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Friday, May 1, 2020 | History

3 edition of Development of a low-aspect ratio fin for flight research experiments found in the catalog.

Development of a low-aspect ratio fin for flight research experiments

Development of a low-aspect ratio fin for flight research experiments

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  • 28 Currently reading

Published 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

    Subjects:
  • F-15 aircraft.,
  • Fins.,
  • Flight test vehicles.,
  • Flight tests.,
  • Ground tests.,
  • Low aspect ratio.

  • Edition Notes

    Other titlesDevelopment of a low aspect ratio fin for flight research experiments
    StatementDavid M. Richwine, John H. Del Frate.
    SeriesNASA technical memorandum -- 4596
    ContributionsDel Frate, John H., United States. National Aeronautics and Space Administration. Scientific and Technical Information Program
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17114754M

      From the moment flying saucers were first seen in there’s been an effort to understand them and duplicate the reported flight performance. There have been many independent efforts ranging from the sincere to the fraudulent, but that’s not .


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Development of a low-aspect ratio fin for flight research experiments Download PDF EPUB FB2

Research systems, but it is smaller, lighter, and has less aerodynamic frontal drag than an empty gal centerline tank that is routinely carried by an F aircraft. The FTF-II is a low-aspect ratio fin-like shape similar to the original FTF, but is larger to allow more volume and surface area for aerodynamic experiments.

The new fixture, a low-aspect ratio vertical fin shape mounted on the centerline of an FB aircraft lower fuselage, is designed for flight research at Mach numbers up to The new fixture is a composite structure with a modular configuration and. Low Aspect Ratio Aerodynamics at Low Reynolds Numbers.

Development and experiments of a bio-inspired robot with multi-mode in aerial and terrestrial locomotion. 29 July | Bioinspiration & Biomimetics, Vol. 14, No. 5 Formation Flight of Low-Aspect-Ratio Wings at Low Reynolds by: Development of a Low-Cost Sub-Scale Aircraft for Flight Research: The FASER Project.

This paper studies low-aspect-ratio (A) rectangular wings at high incidence and in side-slip. The main objective is to incorporate the effects of high angle of attack and side-slip into a.

The ratio of the square of the span of an airfoil to the total airfoil area, or the ratio of its span to its mean chord. An airfoil of high aspect ratio is of relatively long span and short chord; one of low aspect ratio is of relatively short span and long chord. Computations were carried out for the same low-aspect-ratio plate wing configuration tested in the experiments.

The baseline Reynolds number is Re c = 10 4, however, additional simulations over the Reynolds number range 10 3 ≤ Re c ≤ 2 × 10 4 were also by: the series of flight experiments to evaluate the applicability of each technical element of the fault tolerant flight control system.

MuPAL-α was developed by JAXA as a flying laboratory based on a Dornier Do, and has carried out flight experiments in support of research and development of various advanced guidance and control.

Suction control of flow separation of a low-aspect-ratio wing at a low Reynolds number 24 September | Fluid Dynamics Research, Vol. 50, No. 6 Interaction of tip vortex and laminar separation bubble over wings with different aspect ratios under low Reynolds numbersCited by: Why another aircraft design book.

Aircraft design is a complex and fascinating business and many books have been written about it. The very complexity and dynamic nature of the subject means that no one book can do it justice.

This book, therefore, will primarily act as an introduction to the whole field of aircraft design leading towards. Experimental results of the thermal and hydraulic performances of silicon-based, low aspect ratio micropin-fin cold plates under cross flow conditions are reported.

The pins were both circular and square in shape with dimensions (diameter for circular and sides for square) ranging from 50 μ m to μ m ⁠.Cited by: The heat transfer characteristics of low aspect ratio pin fin arrays has not been as widely studied as the heat transfer in high aspect ratio pin fin arrays commonly used in heat exchanger applications.

This paper presents experimental results that show how the addition of pin fin arrays augments convective heat by: The FB aircraft is ft long and has a wingspan of ft (fig. The aircraft has a basic operating weight of 27, lb and a takeoff gross weight of 54, lb.

The NASA FB airplane has been converted from its U. Air Force role as an air-superiority fighter to a research test bed by: 8. Introduction.

