David B.: Development of aerodynamic prediction methods for irregular planform wings / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical.
for the development of a method for the prediction of aerodynamic load distri-butions of wings with nonconical leading-edge vortex flow. This paper is presented as a progress report on this work, bringing forward the motivation for this research program, the objectives of the work, and some selected results.
55File Size: 4MB. A systematic kernel function procedure for determining aerodynamic forces on oscillating or steady finite wings at subsonic speeds [electronic resource] / (Langley Field, VA: Langley Research Center ; Springfield, Va.: for sale by the National Technical Information Service, ), by Charles E.
Watkins, Herbert J. Cunningham, Donald S. The Development of aerodynamic prediction methods for irregular planform wings book proposed for use would include known analytical approaches as modified for correlation with applicable test data. The data presented here covers recommended design equations and curves for a wide range of structural configurations and loading condition including combined loads.
APPARATUS AND METHODS Model Details of the model are presented in figure 1. The configuration was the midwing type having an ogive-cylinder fuselage. The vertical tail consisted of a constant-thickness slab with a wedge-shaped leading edge and a trapezoidal planform.
The wing was composed of a main spar to which leading- and trailing-edge extenFile Size: 5MB. mercial transport aircraft show a sucessful trade of planform design, leading to meaingful designs. The results also support the necessity of including the structure weight in the cost function. INTRODUCTION WHILE aerodynamic prediction methods based on CFD are now well established, and quite accurate and robust, the ultimate need in the design.
resize these study wings per real aircraft design considerations. Both of these elements introduce non-optimal characteristics in the planform layout of the study wings, especially for those with sweep deviating most from that of the baseline.
In this respect, the ﬁndings herein for the lowest-sweep wings may be overly by: Aerodynamic analysis and calculation are very important parts in the aircraft design, and aerodynamic engineering prediction is widely used in the aircraft preliminary design stage.
However, traditional aerodynamic engineering prediction causes heavy computation and is time-consuming. The developed software such as DATCOM has the disadvantages of complicated operation and black box : Di Liang, Sheng Jing Tang.
techniques to CFD methods of ever increasing capabilities. In the experimental field, more advanced windtunnel test facilities and techniques have also been progressively employed of the computational methods. Keywords: Aerodynamic design, aircraft wings, EMBRAER 1 Glossary Aspect ratio = ratio between the square of the wing span and the wing area.
aerodynamic characteristics of curved leading edge wing. Two geometries of NACA airfoil with rectangular planform and with curved leading edge planform are developed in Solidworks to compare numerically in ANSYS Fluent. The lift and drag coefficients are determined and compared for both models.
Moreover, the flowFile Size: KB. aerodynamic center of such wings is located along the centroidal chord as specified by Eq. (3). However, wings with linear taper do not produce a uniform additional section lift coefficient. Thus, Eq. (2) should be used only as a rough estimate for the semispan aerodynamic center of a trapezoidal by: 7.
Various aerodynamic aspects of low-Reynolds number rectangular wings have been studied for many years. These studies include experimental investigations (WinterBradley et alTorres. Aerodynamic Design of Swept Wings and Bodies 3. WING PLANFORM DESIGN As pointed out in the previous section, swept vsings with conventional straight-edged planforms have two principal defects in the transonic speed range.
The first is that, particularly when the planform is highly tapered,File Size: 6MB. "The basic aerodynamic relations needed for the design of wings with cambered span having a minimum induced drag at specified flight conditions are developed for wings of arbitrary spanwise camber.
Procedures are also developed for determining the physical wing form required to obtain the maximum value of lift-drag ratio at cruise, when the wing spanwise camber-line and section profiles are.
AERODYNAMIC DESIGN OF FLYING WING WITH EMPHASIS ON HIGH WING LOADING. Fig. 22 Pitching moment coefficient vs. angle of attack. Fig. 23 Drag polar for Model No 9 Trim condition The trim condition is a very important issue for the aircraft in File Size: KB.
