3 edition of Aerodynamic characteristics of a distinct wing-body configuration at Mach 6 found in the catalog.
Aerodynamic characteristics of a distinct wing-body configuration at Mach 6
1985 by National Aeronautics and Space Administration, Scientific and Technical Information Branch, National Technical Information Service, distributor] in [Washington, DC], [Springfield, Va .
Written in English
|Statement||Jim A. Penland and James L. Pittman.|
|Series||NASA technical paper -- 2467.|
|Contributions||Pittman, Jimmy L., United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.|
|The Physical Object|
RANS-based Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft. Title: RANS-based Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft: Publication Type: Conference Papers: Year of Publication: Authors: Lyu, Z, Martins, JRRA: Conference Name: 43rd AIAA Fluid Dynamics Conference and Exhibit. For a blended-wing-body aircraft cruising at Mach , a reduction in induced and wave drag of almost 40%, relative to the baseline geometry, is achieved at the target lift coe - cient. A partial section optimization results in more than 50% drag reduction relative to the baseline geometry. Nomenclature ↵ Angle of attack, degrees CL Lift.
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Book Title: Aerodynamic Characteristics of a Distinct Wing body Configuration at Mach 6 Experiment Theory and the Hypersonic Isolation Principle Author: Jim Aerodynamic characteristics of a distinct wing-body configuration at Mach 6 book.
Penland Publisher: Release Date: Pages: 35 ISBN: NASA Available Language: English, Spanish, And French. Get this from a library. Aerodynamic characteristics of a distinct wing-body configuration at Mach 6: experiment, theory, and the hypersonic isolation principle.
[Jim A Penland; Jimmy L Pittman; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.]. ance characteristics of aircraft configurations for Mach numbers up to and greater than 4.
Reference 1 presents the results of a study of the effects of wing planform on the longitudinal and lateral characteristics of a wing-body-tail configuration for angles of attack up to about 26O at Mach numbers from to File Size: 5MB. Longitudinal Aerodynamic Characteristics and Wing Pressure Distributions of a Blended-Wing-Body Configuration at Low and High Reynolds Numbers Richard J.
Re Langley Research Center, Hampton, Virginia MAC mean aerodynamic chord, in. M free-stream Mach number NTF National Transonic Facility q free-stream dynamic pressure, psi R. EFFECT OF NACELLE ORIENTATION ON THE AERODYNAMIC CHARClCTEiUSTICS OF AN ARROW WING-BODY CONFIGURATION Aerodynamic characteristics of a distinct wing-body configuration at Mach 6 book MACH NUMBER By Ehna Jean Landrum Langley Research Center SUMMARY The investigation was performed in the Langley 4-by 4-foot supersonic pressure tunnel at a Reynolds number based on the wing mean aerodynamic File Size: KB.
These aerodynamic characteristics will be used to assess the acceptability and viability of the concept through simulator and mission studies. The parametric tests included configuration buildup and elevon and rudder deflection.
Most of the study was conducted at Mach. Investigations on Missile Configuration Aerodynamic Characteristics for Design Optimization Wing-body-tail configuration.
to examine the aerodynamic characteristics of a one-third-scale. The tests were conducted in the Langley foot transonic tunnel at Mach numbers from to and at angles of attack from 0 deg.
to 14 deg., with Reynolds numbers based on Aerodynamic characteristics of a distinct wing-body configuration at Mach 6 book aerodynamic chord varying from 7 x 10(exp 6) to 8 x 10(exp 6).
Report presenting an investigation to determine the aerodynamic characteristics of a cruciform 70 degree delta-wing missile configuration with 70 degree delta canard control surfaces at M = in the 4- by 4-foot supersonic pressure tunnel.
Modifications to the configuration included variation of the body length and canard area and the substitution of a Author: M. Leroy Spearman, Ross B. Robinson. Aerodynamic characteristics of lambda wings tests on a 3D half wing-body configuration are presented for several freestream Mach numbers (–) and Reynolds numbers ( ×.
Aerodynamic Shape Optimization of the Common Research Model Wing-Body-Tail Conﬁguration Song Chen, Zhoujie Lyuy, Gaetan K. Kenwayz, and Joaquim R. Martinsx Department of Aerospace Engineering, University of Michigan, Ann Arbor, MI Wing shape is one of the main drivers of aircraft aerodynamic performance, so most aerodynamic.
computational aerodynamic Analysis of BWB at subsonic speeds using Ansys CFD as a simulation tool and ICEM CFD as modeling tool at different angle of attacks and freestream velocities.
