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Soaring Weather
Chapter 16 SOARING WEATHER While horse racing may be the "Sport of Kings," of the craft depends on the weather and the skill soaring may be considered the "King of Sports." of the pilot. Forward thrust comes from gliding Soaring bears the relationship to flying that sailing downward relative to the air the same as thrust bears to power boating. Soaring has made notable is developed in a power-off glide by a conven contributions to meteorology. For example, soar tional aircraft. Therefore, to gain or maintain ing pilots have probed thunderstorms and moun altitude, the soaring pilot must rely on upward tain waves with findings that have made flying motion of the air. safer for all pilots. However, soaring is primarily To a sailplane pilot, "lift" means the rate of recreational. climb he can achieve in an up-current, while "sink" A sailplane must have auxiliary power to be denotes his rate of descent in a downdraft or in come airborne such as a winch, a ground tow, or neutral air. "Zero sink" means that upward cur a tow by a powered aircraft. Once the sailcraft is rents are just strong enough to enable him to hold airborne and the tow cable released, performance altitude but not to climb. Sailplanes are highly 171 r efficient machines; a sink rate of a mere 2 feet per second. There is no point in trying to soar until second provides an airspeed of about 40 knots, and weather conditions favor vertical speeds greater a sink rate of 6 feet per second gives an airspeed than the minimum sink rate of the aircraft. -
5.2 Drag Reduction Through Higher Wing Loading David L. Kohlman
5.2 Drag Reduction Through Higher Wing Loading David L. Kohlman University of Kansas |ntroduction The wing typically accounts for almost half of the wetted area of today's production light airplanes and approximately one-third of the total zero-lift or parasite drag. Thus the wing should be a primary focal point of any attempts to reduce drag of light aircraft with the most obvious configuration change being a reduction in wing area. Other possibilities involve changes in thickness, planform, and airfoil section. This paper will briefly discuss the effects of reducing wing area of typical light airplanes, constraints involved, and related configuration changes which may be necessary. Constraints and Benefits The wing area of current light airplanes is determined primarily by stall speed and/or climb performance requirements. Table I summarizes the resulting wing loading for a representative spectrum of single-engine airplanes. The maximum lift coefficient with full flaps, a constraint on wing size, is also listed. Note that wing loading (at maximum gross weight) ranges between about 10 and 20 psf, with most 4-place models averaging between 13 and 17. Maximum lift coefficient with full flaps ranges from 1.49 to 2.15. Clearly if CLmax can be increased, a corresponding decrease in wing area can be permitted with no change in stall speed. If total drag is not increased at climb speed, the change in wing area will not adversely affect climb performance either and cruise drag will be reduced. Though not related to drag, it is worthy of comment that the range of wing loading in Table I tends to produce a rather uncomfortable ride in turbulent air, as every light-plane pilot is well aware. -
Conceptual Design Study of a Hydrogen Powered Ultra Large Cargo Aircraft