Fixed and Flapping Wing Aerodynamics for Micro Air Vehicle Applications. Thomas J. Mueller. II Effect of Aspect Ratio and Planform on the Aerodynamic Lift and Drag. Fixed and Flapping Wing Aerodynamics for Micro Air Vehicle Applications Progress in astronautics and aeronautics:5/5(1).
exceptions. The methods are extremely accurate for elliptic wings and rectangular wings with some notable difficulty attributed to swept wings and wings with control surface deflection.
A method for accounting for the shift in the locus of aerodynamic centers is also presented and. Induced drag is caused by the downward deflection of the air streaming around the wing. The resulting aerodynamic force is tilted backwards by half the deflection angle, and the air flows off the wing with an added vertical speed component, producing sing the downwash angle means increasing both lift and the backward tilt, so the induced drag goes up with the square of the lift.
This paper examines the dynamic stalling of three wing planforms and characterises the main features of the stalling process in each case. The particular data were obtained during a three year research programme in the Department of Aerospace Engineering, University of Glasgow to collect high-resolution unsteady pressure data on the dynamic stalling characteristics of finite wing by: 2.
Bharath H. () Design of an Aircraft Wing for Given Flight Conditions and Planform by Varying Other Geometric Parameters, Thesis, Dept.
of Automotive and Aeronautical Engineering, M. Ramaiah School of Advanced Studies, Bangalore, : H. Bharath, H. Narahari, A. Sriram. A circular planform non-spinning body with an airfoil section offer advantages over a conventional wing aircraft.
One such configuration developed and produced by Geobat Flying Saucer Aviation Inc Author: Bryan Recktenwald. Aerodynamic Analysis of a Light Aircraft at Different Design Stages During the evolution of an airplane aerodynamic design, proper calculation methods and software tools should be utilized, which correspond to the airplane category and project development level.
In case of light aircraft, the general trend is the application of analytical and semi. surface, rotor blade number and planform, stabilizer sizes and planforms, basic structural and control features, noise characteristics).
The disciplinary methods applied reach from textbook methods to sophisticated numerical meth-ods (e.g. comprehensive rotor codes, CFD, FEM). At the end of the preliminary design phase the configuration is Size: 3MB. Its aerodynamic instability is impacting wing and horizontal tail design, as well as aircraft directional stability characteristics.
This paper proposes methods, developed through CFD analyses, to estimate fuselage aerodynamic drag, pitching, and yawing moment coefficients. These methods are focused on the regional turboprop aircraft by: Computational Modelling and Aerodynamic Analysis of a Conventional Flight simulators serve as a foundation to research, development, and training.
The (wing planform area). The wings are therefore representative of the entire aircraft. Relatively inaccurate simulation of pitching moment. “Aerodynamic Analysis of Aircraft Wing “VNU Journal of Science: Mathematics –Physics, Vol. 31, No. 2 () 2) Ankan Dash “CFD Analysis of Wind Turbine Airfoil at Various Angles of Attack”, IOSR Journal of Mechanical and Civil Engineering, Vol No, Issue 4() In this chapter we discuss the aerodynamics of swept wings in transonic flow.
To demonstrate the merits of swept-back wings, simple sweep theory is presented. It is shown why a swept wing can experience local supersonic flow while still being in subcritical conditions, thereby postponing the onset of strong shock waves and drag : Roelof Vos, Saeed Farokhi.
Aerodynamic Design Considerations and Shape Optimization of Flying Wings in Transonic Flight 1, 2, 3and on 1Royal Institute of Technology (KTH), Stockholm, Sweden 2Nangia Aero Research Associates, Bristol BS8 1QU, UK 3Swedish Defence Research Agency (FOI), Stockholm, Sweden This paper provides a technique that.
The aerodynamic tests on the four types of wings are under taken and the results are mentioned in the given tables. Result Analysis of all the Wings at 10 m/s Speed. Fig. Result Analysis of all the Wings at 10 m/s Speed. Result Analysis of all the Wings at 15m/s Speed.