The study will focus on the aerodynamic characteristics such as mach number and pressure variation. Langley Research Center: Aeordynamic characteristics of a distinct wing-body configuration at Mach 6: experiment, theory, and the hypersonic isolation principle / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch.
Aerodynamic Characteristics at Mach L60,and of a Cruciform Missile Configuration With In-Line Tail Controls. NASA TM X»ni2, UL luller, Dennis E.; and Corlett, William A.: Supersonic Aerodynamic Characteristics of a Cruciform Missile Configuration With Low-Aspect-Ratio Wings and In-Line Tail Controls.
Aerodynamic characteristics of a distinct wing-body configuration at Mach 6 book NASA TM X, In a recent paper, Roman et al. studied the aerodynamic behaviour of a blended wing body aircraft at high transonic speed and concluded that a Mach number of is feasible with a performance penalty relative to Mach designs.
In particular, a 10% reduction in ML/D was observed for the by: Combining wing and body in the blended-wing-body configuration is an innovative idea which benefits from its inherent aerodynamic potential. However, it needs creative and careful revision at its stage of evolution as a proper candidate for the future generation of commercial by: 8.
AERODYNAMIC STUDY OF A BLENDED WING BODY; COMPARISON WITH A CONVENTIONAL TRANSPORT AIRPLANE Cross-sectional area variation 0,0 0,2 0,4 0,6 0,8 1,0 x A r e a / A m a x The results of model 4 are: • ML/D = • MP/D = • D = kN • C = 13 kg Model 5 In this last model the wingspan has grown to the prefixed maximum of 70 m.
A Basic Aerodynamics Project for a simple wing-body configuration and a Triangular–Wing and Body Combination at Mach Numbers from to ,” NASA TN D, Juneas the basis for this project. Figure 1. Swept Wing-Body Model tested with results presented in. Report presenting an experimental investigation to determine the effects of vertical location of an unswept wing and horizontal tail on the aerodynamic characteristics in pitch of a wing-body-tail combination.
The wings had an aspect ratio ofa taper ratio ofthe quarter-chord line swept back degrees, and biconvex sections. 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 a plane parallel to the x-z plane of the aircraft, the intersection of the wing surfaces with that plane is called an airfoil. This airfoil shape can beFile Size: KB.
The aerodynamic characteristics such as lift co-efficient and drag coefficient are calculated and compared. of Blended Wing Body Unmanned Aerial Vehicle at Mach and Mach ,” 13th International Conference on Aerospace Science and Aviation Technology, May T. Ikeda, C.
Bil,“Aerodynamic Performance of a Blended. Report presenting an investigation to determine the aerodynamic characteristics of a cruciform 70 degree delta-wing missile configuration with 70 degree delta canard control surfaces at M = in the 4- by 4-foot supersonic pressure tunnel.
Modifications to the configuration included variation of the body length and canard area and the substitution of a series of very small span. Aerodynamic Shape Optimization of Wing and Wing-Body Configurations Using Control Theory J. Reuther, RIACS, NASA Ames Research Center, Moffett Field, CA and A.
Jam eson, Princeton University, Princeton, NJ 33rd Aerospace Sciences Meeting and Exhibit January. The main purpose of the paper is to study the aerodynamic and stability characteristics of a blended-wing-body (BWB) aircraft.
This paper presents the estimation and selection of aircraft design parameters, planform design, reflex airfoils, and conduct thorough stability investigation of the aircraft. A conceptual design of BWB aircraft has been done and Author: Sanjiv Paudel, Shailendra Rana, Saugat Ghimire, Kshitiz Kumar Subedi, Sudip Bhattrai.
capital cities (hubs). A configuration that shows promise in terms of improved efficiency over conventional configurations is the Blended-Wing-Body (BWB) concept. Fig.1 Image of BWB Concept Aircraft The BWB concept design was analysed an aerodynamic feature using Computational Fluid Dynamics (CFD) based on the structural weight.
Aerodynamic Performance of Wing-Body Configurations and the Flying Wing An elementary analysis has been made of generic wing-body configurations with variable volume allotment in wing and body, for constant total Cited by: 8.