Butterfly flight has long fascinated scientists and the public, but only in recent years have technological advances made it possible to at least approximate insect-sized flying robots [1–5].The construction of such robots offers important challenges to materials scientists, engineers and physicists, but research is also driven by practical applications for search and Cited by: Thermal soaring flight of birds and UAVs Zsuzsa Ákos 1, Máté Nagy 1, Severin Leven 2 and Tamás Vicsek 1,3 1Department of Biological Physics, Eötvös University, Pázmány Péter sétány 1A, H, Budapest, Hungary, 2Laboratory of Intelligent Systems, École Polytechnique Fédérale de Lausanne, Switzerland, 3Statistical and Biological Physics Research Group of.

Important to the development of improved system capability is This effort addresses aspects of item (1) above. It develops a new program, called EFPLAN, for conducting flight planning research.

EFPLAN is complementary to the OPTIM series of programs for conducting flight manage- ment research developed earlier[l]. Development. The dural and fabric BOK-5 was a single-engined tail-less monoplane used to develop trailing edge controls for tail-less aircraft. The aircraft had a low aspect ratio moderately tapered wing with the fixed tail-wheel undercarriage, single M engine, pilots cockpit all accommodated by the central nacelle which faired into an integral fin, with rudder, at the flight: summer Research Portfolio in Life and Physical Sciences: Ground based and planned flight experiments David Tomko, Ph.D.; Francis Chiaramonte, Ph.D.

Advanced Capabilities Division Exploration Systems Mission Directorate. propulsion, and flight controls. The development of automatic control system has played an important role in the growth of civil and military aviation.

Modern aircraft include a variety of automatic control system that aids the flight crew in navigation, flight management and augmenting the stability characteristic of the Size: KB. While high–aspect ratio wings, such as those of bird 1 in Fig.

4B, allow for reduced aerodynamic drag and are ideal for gliding, broader, low–aspect ratio wings permit maneuverability in flight. Through allometrically adjusting the percent humerus length within the wing, nature has provided a means for the bird wing to be optimized for many Cited by: 2.

I took this book and ran with it and calculated our design's research cost, prototype cost, and production cost and demonstrated the learning curve in manufacturing and how the cost decreased.

While it wasn't exactly what the professors were used to, it did raise a few eyes and ears from the manufacturing companies who had come to listen to the 5/5(3). Get this from a library. Comparison of theoretical and flight-measured local flow aerodynamics for a low-aspect-ratio fin. [J Blair Johnson; Doral R Sandlin; Dryden Flight Research Facility.].

Design and development. The Mallard was the third aircraft type produced by Cornelius Aircraft. The first two, the FreWing and the LW-1 were conventional in layout but unusual in using independently variable incidence wings for pitch and roll control.

The wings of the Mallard could also be adjusted in the air, but they were of low aspect ratio with marked forward er: George Cornelius. Kuhlman, J.

M., Liaw, P., Cerney, M. Theoretical/numerical study of feasibility of use of winglets on low aspect ratio wings at subsonic and transonic Mach numbers to reduce drag.

NASA CR, Google ScholarCited by: S. Karmakar and A. Kushari, “Pressure Fluctuations in the Flow through a Low Aspect Ratio Dump Combustor with Tapered Exit,” International Journal of Fluid Mechanics Research, Vol.

36,pp. A succession of X aircraft, designed primarily for flight experiments, populated the skies above Muroc in a continuous cycle of research and development (R&D). Two more X-1 aircraft were ordered by the Air Force, followed by the X-1A and the.

In preparation for a flight test, the prototype FLAP was mounted on the air-data boom of a flight-test fixture (FTF) on the NASA Dryden FB flight research airplane. The FTF is an aerodynamic fixture for flight-research experiments that is carried underneath the FB fuselage (see Figure 2).

4 Flight simulation54 Speci c heat ratio, for air = c Fin midchord sweep angle Fin cant angle Air ow inclination angle over a n Roll angle results as a research and development project at the 8th National Associ-ation of Rocketry Annual Meeting (NARAM-8) File Size: 1MB.

I do read that you by a low aspect ratio airplane imply a tail less airplane or a flying wing. If so, the reason for the short rudder lever arm is not that the plane has a low aspect ratio, but that it is a flying wing or tail less design.