Conceptual Design Study of a Hydrogen Powered Ultra Large Cargo Aircraft R.A.J. Jansen University of Technology Technology of University Delft Delft Conceptual Design Study of a Hydrogen Powered Ultra Large Cargo Aircraft Towards a competitive and sustainable alternative of maritime transport by R.A.J. Jansen to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Tuesday January 10, 2017 at 9:00 AM. Student number: 4036093 Thesis registration: 109#17#MT#FPP Project duration: January 11, 2016 – January 10, 2017 Thesis committee: Dr. ir. G. La Rocca, TU Delft, supervisor Dr. A. Gangoli Rao, TU Delft Dr. ir. H. G. Visser, TU Delft An electronic version of this thesis is available at http://repository.tudelft.nl/. Acknowledgements This report presents the research performed to complete the master track Flight Performance and Propulsion at the Technical University of Delft. I am really grateful to the people who supported me both during the master thesis as well as during the rest of my student life. First of all, I would like to thank my supervisor, Gianfranco La Rocca. He supported and motivated me during the entire graduation project and provided valuable feedback during all the status meeting we had. I would also like to thank the exam committee, Arvind Gangoli Rao and Dries Visser, for their flexibility and time to assess my work. Moreover, I would like to thank Ali Elham for his advice throughout the project as well as during the green light meeting. Next to these people, I owe also thanks to the fellow students in room 2.44 for both their advice, as well as the enjoyable chats during the lunch and coffee breaks. -
Airframe Integration
Aerodynamic Design of the Hybrid Wing Body Propulsion- Airframe Integration May-Fun Liou1, Hyoungjin Kim2, ByungJoon Lee3, and Meng-Sing Liou4 NASA Glenn Research Center, Cleveland, Ohio, 44135 Abstract A hybrid wingbody (HWB) concept is being considered by NASA as a potential subsonic transport aircraft that meets aerodynamic, fuel, emission, and noise goals in the time frame of the 2030s. While the concept promises advantages over conventional wing-and-tube aircraft, it poses unknowns and risks, thus requiring in-depth and broad assessments. Specifically, the configuration entails a tight integration of the airframe and propulsion geometries; the aerodynamic impact has to be carefully evaluated. With the propulsion nacelle installed on the (upper) body, the lift and drag are affected by the mutual interference effects between the airframe and nacelle. The static margin for longitudinal stability is also adversely changed. We develop a design approach in which the integrated geometry of airframe (HWB) and propulsion is accounted for simultaneously in a simple algebraic manner, via parameterization of the planform and airfoils at control sections of the wingbody. In this paper, we present the design of a 300-passenger transport that employs distributed electric fans for propulsion. The trim for stability is achieved through the use of the wingtip twist angle. The geometric shape variables are determined through the adjoint optimization method by minimizing the drag while subject to lift, pitch moment, and geometry constraints. The design results clearly show the influence on the aerodynamic characteristics of the installed nacelle and trimming for stability. A drag minimization with the trim constraint yields a reduction of 10 counts in the drag coefficient. -
Hang Glider: Range Maximization the Problem Is to Compute the flight Inputs to a Hang Glider So As to Provide a Maximum Range flight
Hang Glider: Range Maximization The problem is to compute the flight inputs to a hang glider so as to provide a maximum range flight. This problem first appears in [1]. The hang glider has weight W (glider plus pilot), a lift force L acting perpendicular to its velocity vr relative to the air, and a drag force D acting in a direction opposite to vr. Denote by x the horizontal position of the glider, by vx the horizontal component of the absolute velocity, by y the vertical position, and by vy the vertical component of absolute velocity. The airmass is not static: there is a thermal just 250 meters ahead. The profile of the thermal is given by the following upward wind velocity: 2 2 − x −2.5 x u (x) = u e ( R ) 1 − − 2.5 . a m R We take R = 100 m and um = 2.5 m/s. Note, MKS units are used through- out. The upwind profile is shown in Figure 1. Letting η denote the angle between vr and the horizontal plane, we have the following equations of motion: 1 x˙ = vx, v˙x = m (−L sin η − D cos η), 1 y˙ = vy, v˙y = m (L cos η − D sin η − W ) with q vy − ua(x) 2 2 η = arctan , vr = vx + (vy − ua(x)) , vx 1 1 L = c ρSv2,D = c (c )ρSv2,W = mg. 2 L r 2 D L r The glider is controlled by the lift coefficient cL. The drag coefficient is assumed to depend on the lift coefficient as 2 cD(cL) = c0 + kcL where c0 = 0.034 and k = 0.069662. -
