Wind-tunnel free-flight investigation of a model of a forward-swept-wing fighter configuration
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National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] , Washington, D.C, [Springfield, Va
Stability of airplanes -- Testing., Fighter planes -- Wings., Wind tun
|Statement||Daniel G. Murri, Luat T. Nguyen, and Sue B. Grafton.|
|Series||NASA technical paper -- 2230.|
|Contributions||Nguyen, Luat T., Grafton, Sue B., United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.|
|The Physical Object|
|Pagination||68 p. :|
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Wind-tunnel free-flight investigation of a model of a forward-swept-wing fighter configuration. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.: For sale by the National Technical Information Service], (OCoLC) Material Type.
Wind-tunnel free-flight investigation of a model of a forward-swept-wing fighter configuration / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. In-Flight Flow Visualization Results from High Angle of Attack Tests on a Forward Swept Wing Aircraft with Comparisons to Water Tunnel Results.
Authors; Jr., “Wind — Tunnel Free-Flight Investigation of a Model of a Spin-Resistant Fighter Configuration, ” NASA TN D, Author: John H. Del Frate.
Low-speed wind-tunnel study of the high-angle-of-attack stability and control characteristics of a cranked-arrow-wing fighter configuration [microform] / Sue B. Grafton National Aeronautics and Space Administration, Scientific and Technical Information Branch ; For sale by the National Technical Information Service] Washington, D.C.
Wind-tunnel free-flight investigation of a model of a forward-swept-wing fighter configuration [microfo Flight stability and control [by] T. Hacker Stability in aviation; an introduction to dynamical stability as applied to the motions of aeroplanes, b. A swept wing is a wing that angles either backward or occasionally forward from its root rather than in a straight sideways direction.
Wing sweep has the effect of delaying the shock waves and accompanying aerodynamic drag rise caused by fluid compressibility near the speed of sound, improving wings are therefore often used on jet aircraft designed to fly at.
Control of flying flexible aircraft using control surfaces and dispersed piezoelectric actuators of a forward-swept wing fighter configuration. wind-tunnel force tests, free-flight model.
Effects of rain and wind on aircraft flight safety dynamics of a forward-swept wing fighter configuration. static and dynamic wind-tunnel force tests, free-flight model tests, drop-model.
Airplanes, Tailless. See also what's at your library, or elsewhere.
Download Wind-tunnel free-flight investigation of a model of a forward-swept-wing fighter configuration PDF
Broader term: Airplanes; Used for: All-wing airplanes; Flying wing airplanes; Tailless airplanes. In-Flight investigation of large airplane flying qualities for approach and landing. High angle-of-attack characteristics of a forward-swept wing fighterconfiguration.
Comparison of free-flight and wind tunnel data for a generic fighterconfiguration. Full text of "NASA Technical Reports Server (NTRS) Aeronautical Engineering: A continuing bibliography, cumulative index" See other formats.
The forward swept wing idea resulted from the transonic test of an aft swept wing of a Grumman configuration which had been proposed to satisfy the NASA HiMAT RFP (request for proposal).
The winning proposal was submitted by Rockwell, and the Rockwell HiMAT was built, flown, and is currently in the Smithsonian Air and Space Museum. Full text of "NASA Technical Reports Server (NTRS) Aeronautical Engineering: A continuing bibliography with indexes (supplement )" See other formats.
Free-flight model studies of the dynamic stability and control characteristics of delta wing designs were conducted in the Free-Flight Tunnel, including an investigation of the Consolidated Vultee (later Convair) XF, which was the first U.S.
delta wing fighter.5/5(2). Read NASA's Contributions to Aeronautics, Volume 1, by National Aeronautics & Space Administration.
in HTML for FREE. Also available in PDF, ePub. Richard Whitcomb and the Quest for Aerodynamic Efficiency NACA–NASA and the Rotary Wing Revolution Softening the Sonic Boom: 50 Years of NASA Research Toward Transatmospheric Fl.
