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Gustave Eiffel, a Pioneer of Aerodynamics
Int. J. Engineering Systems Modelling and Simulation, Vol. 5, Nos. 1/2/3, 2013 3 Gustave Eiffel, a pioneer of aerodynamics Bruno Chanetz* Onera, 8 rue des Vertugadins, F-92 190 Meudon, France Fax: +33-1-46-23-51-58 and University Paris-Ouest, LTIE-GTE, EA 4415, 50 rue de Sèvres, F-92410 Ville d’Avray, France Fax: +33-1-40-97-48-73 E-mail: [email protected] E-mail: [email protected] *Corresponding author Martin Peter Laboratoire Aérodynamique Eiffel, 68 rue Boileau, F-75016 Paris E-mail: [email protected] Abstract: At the beginning of the 20th century, Gustave Eiffel contributes with Ludwig Prandtl to establish a new science: aerodynamics. He was going to study the forces to which he was confronted as engineer during his life: gravity and wind. Keywords: Eiffel wind tunnel; diffuser; laminar regime; turbulent regime; transition; drag of the sphere; Eiffel chamber. Reference to this paper should be made as follows: Chanetz, B. and Peter, M. (2013) ‘Gustave Eiffel, a pioneer of aerodynamics’, Int. J. Engineering Systems Modelling and Simulation, Vol. 5, Nos. 1/2/3, pp.3–7. Biographical notes: Bruno Chanetz joins Onera in 1983 as a Research Engineer. He was the Head of Hypersonic Group in 1990, Head of Hypersonic Hyperenthalpic Project in 1997 and Head of Experimental Simulation and Physics of Fluid Unit in 1998, then Deputy Director of the Fundamental and Experimental Aerodynamics Department in 2003. He was a Lecturer in Charge of the course ‘Boundary Layer’ at the Ecole Centrale de Paris from 1996 to 2003, then Associate Professor at the University of Versailles from 2003 to 2009. -
Brief History of the Early Development of Theoretical and Experimental Fluid Dynamics
Brief History of the Early Development of Theoretical and Experimental Fluid Dynamics John D. Anderson Jr. Aeronautics Division, National Air and Space Museum, Smithsonian Institution, Washington, DC, USA 1 INTRODUCTION 1 Introduction 1 2 Early Greek Science: Aristotle and Archimedes 2 As you read these words, there are millions of modern engi- neering devices in operation that depend in part, or in total, 3 DA Vinci’s Fluid Dynamics 2 on the understanding of fluid dynamics – airplanes in flight, 4 The Velocity-Squared Law 3 ships at sea, automobiles on the road, mechanical biomedi- 5 Newton and the Sine-Squared Law 5 cal devices, and so on. In the modern world, we sometimes take these devices for granted. However, it is important to 6 Daniel Bernoulli and the Pressure-Velocity pause for a moment and realize that each of these machines Concept 7 is a miracle in modern engineering fluid dynamics wherein 7 Henri Pitot and the Invention of the Pitot Tube 9 many diverse fundamental laws of nature are harnessed and 8 The High Noon of Eighteenth Century Fluid combined in a useful fashion so as to produce a safe, efficient, Dynamics – Leonhard Euler and the Governing and effective machine. Indeed, the sight of an airplane flying Equations of Inviscid Fluid Motion 10 overhead typifies the laws of aerodynamics in action, and it 9 Inclusion of Friction in Theoretical Fluid is easy to forget that just two centuries ago, these laws were Dynamics: the Works of Navier and Stokes 11 so mysterious, unknown or misunderstood as to preclude a flying machine from even lifting off the ground; let alone 10 Osborne Reynolds: Understanding Turbulent successfully flying through the air. -
Helicopter Dynamics Concerning Retreating Blade Stall on a Coaxial Helicopter
Helicopter Dynamics Concerning Retreating Blade Stall on a Coaxial Helicopter A project presented to The Faculty of the Department of Aerospace Engineering San José State University In partial fulfillment of the requirements for the degree Master of Science in Aerospace Engineering by Aaron Ford May 2019 approved by Prof. Jeanine Hunter Faculty Advisor © 2019 Aaron Ford ALL RIGHTS RESERVED ABSTRACT Helicopter Dynamics Concerning Retreating Blade Stall on a Coaxial Helicopter by Aaron Ford A model of helicopter blade flapping dynamics is created to determine the occurrence of retreating blade stall on a coaxial helicopter with pusher-propeller in straight