Tinamiformes – Falconiformes
LIST OF THE 2,008 BIRD SPECIES (WITH SCIENTIFIC AND ENGLISH NAMES) KNOWN FROM THE A.O.U. CHECK-LIST AREA. Notes: "(A)" = accidental/casualin A.O.U. area; "(H)" -- recordedin A.O.U. area only from Hawaii; "(I)" = introducedinto A.O.U. area; "(N)" = has not bred in A.O.U. area but occursregularly as nonbreedingvisitor; "?" precedingname = extinct. TINAMIFORMES TINAMIDAE Tinamus major Great Tinamou. Nothocercusbonapartei Highland Tinamou. Crypturellus soui Little Tinamou. Crypturelluscinnamomeus Thicket Tinamou. Crypturellusboucardi Slaty-breastedTinamou. Crypturellus kerriae Choco Tinamou. GAVIIFORMES GAVIIDAE Gavia stellata Red-throated Loon. Gavia arctica Arctic Loon. Gavia pacifica Pacific Loon. Gavia immer Common Loon. Gavia adamsii Yellow-billed Loon. PODICIPEDIFORMES PODICIPEDIDAE Tachybaptusdominicus Least Grebe. Podilymbuspodiceps Pied-billed Grebe. ?Podilymbusgigas Atitlan Grebe. Podicepsauritus Horned Grebe. Podicepsgrisegena Red-neckedGrebe. Podicepsnigricollis Eared Grebe. Aechmophorusoccidentalis Western Grebe. Aechmophorusclarkii Clark's Grebe. PROCELLARIIFORMES DIOMEDEIDAE Thalassarchechlororhynchos Yellow-nosed Albatross. (A) Thalassarchecauta Shy Albatross.(A) Thalassarchemelanophris Black-browed Albatross. (A) Phoebetriapalpebrata Light-mantled Albatross. (A) Diomedea exulans WanderingAlbatross. (A) Phoebastriaimmutabilis Laysan Albatross. Phoebastrianigripes Black-lootedAlbatross. Phoebastriaalbatrus Short-tailedAlbatross. (N) PROCELLARIIDAE Fulmarus glacialis Northern Fulmar. Pterodroma neglecta KermadecPetrel. (A) Pterodroma -
B-52, the “Stratofortress”
B-52, The “StratoFortress” Aerodynamics and Performance Build-up Service • Crew – Upper Deck • 2 Pilots • Electronic Warfare Officer • Latest Model – Lower Deck – B-52H • Bombardier – Last B-52H delivered in 1962 • Radar Navigator • Transonic Bomber – Nuclear Payload capable • Deployment – 20 Cruise Missiles – 102 B-52H’s • AGM-86C – 192 B-52G’s • AGM-12 Have Nap • AGM-84 Harpoon – All in Service of USAF as – Up to 50,000 lb ordnance far as we can tell payload – $53.4 million each [1998$] – 51 bombs of 750-lb class Additional Payload • In addition to attack ordnance, B-52H carries: – Norden APQ-156 Multi-mode targeting radar – Terrain Avoidance Radar – Electro-Optical Viewing System (EVS) • Infra-red and low light display used in conjunction with terrain avoidance sensors to navigate in bad weather at low altitudes, or with the nuclear windscreen shielding in place – ECM • ALT-28 jammer • ALQ-117, -115, -172 deception jammers – Optional Stinger Air to Air missiles in aft gun-turret Weight Breakdown • Max TOGW – 505,000 lb • Fuel Weight – 299,434 lb internal – 9,114 lb on non-jettisonable under- wing pylons • Ordnance Weight – 50,000 lb • Airframe operational empty – 146452 lb Basic Geometry • Length: 160.9 ft • Tail Plane • Wing – Horizontal Tail Span: – Span: 185 ft 55.625 ft – Horizontal Tail Plan Area: – Area: 4000 ft^2 ~1004 ft^2 – Root Chord: ~34.5 ft – Mean Chord: 21.62 ft – Vertical Tail Height: – Taper Ratio: 0.37 24.339 ft – Leading Edge Sweep: – Vertical Tail Plan Area: 35° ~451 ft^2 – AR: 8.56 Wing Geometry • Wing Root: 14% -
MAGNIFICENT FRIGATEBIRD Fregata Magnificens
