Download or read book Damping in Roll of Models with 45 60 and 70 Delta Wings Determined at High Subsonic Transonic and Supersonic Speeds with Rocket powered Models written by E. Claude Sanders and published by . This book was released on 1952 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Damping in Roll of Models with 45 Degree 60 Degree and 70 Degree Delta Wings Determined at High Subsonic Transonic and Supersonic Speeds with Rocket powered Models written by E. Claude Jr Sanders and published by . This book was released on 1952 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Note National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1957 with total page 618 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Methods for Obtaining Desired Helicopter Stability Characteristics and Procedures for Stability Predictions written by F. B. Gustafson and published by . This book was released on 1957 with total page 720 pages. Available in PDF, EPUB and Kindle. Book excerpt: Part 1 of this report presents a brief review of methods available to the helicopter designer for obtaining desired stability characteristics by modifications to the airframe design. The discussion is based on modifications made during the establishment of flying-qualities criteria and includes sample results of theoretical studies of additional methods. The conclusion is reached that it is now feasible to utilize combinations of methods whereby stability-parameter values are realized which in turn provide the desired stability characteristics. Part 2 reviews some of the methods of predicting rotor stability derivatives. The procedures by which these rotor derivatives are employed to estimate helicopter stability characteristics have been summarized.

Download or read book Advanced Aircraft Flight Performance written by Antonio Filippone and published by Cambridge University Press. This book was released on 2012-12-17 with total page 665 pages. Available in PDF, EPUB and Kindle. Book excerpt: This unique book deals with the aeroplane at several levels and aims to simulate its flight performance using computer software.

Download or read book Flight Performance of Fixed and Rotary Wing Aircraft written by Antonio Filippone and published by Elsevier. This book was released on 2006-05-10 with total page 594 pages. Available in PDF, EPUB and Kindle. Book excerpt: Calculation and optimisation of flight performance is required to design or select new aircraft, efficiently operate existing aircraft, and upgrade aircraft. It provides critical data for aircraft certification, accident investigation, fleet management, flight regulations and safety. This book presents an unrivalled range of advanced flight performance models for both transport and military aircraft, including the unconventional ends of the envelopes. Topics covered include the numerical solution of supersonic acceleration, transient roll, optimal climb of propeller aircraft, propeller performance, long-range flight with en-route stop, fuel planning, zero-gravity flight in the atmosphere, VSTOL operations, ski jump from aircraft carrier, optimal flight paths at subsonic and supersonic speed, range-payload analysis of fixed- and rotary wing aircraft, performance of tandem helicopters, lower-bound noise estimation, sonic boom, and more.This book will be a valuable text for undergraduate and post-graduate level students of aerospace engineering. It will also be an essential reference and resource for practicing aircraft engineers, aircraft operations managers and organizations handling air traffic control, flight and flying regulations, standards, safety, environment, and the complex financial aspects of flying aircraft. Unique coverage of fixed and rotary wing aircraft in a unified manner, including optimisation, emissions control and regulation. Ideal for students, aeronautical engineering capstone projects, and for widespread professional reference in the aerospace industry. Comprehensive coverage of computer-based solution of aerospace engineering problems; the critical analysis of performance data; and case studies from real world engineering experience. Supported by end of chapter exercises

Download or read book Research Abstracts and Reclassification Notice written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book WADC Technical Report written by United States. Wright Air Development Division and published by . This book was released on 1957 with total page 1268 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A New Dimension Wallops Island Flight Test Range written by Joseph Adams Shortal and published by . This book was released on 1978 with total page 796 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Technique Utilizing Rocket propelled Test Vehicles for the Measurement of the Damping in Roll of Sting mounted Models and Some Initial Results for Delta and Unswept Tapered Wings written by William M. Bland and published by . This book was released on 1950 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: A free-flight test technique utilizing rocket-propelled test vehicles with which the damping in roll of sting-mounted wings and wing-fuselage combinations can be obtained over the high subsonic, transonic, and supersonic speed range is described and some results for delta and unswept tapered wings are presented. Initial results compare well with those obtained in supersonic wind-tunnel tests. Results for all of the configurations tested show that damping in roll was maintained throughout the Mach number range investigated and that subsonic damping-in-roll agreed with theoretical values within experimental accuracy. In the lower supersonic region these results differ from the values predicted by linearized flow theory; however, the agreement improved with increasing Mach number. Increased section thickness decreased the damping in roll of the delta wings throughout the Mach number range investigated.

Download or read book Advanced Aircraft Flight Performance written by Antonio Filippone and published by Cambridge University Press. This book was released on 2012-12-17 with total page 665 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book discusses aircraft flight performance, focusing on commercial aircraft but also considering examples of high-performance military aircraft. The framework is a multidisciplinary engineering analysis, fully supported by flight simulation, with software validation at several levels. The book covers topics such as geometrical configurations, configuration aerodynamics and determination of aerodynamic derivatives, weight engineering, propulsion systems (gas turbine engines and propellers), aircraft trim, flight envelopes, mission analysis, trajectory optimisation, aircraft noise, noise trajectories and analysis of environmental performance. A unique feature of this book is the discussion and analysis of the environmental performance of the aircraft, focusing on topics such as aircraft noise and carbon dioxide emissions.

Download or read book Subject Index to Unclassified ASTIA Documents written by Defense Documentation Center (U.S.) and published by . This book was released on 1960 with total page 308 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Subsonic Roll Damping of a Model with Swept back and Swept forward Wings written by and published by . This book was released on 1978 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Damping in Roll of Rocket powered Test Vehicles Having Rectangular Wings with NACA 65 006 and Symmetrical Double wedge Airfoil Sections of Aspect Ratio 4 5 written by Albert E. Dietz and published by . This book was released on 1950 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: A free-flight investigation of two rocket-powered model configurations has been made to determine the damping of roll. The models had rectangular wings of 4.5 aspect ratio and were the same except for airfoil section; one configuration had an NACA 65-006 airfoil section and the other had a modified double-wedge airfoil section (6 percent thick). Each model used a rocket motor incorporating a torque nozzle which produced a known torque to roll the model during the accelerated portion of flight. The damping in roll was calculated by balancing the moments acting on the model throughout the accelerating and decelerating portions of flight.

Download or read book A Collection of Data for Zero lift Damping in Roll of Wing body Combinations as Determined with Rocket powered Models Equipped with Roll torque Nozzles written by David G. Stone and published by . This book was released on 1953 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Free flight Technique for Measuring Damping in Roll by Use of Rocket powered Models and Some Initial Results for Rectangular Wings written by James L. Edmondson and published by . This book was released on 1949 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: A simplified method for obtaining free-flight measurements of damping in roll through use of rocket-powered models has been developed; and initial configurations have been tested through a Mach number range of approximately 0.85 to 1.40, which corresponds to a Reynolds number range of 4,500,000 to 8,000,000. The basic principle of this method is that the model is forced to roll by a non-aerodynamic rolling moment of known magnitude which is produced by a canted-nozzle assembly, and the damping in roll is computed by balancing moments acting on the model.