Fig. Result Analysis of all the W ings at 15 m/s Speed. This paper presents an application for the calculation of the mean aerodynamic chord (MAC) of an arbitrary wing planform. The MAC is most often used in the aerodynamic and stability analysis.
The calculation uses a method where the MAC is defined by an array of by: 1. Human powered aircraft design is a caricature of the classic structural efficiency (thick, short wing) versus aerodynamic efficiency (thin, long wing) tradeoff. The `sport' is going through a renaissance in the UK, with the advent of the Royal Aeronautical Society's Icarus Cup, and the authors have been involved with the design of SUHPA (Southampton University.
of wings especially at low Re. Introduction The geometric parameters and kinematics of insect wings and their effects on the aerodynamic performance in hovering flight have attracted great attention in the past. However, previous studies on aerodynamic performance of wing planform shapes have shown contrasting results.
For rectangular wings, the wing ac is the same as the airfoil ac. But for wings with some other planform (triangular, trapezoidal, compound, etc.) we have to find a mean aerodynamic center (mac) which is the average for the whole wing.
The computation of the. aerodynamic prediction code. Semi-empirical methods are used to estimate the effects of vortex lift and breakdown. Output files provide information on the overall configuration, component loads, and vortex characteristics. The HASC code is primarily an integration of three routines: VORLAX: A generalized vortex lattice program.
The Aerodynamic Design of Aircraft is as relevant and as forward looking today as it was in The swept wing aircraft, in becoming the mainstay of the aerospace industry, has achieved a high degree of sophistication, but much of the nuance contained in this text, required to continue advancing these designs, is lost outside a few.
Liebrecht B., Neuwerth G., Jacob D. () Analysis of the Oblique Flying Wing Concept’s Aerodynamic Potential by Means of Parameterization and Optimization.
In: Breitsamter C., Laschka B., Heinemann HJ., Hilbig R. (eds) New Results in Numerical and Experimental Fluid Mechanics : Bastian Liebrecht, Günther Neuwerth, Dieter Jacob.
Aerodynamic Design 2/15/06 Clearly a low W/S is key a requirement for achieving a high value of rly, the takeoff distance is related to the so-called takeoff parameter, TOP, which also includes CLmax, is: TOP= (W/S)CL max (T/W)() and the landing distance can be related to the approach speed:File Size: KB.
Aerodynamics is a branch of dynamics concerned with the study of the motion of is a sub-field of fluid and gas dynamics, and the term "aerodynamics" is often used when referring to fluid dynamics. Early records of fundamental aerodynamics concepts date back to the work of Aristotle and Archimedes in the 2nd and 3rd centuries BC, but efforts to develop a quantitative theory of air flow.
Aerodynamics is the science of airflow over airplanes, cars, buildings, and other objects. Aerodynamic principles are used to find the best ways in which airplanes produce lift, reduce drag, and remain stable (by controlling the shape and size of the wing, the angle at which it is positioned with respect to the airstream, and the flight speed).
minimum induced drag over a rectangular or tapered wing configuration. 2 However, disadvantages of a circular planform aircraft include a reduced lift-curve slope and longitudinal instability.
1 Jack Jones 3, a RC model airplane enthusiast, designed, built and flew a circular wing airplane namedFile Size: KB.1. DctroductionFor combinations of bodies and wings without sweepback (i.e., straight wings) the influence of the body gives a forward movement of the aerodynamic centre of about 5 to 8 per cent.
of the mean chord. This movement of the aerodynamic centre can be calculatedFile Size: 2MB.1. Wing reference (or planform) area (S W or S ref or S) 2. Number of the wings 3. Vertical position relative to the fuselage (high, mid, or low wing) 4.
Horizontal position relative to the fuselage 5. Cross section (or airfoil) 6. Aspect ratio (AR) 7. Taper ratio () 8. Tip chord (C t) 9. Root chord (C r) Mean Aerodynamic Chord (MAC or C.