PALM BEACH DOLPHIN PROJECT FACT SHEET The Taras Oceanographic Foundation 5905 Stonewood Court - Jupiter, FL 33458 - (561-762-6473) [email protected] MAGNIFICENT FRIGATEBIRD Fregata magnificens CLASS: Aves ORDER: Suliformes FAMILY: Fregatidae GENUS: Fregata SPECIES: magnificens A long-winged, fork-tailed bird of tropical oceans, the Magnificent Frigatebird is an agile flier that snatches food off the surface of the ocean and steals food from other birds. It breeds mostly south of the United States, but wanders northward along the coasts during nonbreeding season. Physical Appearance: Frigate birds are the only seabirds where the male and female look strikingly different. All have pre- dominantly black plumage, long, deeply forked tails and long hooked bills. Females have white underbellies and males have a distinctive red throat pouch, which they inflate during the breeding season to attract females Their wings are long and pointed and can span up to 2.3 meters (7.5 ft), the largest wing area to body weight ratio of any bird. These birds are about 35-45 inches ((89 to 114 cm) in length, and weight between 35 and 67 oz (1000-1900 g). The bones of frigate birds are markedly pneumatic (filled with air), making them very light and contribute only 5% to total body weight. The pectoral girdle (shoulder joint) is strong as its bones are fused. Habitat: Frigate birds are found across all tropical oceans. Breeding habitats include mangrove cays on coral reefs, and decidu- ous trees and bushes on dry islands. Feeding range while breeding includes shallow water within lagoons, coral reefs, and deep ocean out of sight of land. -
Subsonic Aircraft Wing Conceptual Design Synthesis and Analysis
View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by GSSRR.ORG: International Journals: Publishing Research Papers in all Fields International Journal of Sciences: Basic and Applied Research (IJSBAR) ISSN 2307-4531 (Print & Online) http://gssrr.org/index.php?journal=JournalOfBasicAndApplied --------------------------------------------------------------------------------------------------------------------------- Subsonic Aircraft Wing Conceptual Design Synthesis and Analysis Abderrahmane BADIS Electrical and Electronic Communication Engineer from UMBB (Ex.INELEC) Independent Electronics, Aeronautics, Propulsion, Well Logging and Software Design Research Engineer Takerboust, Aghbalou, Bouira 10007, Algeria [email protected] Abstract This paper exposes a simplified preliminary conceptual integrated method to design an aircraft wing in subsonic speeds up to Mach 0.85. The proposed approach is integrated, as it allows an early estimation of main aircraft aerodynamic features, namely the maximum lift-to-drag ratio and the total parasitic drag. First, the influence of the Lift and Load scatterings on the overall performance characteristics of the wing are discussed. It is established that the optimization is achieved by designing a wing geometry that yields elliptical lift and load distributions. Second, the reference trapezoidal wing is considered the base line geometry used to outline the wing shape layout. As such, the main geometrical parameters and governing relations for a trapezoidal wing are -
F—18 Navy Air Combat Fighter
74 /2 >Af ^y - Senate H e a r tn ^ f^ n 12]$ Before the Committee on Appro priations (,() \ ER WIIA Storage ime nts F EB 1 2 « T H e -,M<rUN‘U«sni KAN S A S S F—18 Na vy Air Com bat Fighter Fiscal Year 1976 th CONGRESS, FIRS T SES SION H .R . 986 1 SPECIAL HEARING F - 1 8 NA VY AIR CO MBA T FIG H TER HEARING BEFORE A SUBC OMMITTEE OF THE COMMITTEE ON APPROPRIATIONS UNITED STATES SENATE NIN ETY-FOURTH CONGRESS FIR ST SE SS IO N ON H .R . 9 8 6 1 AN ACT MAKIN G APP ROPR IA TIO NS FO R THE DEP ARTM EN T OF D EFEN SE FO R T H E FI SC AL YEA R EN DI NG JU N E 30, 1976, AND TH E PE RIO D BE GIN NIN G JU LY 1, 1976, AN D EN DI NG SEPT EM BER 30, 1976, AND FO R OTH ER PU RP OSE S P ri nte d fo r th e use of th e Com mittee on App ro pr ia tio ns SPECIAL HEARING U.S. GOVERNM ENT PRINT ING OFF ICE 60-913 O WASHINGTON : 1976 SUBCOMMITTEE OF THE COMMITTEE ON APPROPRIATIONS JOHN L. MCCLELLAN, Ark ans as, Chairman JOH N C. ST ENN IS, Mississippi MILTON R. YOUNG, No rth D ako ta JOH N O. P ASTORE, Rhode Island ROMAN L. HRUSKA, N ebraska WARREN G. MAGNUSON, Washin gton CLIFFORD I’. CASE, New Je rse y MIK E MANSFIEL D, Montana HIRAM L. -