and level flight. Equations of motion are developed, and blade element theory is utilized to evaluate the appropriate aerodynamics. Modelling of the blade flapping behavior is verified against benchmark data and then used to determine the angle of attack distribution about the rotor disk for standard helicopter configurations utilizing both hinged and hingeless rotor blades. Modelling of the coaxial configuration with the pusher-prop in straight and level flight is then considered. An approach was taken that minimizes the angle of attack and generation of lift on the advancing side while minimizing them on the retreating side of the rotor disk. The resulting asymmetric lift distribution is compensated for by using both counter-rotating rotor disks to maximize lift on their respective advancing sides and reduce drag on their respective retreating sides. The result is an elimination of retreating blade stall in the coaxial and pusher-propeller configuration. Finally, an assessment of the lift capability of the configuration at both sea level and at “high and hot” conditions were made. -
A Method That Lends Wings
FLASHBACK_Aerodynamics A method that lends wings Mathematician Irmgard Flügge-Lotz was one of the first female researchers in the field of aerodynamics and automatic control. While working at the Kaiser Wilhelm Institute for Flow Research, she succeeded in simplifying the calculations required for aircraft construction. Flügge-Lotz was later appointed the first female Professor of Engineering at Stanford University. In the U.S., her work is still held in high esteem. In Germany, however, she has been all but forgotten. TEXT KATJA ENGEL Goettingen, 1931. Leading flow researcher could only be tested by means of complex Ludwig Prandtl was astonished. His colleague, wind tunnel measurements. Ludwig Prandtl, at 28 just half his age, had just handed him who is generally thought to be the founder of the solution to a mathematical puzzle that no- aircraft aerodynamics, and his team in Goet- body had been able to crack for more than ten tingen carried out pioneering work on the years. This conundrum was on his “menu”, as theoretical description of lift. However, math- he called his list of uncompleted research ematical calculations of his wing theory tasks. The result went down in the history of turned out to be difficult. In 1919, Albert Betz, aerodynamic research together with the a doctoral student in Goettingen who was young researcher's name. The "Lotz method" later to become Prandtl’s successor at the In- makes it possible to calculate the lift on an air- stitute, finally succeeded in the describing lift plane wing with comparative ease. by means of differential equations. However, Prandtl soon made the woman who had so his formulae were too complex for practical impressed him an (unofficial) Head of Depart- use when constructing new profiles. -
REPORT No. 201
REPORT No. 201 THE EFFECTS OF -SHIELDING THE THIS OF AIRFOILS By ELLIOTT G. IWD Langley Memorial Aeronautical Laboratory 3-M REPORT No. 201 THE EFFECTS OF SHIELDING THE TIPS OF AIRFOILS By ELLIOTT G. REID SUMMARY Tests have recently been made at Langley Memorial Aeronautical Laboratory to ascertain whet her the aerodynamic characteristics of an airfoil might be subst antiall-j -impro~ed by imposing certain limitations upon the airflow about its tips. AU of the moditied forms were slightly inferior to the plain airfoil at small lift coefikients; however, by mounting thin plates, in planes perpendicular to the span, at the W@ tips, the characteristics were impro~ed throughout the range above three-tenths of the masimum lift coefficient. With this form of limitation the detrimental effect was slight; at the higher lift .—— coefEcients there resulted a eorsiderable reduction of induced drag and, consequently, of pow-er required for sustentation. The s16pe of the curve of lift ~erws angle of attack was increased. OUTLINE OF TESTS These tests wwe directed to-ward the disco~ery of some economical means of increasing the “ effecti~e aspect ratio” of an airfol As it. is recognized that the induced drag of an airfoiI is inversely proportional to its aspect ratio and that elimination of the transverse velocity, components of the air.tlow about a wing reproduces, in effecfi, the conditions which wouId exist with Mnite aspect ratio, it was planned to investigate the effects of elimination of a portion of the transverse flow by. fln.ite barriers at. the tips and ‘also by the production of an aer~- dcynamic counterforee, in lieu of the com- straints:-by the localization of severe washout at the tzps. -
