Download or read book Aerodynamics of the Model Airplane Airfoil measurements written by Franz Wilhelm Schmitz and published by . This book was released on 1967 with total page 218 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamics of the Model Airplane written by F. W. Schmitz and published by . This book was released on 1942* with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamics of the Model Airplane Part 1 Airfoil Measurements written by and published by . This book was released on 1967 with total page 189 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Model Aircraft Aerodynamics written by Martin Simons and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Summary of Low Speed Airfoil Data written by Michael S. Selig and published by Soartech. This book was released on 1995 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Introduction to Flapping Wing Aerodynamics written by Wei Shyy and published by Cambridge University Press. This book was released on 2013-08-19 with total page 321 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is an ideal book for graduate students and researchers interested in the aerodynamics, structural dynamics and flight dynamics of small birds, bats and insects, as well as of micro air vehicles (MAVs), which present some of the richest problems intersecting science and engineering. The agility and spectacular flight performance of natural flyers, thanks to their flexible, deformable wing structures, as well as to outstanding wing, tail and body coordination, is particularly significant. To design and build MAVs with performance comparable to natural flyers, it is essential that natural flyers' combined flexible structural dynamics and aerodynamics are adequately understood. The primary focus of this book is to address the recent developments in flapping wing aerodynamics. This book extends the work presented in Aerodynamics of Low Reynolds Number Flyers (Shyy et al. 2008).
Download or read book Model Aircraft Aerodynamics written by Martin Simons and published by Chris Lloyd Sales & Marketing. This book was released on 2015-01-15 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Measurements and Analysis of the Motion of a Canard Airplane Model in Gusts written by Philip Donely and published by . This book was released on 1940 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Low Reynolds Number Aerodynamics written by Thomas J. Mueller and published by Springer Science & Business Media. This book was released on 2013-03-08 with total page 456 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Aerodynamic and Landing Measurements Obtained During the First Powered Flight of the North American X 15 Research Airplane written by and published by . This book was released on 1960 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12 foot span Fighter type Wing of NACA 230 series Airfoil Sections written by E. O. Pearson and published by . This book was released on 1945 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Comparison of Measured and Predicted Indicated Angles of Attack Near the Fuselages of a Triangular wing Wind tunnel Model and a Swept wing Fighter Airplane in Flight written by Norman M. McFadden and published by . This book was released on 1953 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book BASIC PRESSURE MEASUREMENTS ON A 0 0667 SCALE MODEL OF THE NORTH AMERICAN X 15 RESEARCH AIRPLANE AT TRANSONIC SPEEDS written by and published by . This book was released on 1960 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High Speed Problems of Aircraft and Experimental Methods written by Allen F. Donovan and published by Princeton University Press. This book was released on 2015-12-08 with total page 1021 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 written by Howard F. Savage and published by . This book was released on 1957 with total page 662 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book A Simple Method for Estimating Terminal Velocity Including Effect of Compressibility on Drag written by Ralph P. Bielat and published by . This book was released on 1945 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Aerodynamic Characteristics Temperature and Noise Measurements of a Large scale External flow Jet augmented flap Model with Turbojet Engines Operating written by Marvin P. Fink and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley full-scale tunnel on a large-scale model powered by turbojet engines with flattened rectangular nozzles. The wing had 35° sweep of the leading edge, an aspect ratio of 6.5, a taper ratio of 0.31, and NACA 65(1)-412 and 65-408 airfoils at the root and tip. The investigation included measurements of the longitudinal aerodynamic characteristics of the model with half-span and full-span flaps and measurements of the sound pressure and skin temperature on the portions of the lower surface of the wing immersed in the jet flow. The tests were conducted over a range or angles of attack from -8° to 16° for Reynolds numbers from 1.8 x 106 to 4.4 x 106 and a range of momentum coefficients from 0 to 2.0. In general, the aerodynamic results of this investigation made with a large-scale hot-jet model verified the results of previous investigations with small models powered by compressed-air jets. Although blowing was only done over the inboard portion of the wing, substantial amounts of induced lift were also obtained over the outboard portion of the wing. Skin temperatures were about 340° F and wing heating could be handled with available materials without cooling. Random acoustic loadings on the wing surface were high enough to indicate that fatigue failure from this source would require special consideration in the design of an external-flow jet flap system for an airplane.