Wind tunnel test times, as shown in Fig. 1, have been growing to o h (all aerodynamic sub-components, full configuration system, and all speed ranges), although the experimental research aircraft Grumman XA required less than h before maiden flight in This was in the same order as the development of the F 30 years Cited by: It’s a shame that none of the many pure-rocket interceptors of the late 40s and early 50s made it into the air, especially thewhich made aircraft appearing 20 years later look a bit staid.
All that remains of thefollowing its cancellation inis a wind-tunnel model at the museum of technology at Dubna. InLangley replaced its first wind tunnel with the 7 by Foot Atmospheric Wind Tunnel (AWT), housed in the same building. This test of a Clark-Y. Comments. Transcription.
English - Scale Soaring UK. Library of Congress Cataloging-in-Publication Data (Revised for vol. 8) NASA historical data book. (NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C.
Bruno. Vol. 8 in series: The NASA historical data book series. Includes bibliographical references and indexes.
A Numerical and Experimental Evaluation of Open Jet Wind Tunnel Interferences using the DrivAer Reference Model. SAE International Journal Passenger Cars - Mech. Syst. (Vol.
Details Wind-tunnel free-flight investigation of a model of a forward-swept-wing fighter configuration EPUB
9, No. 2),pp. mehr. Find link is a tool written by Edward Betts.Free flight (model aircraft), List of model aircraft manufacturers radial engines and was designed as a scaled-up version of a wind tunnel model aircraft. One was built and flew in the mids.
In the development of the. Dynamically Scaled Free-Flight Model Testing Joseph R Chambers CASE. NASA and the Evolution of the Wind Tunnel Jeremy Kinney CASE.
Evolving the Modern Composite Airplane Stephen Trimble CASE. NACANASAs Contribution to General Aviation Weneth D Painter CASE. The Evolution of Remotely Piloted Research Vehicles Peter W Merlin 5/5(1).
A Numerical and Experimental Evaluation of Open Jet Wind Tunnel Interferences using the DrivAer Reference Model. SAE International Journal Passenger Cars - Mech. Syst. (Vol. 9, No. 2),pp. more.
Description Wind-tunnel free-flight investigation of a model of a forward-swept-wing fighter configuration PDF
For example, C.H. Dearborn and H.W. Kirschbaum, “Maneuverability Investigation of the F6C-3 Airplane with Special Flight Instruments,” NACA TR (); and Philip Donely and Henry A. Pearson, “Flight and Wind-Tunnel Tests of an XBM-1 Dive Bomber,” NACA TN ().
The first free flight occurred Novembut the nozzle spoiler control system proved unacceptable. After 5 flights, testing was temporarily halted 12/5/, after logging hours of test time in both tethered and free flight. Flight tests resumed 01/ and a USAF flight evaluation was held 4/4/ Model of the jet fighter project.
broad wings tapered on the leading edge with squared-off tips carrying swept fins and rudders. Beyond these were small forward-swept ailerons.
InGrumman engineers had analyzed data from HiMAT model tests in NASA Langley’s 8-foot transonic pressure tunnel that promised a decrease in induced drag and improvements in maneuverability for a wing “by sweeping the wing forward (leading edge of the tip forward of the leading edge of the root).” 4 0 A Grumman memo dated April Effect of Reynolds number on lift of a general-aviation model as measured in wind tunnel tests.
Data were obtained at relatively low values of Reynolds number corresponding to model free- flight tests and high values representative of full-scale flight tests.
The full-scale data show a markedly higher magnitude and angle of attack for maximum lift. This wind tunnel investigation used a model of the SCIF-5 fighter design concept. It featured a highly swept cranked-arrow wing designed for a cruise Mach number of Leading-edge sweep angle was 74 degrees on the inboard wing segments and 65 degrees on the outer wing panels.The conventional gear configuration, being a relic of the past is affectionately dubbed a "tail dragger" by pilots.
This configuration is unstable, and, while rolling along the runway with this type of gear, the pilot must exercise prudent brake and rudder steering to prevent excessive yaw.5/5(5).A New Twist in Flight Research.
AFW Wind Tunnel Model Testing half-span wind tunnel model. This investigation, culminating in July and August with testing in Langleys TDT, the X Forward Swept Wing and the Advanced Fighter Technology Integration F
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