May 1983 Issue of Soaring Magazine
Cambridge Introduces The New M KIV NA V Used by winners at the: 15M French Nationals U.S. 15M Nationals U.S. Open Nationals British Open Nationals Cambridge is pleased to announce the Check These Features: MKIV NAV, the latest addition to the successful M KIV System. Digital Final Glide Computer with • "During Glide" update capability The MKIV NAV, by utilizing the latest Micro • Wind Computation capability computer and LCD technology, combines in • Distance-to-go Readout a single package a Speed Director, a • Altitude required Readout 4-Function Audio, a digital Averager, and an • Thermalling during final glide capability advanced, digital Final Glide Computer. Speed Director with The MKIV NAV is designed to operate with the MKIV Variometer. It will also function • Own LCD "bar-graph" display with a Standard Cambridge Variometer. • No effect on Variometer • No CRUISE/CLIMB switching The MKIV NAV is the single largest invest ment made by Cambridge in state-of-the-art Digital 20 second Averager with own Readout technology and represents our commitment Relative Variometer option to keeping the U.S. in the forefront of soar ing instrumentation. 4·Function Audio Altitude Compensation Cambridge Aero Instruments, Inc. Microcomputer and Custom LCD technology 300 Sweetwater Ave. Bedford, MA 01730 Single, compact package, fits 80mm (31/8") Tel. (617) 275·0889; TWX# 710·326·7588 opening Mastercharge and Visa accepted BUSINESS. MEMBER G !TORGLIDING The JOURNAL of the SOARING SOCIETYof AMERICA Volume 47 • Number 5 • May 1983 6 THE 1983 SSA INTERNATIONAL The Soaring Society of America is a nonprofit SOARING CONVENTION organization of enthusiasts who seek to foster and promote all phases of gliding and soaring on a national and international basis. -
Robins 50E ARF Scale
SebArt professional line RobinS 50E ARF scale ASSEMBLY MANUAL The real plane The Robin DR400 is a wooden sport monoplane, conceived by Pierre Robin and Jean Délémontez. The Robin with a forward-sliding canopy, the DR400 flew in 1972. It has a tricycle undercarriage, and can carry four people. The DR400 aircraft have the 'cranked wing' configuration, in which the dihedral angle of the outer wing is much greater than the inboard. This model is considered easy to fly by many and quiet during flight due to its wooden frame. The wing is a distinctive feature of this airplane; the Robin is light, stiff and strong, with the dihedral of the outer panels imparting substantial lateral stability in flight. Being fabric covered, it presents a smooth surface to aid airflow, unhindered by the typical overlapping panels or rivets found on metal aircraft. The secret to the DR400's relatively high performance lies in the pronounced washout in the outer panels. Since they have a lower angle of attack to the airflow than the centre section, they create less drag in cruise flight. Specifications: Year Built: 1968 Capacity: 4 persons Length: 6.96 m (22 ft 10 in) Wingspan: 8.72 m (28 ft 7¼ in) Wing area: 14.20 m2 (152.85 ft2) Empty weight: 600 kg (1323 lb) Powerplant: 1 × Lycoming O-360-four piston engine, 134 kW (180 hp) Performance Maximum speed: 278 km/h (173 mph) Range: 1450 km (900 miles) Service ceiling: 4715 m (15,470 ft) The model The RobinS 50E ARF scale, was designed by the 15 times Italian Champion Sebastiano Silvestri, vice-European Champion and 2 time F.A.I World Cup winner F3A. -
Ludwig Prandtl and Boundary Layers in Fluid Flow How a Small Viscosity Can Cause Large Effects