Two good examples of low aspect ratio airplanes with delta wings are the Mig 21 and A4 Skyhawk. Grade Anyone who performed most of the experiments in this book would have a thorough understanding of the basic principles of aerodynamics.

Some experiments are designed so that readers can compare different designs of airplanes, gliders, and hovercraft. There are auxiliary designs for building air-speed indicators and wind : $ Do Different Fin Designs Affect a Rocket Maximum Altitude Aerodynamics Science Fair Projects, Hydrdynamics Model Experiments for CBSE ISC Stream Students and for Kids in Middle school, Elementary School for class 5th Grade, 6th, 7th, 8th, 9th 10th, 11th, 12th Grade and High School, MSC and College Students.

Assessing Safety Culture within a Flight Training Organization 2. ABSTRACT. This study was prompted by a string of aircraft hull losses experienced by a multinational, multi-campus flight training organization. A mixed methods study was conducted to study the attitudes and perceptions of the operations and.

Abstract. A low-cost and high-fidelity flight simulation training device (FSTD) has been developed for the purpose of research and education. With inexpensive and easy obtained materials, the FSTD duplicates a realistic cockpit and relevant hardware of Cited by: 3.

Historical Development of Aircraft Flutter I. E Garric k nd Wilme r H Ree d I NASA Langley Research Center, Hampton, Va. Introduction AEROELASTICITY, and in particular flutter, has in-fluenced he evolutio n of aircraf t since he earlies t days of flight.

This paper presents a glimpse of problems arising in these areas ndow the y were attacked. Aerospace engineering and operations technicians are essential to the development of new aircraft and space vehicles.

They build, test, and maintain parts for air and spacecraft, and assemble, test, and maintain the vehicles as well. They are key members of a flight readiness team, preparing space vehicles for launch in clean rooms, and on the.

development of the Digital Datcom computer program is an approach to provide rapid and economical estimation of aerodynamic stability and control characteristics. Digital Datcom calculates static stability, high-lift and control device, and dynamic-derivative characteristics using the methods contained in Sections 4 through 7 of Datcom.

NASA Dryden Flight Research Center has developed a second-generation flight test fixture for use as a generic test bed for aerodynamic and fluid mechanics research. The Flight Test Fixture II (FTF-II) is a low-aspect-ratio vertical fin-like shape that is mounted on the centerline of the FB lower fuselage.

The fixture is designed for flight. Delta The delta is a very low aspect ratio wing used in supersonic aircraft, most notably in the European designs. The main advantages of the delta wing is that is efficient in all the flight regimes (subsonic, transonic and supersonic).

Also, the wing offers a large wing area for the shape, reducing wing loading and improving maneuverability. Aerodynamic Principles for Professional Pilots illustrates the essential aerodynamic principles and applications relevant to flight technique issues. Applications are presented at the professional pilot level without unnecessary context, utilizing a visual format emphasizing pictorial concepts that enhance learning and retention.

Ostanek and Karen A Thole,"Flowfield measurements in a single row of low aspect ratio pin-fins", Journal of Turbomachinery,(5), pp. Lawson, Karen A Thole, Y. Okita and C. Nakamata,"Simulations of multi-phase particle deposition on a showerhead with staggered film-cooling holes", Journal of Turbomachinery.

of low aspect ratio and (2) slender wing theory matched the rolling characteristics obtained from flight test data for missiles which were equipped with low aspect ratio rectangular fins. Cl Cl 6 of RValues p and R were taken from Reference 7 for the fins selected in -this study. Since the coefficients of Reference 7 were.Development and Validation of an Aviation Research Survey David C.

Ison. PDF. Tracing the History of the Ornithopter: Past, Present, and Future Benjamin J. Goodheart. Editorial. PDF. Editor's Forum William Kohlruss.

Forum. PDF. Freud’s Ego in the Cockpit Kelsie M. O'Bryan. .advances in the development of scramjet combustors have shown an increased interest in low aspect ratio geometries1,2.

In addition, issues related to the scalability of the combustors present a formidable challenge regarding the utilization of hypersonic vehicles as practical, affordable, and reusable means of hypersonic transport for space Size: 2MB.