Mach number of with a fixedC L of An optional objective is to reduce the sonic boom at Mach number of with a fixed C L of Design specification of the present SST wing-body configuration is describe d in Table 1.
The constraints are given based on the conceptual design for SST. Table 1 Target SST wing -body specification. The variation of CL, CD, end Cm, for the delta wing-body ccmbination atM = 2d The variation of CL, CD, and Cm, for the swept wing-body combination at hl = I 2e Th;tvhy2aFg of CL, CD, and Cm, for the swept vrmg-body ccmblnatun.
2f The effect of bcdy length and ncse shape on the lncrcments 3.n. configuration of WIG crafts experimentally and theoretically is investigated to improve their aerodynamic performance.
The principal means to develop lifting force is the ram effect; lift is improved when flow underneath the wing body around stagnation point on the pressure surface (lower surface of body) is trapped. 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.
A passenger BWB with a distributed propulsion system configuration is carried out and its aerodynamic performance in cruising and taking off are analyzed and discussed. It is shown from computation that the integrated configuration has a commendable aerodynamic performance in cruising and taking off.
The cruise lift to drag ratio is reach to in by: 1. Aerodynamic analysis of a blended-wing-body aircraft configuration Author(s) Ikeda, T: Year Australia was modelled, and its aerodynamic characteristics assessed using CFD to enable comparison with the BWB design. The BWB design had to be compatible with airports that took conventional aircraft, meaning a wingspan of not more than [Mason] transonic aerodynamics of airfoils and wings 1.
W.H. Mason 4/12/04 7. Transonic Aerodynamics of Airfoils and Wings Introduction Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = or to ). Khalid, A., & Kumar, P. Aerodynamic Optimization of Box Wing – A Case Study.
International Journal of Aviation, Aeronautics, and Aerospace, 1(4). Retrieved from vol1/iss4/6 This Article is brought to you for free and open access by the Journals at Scholarly Commons.
It has been. 4 Challenges and Complexity of Aerodynamic Wing Design coordinates (x1;x2;x3), E is the total energy, and ij is the Kronecker delta function.
The pressure is determined by the equation of state p= (1)ˆ ˆ E 1 2 (uiui) ˙; and the stagnation enthalpy is File Size: KB. Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft Configuration by Nimeesha B. Kuntawala A thesis submitted in conformity with the requirements for the degree of Masters of Applied Science Mach number distribution over the top and bottom (inset) surfaces of theCited by: 1.
Aerodynamic Characteristics at M = of Monoplane, Triform and Cruciform Slender Delta Wing was made at a Mach number of in a small, 11 inch x 6 inch, supersonic wind tunnel at R.A.E.
Farnborough. examined for the various wing body combinations. Appendix A. The nonlinear behaviour stems from the effect of Mach number in the transonic regime and from the aerodynamic characteristics of the FTB_1 low aspect ratio, lifting-body configuration.
The parameters of the aerodynamic model are firstly determined before flight, fitting a pre-flight aerodynamic database, built upon wind-tunnel test data and. The writing style is intentionally conversational in order to make the book easier to read.
The book is designed to talk to the reader; in part to be a self-teaching instrument. Learning objectives have been added to each chapter to reflect what is believed to be the most important items to learn from that particular chapter.
Since the education of aeronautical engineers at Delft University of Technology started in under the inspiring leadership of Professor H.J. van der Maas, much emphasis has been placed on the design of aircraft as part of the student's curriculum.
Not. Title: Utilization of pdf Wing-Body Aerodynamic Analysis Program Author: Robert E. Curry Subject: NASA TM Keywords: Computational aerodynamics, Woodward panel method, Wake vortex upsets, F TACT airplane.$\begingroup$ @JayCarr From Wikipedia: "The aerodynamic center is the point at which the pitching moment coefficient for the download pdf does not vary with lift coefficient (i.e.
angle of attack), so this choice makes analysis simpler." I personally had never heard of the term and was surprised to find so much on it when I Googled "aerodynamic center.".Aerodynamic characteristics of ebook deg delta wing at steep spin.
T. Yamada and; Y. Nakamura; Comparison of two distinct models of rotor wakes with experiment. S. Kini, A. Conlisk and; Aeroheating predictions for the X hyper-X cowl-closed configuration at Mach 7 and C.
Cockre, A. Auslender, J. White and.