GENERAL I ARTICLE Ludwig Prandtl and Boundary Layers in Fluid Flow How a Small Viscosity can Cause large Effects Jaywant H Arakeri and P N Shankar In 1904, Prandtl proposed the concept of bound ary layers that revolutionised the study of fluid mechanics. In this article we present the basic ideas of boundary layers and boundary-layer sep aration, a phenomenon that distinguishes stream lined from bluff bodies. Jaywant Arakeri is in the Mechanical Engineering A Long-Standing Paradox Department and in the Centre for Product It is a matter of common experience that when we stand Development and in a breeze or wade in water we feel a force which is Manufacture at the Indian called the drag force. We now know that the drag is Institute of Science, caused by fluid friction or viscosity. However, for long it Bangalore. His research is was believed that the viscosity shouldn't enter the pic mainly in instability and turbulence in fluid motion. ture at all since it was so small in value for both water He is also interested in and air. Assuming no viscosity, the finest mathematical issues related to environ physicists of the 19th century constructed a large body ment and development. of elegant results which predicted that the drag on a body in steady flow would be zero. This discrepancy between ideal fluid theory or hydrodynamics and com mon experience was known as 'd' Alembert's paradox' The paradox was only resolved in a revolutionary 1904 paper by L Prandtl who showed that viscous effects, no matter how'small the viscosity, can never be neglected. -
A Method for Localizing Wing Flow Separation at Stall to Alleviate Spin Entry Tendencies
78-1476 A Method for Localizing Wing Flow Separation \* at Stall to Alleviate Spin Entry Tendencies T. W. Feistel and S. B. Anderson, NASA Ames Research Center, Moffett Field, Ca.; and R. A. Kroeger, University of Michigan, Ann Arbor, Mich. AlAA AIRCRAFT SYSTEMS AND TECHNOLOGY CONFERENCE L Los Angeles, CalifJAugust 21-23,1978 This is a US. Government work and is not copyrightable under U.S.C. 105. -- A \IETIIOD FOR 1I)CALIZING WISC fLW SEPARRTION .\T STALI TO ALI.FVIAT? SPIN ENTRY TENDENCIES T. W. Fe15t~!l' and S. B. AndersonT Am. Research Center, NASA. MJffs>tt Field. Calrforn1.3 md R. &. Krocger' university Of Mlch1g.m. Ann li-bor. Mic:irgan ABSTRACT Theoretical models of three-dimensional wings, using a nonlinear-lifting-line approach with a sim- A wing leading-edge modification has been ulated Stalled wing section, had suggested that developed, applicable at present to single-engine strong vorticity would be Shed at the edges of the light aircraft, which produces stabilizing vortices unattached section. A wind-tunnel model was fabri- at stall and beyond. These Vortices have the effect cated with partial span slats added along the of fixing the stall pattern of the wing such that entire leading-edge except for a ma11 length near the various portions of the wing upper surface stall the mid-semispan. These differences in leading- nearly symmetrically. The lift coefficient produced edge configuration were intended to produce a is essentially constant to very high angles of strong streamwise vorticity around the stalled sec- attack above the Stall angle of the unmodified wing. -
Tailless Aircraft : an Overview
o Journal of Aeronautics and Aerospace ISSN: 2168-9792 Engineering Editorial Tailless Aircraft : An Overview Srikanth Nuthanapati Department of Aeronautics, IIT Madras,Chennai,India. EDITORIAL Apart from its main wing, it lacks a tail assembly and any other Low or null pitching moment airfoils, as seen in the Horten horizontal surface. The main wing incorporates aerodynamic family of sailplanes and fighters, provide an alternative. These control and stabilisation functions in both pitch and roll. A have a unique wing segment with reflex or reverse camber on the tailless design might nevertheless feature a rudder and a vertical back or entire wing. The flatter side of the wing is on top, while fin (vertical stabiliser). Low parasitic drag, similar to the Horten the steeply curved side is on the bottom, resulting in a high angle H.IV soaring glider, and strong stealth qualities, similar to the of attack in the front part. Northrop B-2 Spirit bomber, are theoretical advantages of the Fitting large elevators to a standard airfoil and trimming them tailless configuration. The tailless delta has proven to be the considerably upwards can approximate reflex camber; the most successful tailless layout, particularly for combat aircraft, centre of gravity must also be moved forward from its normal albeit the Concorde airliner is the most well-known tailless position. Reflex camber tends to cause a tiny downthrust due to delta. the Bernoulli effect, thus the wing's angle of attack is increased A horizontal stabiliser surface separate from the main wing is to compensate. This, in turn, adds to the drag. -
