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Author : Franz Wilhelm Schmitz
Publisher : Unknown
Page : 218 pages
File Size : 48,7 Mb
Release : 1967
Category : Aerodynamics
ISBN : PSU:000022807830
Author : F. W. Schmitz
Publisher : Unknown
Page : 190 pages
File Size : 48,8 Mb
Release : 1942*
Category : Aerofoils
ISBN : OCLC:220084335
Author : Anonim
Publisher : Unknown
Page : 189 pages
File Size : 50,6 Mb
Release : 1967
Category : Electronic
ISBN : OCLC:223757888
Author : Martin Simons
Publisher : Chris Lloyd Sales & Marketing
Page : 0 pages
File Size : 54,8 Mb
Release : 2015-01-15
Category : Technology & Engineering
ISBN : 1854862707
This is the latest edition - fully revised and updated - of the standard textbook on aerodynamic theory, as applied to model flight. Everything is explained in a concise and practical form for those enthusiasts who appreciate that a better understanding of model behaviour is the sure path to greater success and enjoyment, whether just for fun or in competition. The revisions for this new edition reflect the significant developments in model aircraft during the last few years, and include brand new data: * The chapter on aerofoils has been rewritten to take account of the vast amount of testing carried out recently in the USA by the University of Illinois. * A brand new chapter explains the latest research into the flight of birds and insects and how it is applied to small drones and model-sized surveillance aircraft. * Older wind tunnel test reports all replaced with the latest trials and measurements.
Author : Philip Donely,Harold B. Pierce,Philip W. Pepoon
Publisher : Unknown
Page : 46 pages
File Size : 52,8 Mb
Release : 1940
Category : Airplanes
ISBN : UOM:39015069157488
A model of a hypothetical canard airplane, which was designed to be of the same size and general aerodynamic characteristics as a Boeing B-247 airplane, was tested in the N.A.C.A. gust tunnel at one wing loading, one forward speed, one gust velocity, and three gust gradients. The purpose of these tests was to determine the reactions of the model and to compare them with the results of unpublished tests on an equivalent model of the Boeing B-247 airplane.
Author : Thomas J. Mueller
Publisher : Springer Science & Business Media
Page : 456 pages
File Size : 55,7 Mb
Release : 2013-03-08
Category : Science
ISBN : 9783642840104
Current interest in a variety of low Reynolds number applications has focused attention on the design and evaluation of efficient airfoil sections at chord Reynolds numbers from about 100,000 to about 1,000,000. These applications include remotely piloted vehicles (RPVs) at high altitudes, sailplanes, ultra-light man-carrying/man powered aircraft, mini-RPVs at low altitudes and wind turbines/propellers. The purpose of this conference was to bring together those researchers who have been active in areas closely related to this subject. All of the papers presented are research type papers. Main topics are: Airfoil Design and Analysis, Computational Studies, Stability and Transition, Laminar Separation Bubble, Steady and Unsteady Wind Tunnel Experiments and Flight Experiments.
Author : E. O. Pearson,A. J. Evans,F. E. West
Publisher : Unknown
Page : 48 pages
File Size : 54,7 Mb
Release : 1945
Category : Aerodynamic load
ISBN : UFL:31262081049735
Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high-speed tunnel to determine the effects of compressibility on the maximum lift characteristics and the span-wise load distribution. The range of angle of attack investigated was from -10 to +24 degrees. The Mach range of from 0.20 to 0.70 at small and medium angles of attack and from 0.15 to 0.625 at very large angles of attack. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Author : Norman M. McFadden,John L. McCloud,Harry A. James
Publisher : Unknown
Page : 20 pages
File Size : 54,5 Mb
Release : 1953
Category : Aerodynamics
ISBN : UFL:31262081065616
Abstract: Comparisons are presented of predicted values of flow angles and those measured using detectors close to the surface of the forward portion of fuselages of a large-scale, triangular-wing, wind-tunnel model at low speeds and a 35° swept-wing fighter airplane in flight. Effects of flap deflection on the upwash of the triangular-wing model are included.
Author : Anonim
Publisher : Unknown
Page : 44 pages
File Size : 49,6 Mb
Release : 1960
Category : Airplanes
ISBN : UIUC:30112106562439
Author : Allen F. Donovan
Publisher : Princeton University Press
Page : 1021 pages
File Size : 51,5 Mb
Release : 2015-12-08
Category : Science
ISBN : 9781400875030
Volume VIII of the High Speed Aerodynamics and Jet Propulsion series. This volume includes: performance calculation at high speed; stability and control of high speed aircraft; aeroelasticity and flutter; model testing; transonic wind tunnels; supersonic tunnels; hypersonic experimental facilities; low density wind tunnels; shock tube; wind tunnel measurements; instrumented models in free flight; piloted aircraft testing; free flight range methods. Originally published in 1961. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.
Author : Harold E. Addy
Publisher : Unknown
Page : 292 pages
File Size : 54,7 Mb
Release : 2000
Category : Aerofoils
ISBN : UCBK:C101374349
Icing tests were conducted to document ice shapes formed on three different two-dimensional airfoils and to study the effects of the accreted ice on aerodynamic performance. The models tested were representative of airfoil designs in current use for each of the commercial transport, business jet, and general aviation categories of aircraft. The models were subjected to a range of icing conditions in an icing wind tunnel. The conditions were selected primarily from the Federal Aviation Administration's Federal Aviation Regulations 25 Appendix C atmospheric icing conditions. A few large droplet icing conditions were included. To verify the aerodynamic performance measurements, molds were made of selected ice shapes formed in the icing tunnel. Castings of the ice were made from the molds and placed on a model in a dry, low-turbulence wind tunnel where precision aerodynamic performance measurements were made. Documentation of all the ice shapes and the aerodynamic performance measurements made during the icing tunnel tests is included in this report. Results from the dry, low-turbulence wind tunnel tests are also presented.
Author : Ralph P. Bielat
Publisher : Unknown
Page : 30 pages
File Size : 44,7 Mb
Release : 1945
Category : Acceleration (Mechanics)
ISBN : UFL:31262081050014
Summary: A generalized drag curve that provides an estimate for the drag rise due to compressibility has been obtained for an analysis of wind-tunnel data of several airfoils, fuselages, nacelles, and windshields at speeds up to and above the wing critical speed. The airfoils analyzed had little or no sweepback and effective aspect ratios above 6.5. A chart based on the generalized drag curve is presented from which the terminal velocity of a conventional airplane that employs a wing of moderate aspect ratio and very little sweepback in a vertical dive may be rapidly estimated. In order to use the chart, the only data that need be known about the airplane are a low-speed drag coefficient, the wing critical speed, and the wing loading. The terminal velocities for three airplanes were computed in order to illustrate the use of the method and chart. Good agreement between the estimated terminal velocity and the measured flight terminal velocity was indicated for all three airplanes.
Author : Anonim
Publisher : Unknown
Page : 104 pages
File Size : 48,7 Mb
Release : 1960
Category : Electronic
ISBN : NASA:31769000460306
Author : Howard F. Savage
Publisher : Unknown
Page : 662 pages
File Size : 41,8 Mb
Release : 1957
Category : Aerodynamics
ISBN : STANFORD:36105024832243
An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
Author : Michael S. Selig
Publisher : Soartech
Page : 320 pages
File Size : 46,6 Mb
Release : 1995
Category : Technology & Engineering
ISBN : STANFORD:36105115142486