The Influence of Wing Loading on Turbofan Powered Stol Transports with and Without Externally Blown Flaps
https://ntrs.nasa.gov/search.jsp?R=19740005605 2020-03-23T12:06:52+00:00Z NASA CONTRACTOR NASA CR-2320 REPORT CXI CO CNI THE INFLUENCE OF WING LOADING ON TURBOFAN POWERED STOL TRANSPORTS WITH AND WITHOUT EXTERNALLY BLOWN FLAPS by R. L. Morris, C. JR. Hanke, L. H. Pasley, and W. J. Rohling Prepared by THE BOEING COMPANY WICHITA DIVISION Wichita, Kans. 67210 for Langley Research Center NATIONAL AERONAUTICS AND SPACE ADMINISTRATION • WASHINGTON, D. C. • NOVEMBER 1973 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA CR-2320 4. Title and Subtitle 5. Reoort Date November. 1973 The Influence of Wing Loading on Turbofan Powered STOL Transports 6. Performing Organization Code With and Without Externally Blown Flaps 7. Author(s) 8. Performing Organization Report No. R. L. Morris, C. R. Hanke, L. H. Pasley, and W. J. Rohling D3-8514-7 10. Work Unit No. 9. Performing Organization Name and Address The Boeing Company 741-86-03-03 Wichita Division 11. Contract or Grant No. Wichita, KS NAS1-11370 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Contractor Report National Aeronautics and Space Administration Washington, D.C. 20546 14. Sponsoring Agency Code 15. Supplementary Notes This is a final report. 16. Abstract The effects of wing loading on the design of short takeoff and landing (STOL) transports using (1) mechanical flap systems, and (2) externally blown flap systems are determined. Aircraft incorporating each high-lift method are sized for Federal Aviation Regulation (F.A.R.) field lengths of 2,000 feet, 2,500 feet, and 3,500 feet, and for payloads of 40, 150, and 300 passengers, for a total of 18 point-design aircraft. -
Design Study of a Supersonic Business Jet with Variable Sweep Wings
27TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES DESIGN STUDY OF A SUPERSONIC BUSINESS JET WITH VARIABLE SWEEP WINGS E.Jesse, J.Dijkstra ADSE b.v. Keywords: swing wing, supersonic, business jet, variable sweepback Abstract A design study for a supersonic business jet with variable sweep wings is presented. A comparison with a fixed wing design with the same technology level shows the fundamental differences. It is concluded that a variable sweep design will show worthwhile advantages over fixed wing solutions. 1 General Introduction Fig. 1 Artist impression variable sweep design AD1104 In the EU 6th framework project HISAC (High Speed AirCraft) technologies have been studied to enable the design and development of an 2 The HISAC project environmentally acceptable Small Supersonic The HISAC project is a 6th framework project Business Jet (SSBJ). In this context a for the European Union to investigate the conceptual design with a variable sweep wing technical feasibility of an environmentally has been developed by ADSE, with support acceptable small size supersonic transport from Sukhoi, Dassault Aviation, TsAGI, NLR aircraft. With a budget of 27.5 M€ and 37 and DLR. The objective of this was to assess the partners in 13 countries this 4 year effort value of such a configuration for a possible combined much of the European industry and future SSBJ programme, and to identify critical knowledge centres. design and certification areas should such a configuration prove to be advantageous. To provide a framework for the different studies and investigations foreseen in the HISAC This paper presents the resulting design project a number of aircraft concept designs including the relevant considerations which were defined, which would all meet at least the determined the selected configuration.