Design Development and CFD Simulation of a Variable Twist Wing
Imperial Journal of Interdisciplinary Research (IJIR) Vol-3, Issue-5, 2017 ISSN: 2454-1362, http://www.onlinejournal.in Design Development and CFD Simulation of a Variable Twist Wing 1 2 3 G.Sawan Kumar , Shuvendra Mohan , R.Surendra Rao 1 Space And Astronautical Engineering, University of Sapienza, Rome, Italy 2Aeronautical Engineering, Institute of Aeronautical Engineering, Dundigal, Hyderabad, India 3Mechanical Engineering Department, Kasi reddy naryan reddy college of engineering and research, Hyderabad, India Abstract: Wing twist is an aerodynamic feature these equations are difficult to solve. For a wing to added to aircraft wings to adjust lift distribution produce "lift", it must be oriented at a suitable angle along the wing. Often, the purpose of lift of attack relative to the flow of air past the wing. redistribution is to ensure that load distribution is When this occurs the wing deflects the airflow uniform from wing tip to root, it ensures that the downwards, "turning" the air as it passes the wing. effective angle of attack is always lower at the wing Since the wing exerts a force on the air to change its tip than at the root, meaning the root will stall before direction, the air must exert a force on the wing, the tip. This is desirable because the aircraft's flight equal in size but opposite in direction. This force control surfaces are often located at the wingtip, and manifests itself as differing air pressures at different the variable stall characteristics of a twisted wing points on the surface of the wing. alert the pilot to the advancing stall while still A region of lower-than-normal air pressure is allowing the control surfaces to remain effective, generated over the top surface of the wing, with a meaning the pilot can usually prevent the aircraft higher pressure existing on the bottom of the wing. -
Chapter on Prandtl
2 Prandtl and the Gottingen¨ school Eberhard Bodenschatz and Michael Eckert 2.1 Introduction In the early decades of the 20th century Gottingen¨ was the center for mathemat- ics. The foundations were laid by Carl Friedrich Gauss (1777–1855) who from 1808 was head of the observatory and professor for astronomy at the Georg August University (founded in 1737). At the turn of the 20th century, the well- known mathematician Felix Klein (1849–1925), who joined the University in 1886, established a research center and brought leading scientists to Gottingen.¨ In 1895 David Hilbert (1862–1943) became Chair of Mathematics and in 1902 Hermann Minkowski (1864–1909) joined the mathematics department. At that time, pure and applied mathematics pursued diverging paths, and mathemati- cians at Technical Universities were met with distrust from their engineering colleagues with regard to their ability to satisfy their practical needs (Hensel, 1989). Klein was particularly eager to demonstrate the power of mathematics in applied fields (Prandtl, 1926b; Manegold, 1970). In 1905 he established an Institute for Applied Mathematics and Mechanics in Gottingen¨ by bringing the young Ludwig Prandtl (1875–1953) and the more senior Carl Runge (1856– 1927), both from the nearby Hanover. A picture of Prandtl at his water tunnel around 1935 is shown in Figure 2.1. Prandtl had studied mechanical engineering at the Technische Hochschule (TH, Technical University) in Munich in the late 1890s. In his studies he was deeply influenced by August Foppl¨ (1854–1924), whose textbooks on tech- nical mechanics became legendary. After finishing his studies as mechanical engineer in 1898, Prandtl became Foppl’s¨ assistant and remained closely re- lated to him throughout his life, intellectually by his devotion to technical mechanics and privately as Foppl’s¨ son-in-law (Vogel-Prandtl, 1993).