Download or read book Principles of Helicopter Aerodynamics with CD Extra written by Gordon J. Leishman and published by Cambridge University Press. This book was released on 2006-04-24 with total page 860 pages. Available in PDF, EPUB and Kindle. Book excerpt: Written by an internationally recognized teacher and researcher, this book provides a thorough, modern treatment of the aerodynamic principles of helicopters and other rotating-wing vertical lift aircraft such as tilt rotors and autogiros. The text begins with a unique technical history of helicopter flight, and then covers basic methods of rotor aerodynamic analysis, and related issues associated with the performance of the helicopter and its aerodynamic design. It goes on to cover more advanced topics in helicopter aerodynamics, including airfoil flows, unsteady aerodynamics, dynamic stall, and rotor wakes, and rotor-airframe aerodynamic interactions, with final chapters on autogiros and advanced methods of helicopter aerodynamic analysis. Extensively illustrated throughout, each chapter includes a set of homework problems. Advanced undergraduate and graduate students, practising engineers, and researchers will welcome this thoroughly revised and updated text on rotating-wing aerodynamics.

Download or read book NASA Technical Memorandum written by and published by . This book was released on 1989 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book New Results in Numerical and Experimental Fluid Mechanics XIII written by Andreas Dillmann and published by Springer Nature. This book was released on 2021-07-13 with total page 787 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book offers timely insights into research on numerical and experimental fluid mechanics and aerodynamics, mainly for (but not limited to) aerospace applications. It reports on findings by members of the STAB (German Aerospace Aerodynamics Association) and DGLR (German Society for Aeronautics and Astronautics) and covers both nationally and EC-funded projects. Continuing on the tradition of the previous volumes, the book highlights innovative solutions, promoting translation from fundamental research to industrial applications. It addresses academics and professionals in the field of aeronautics, astronautics, ground transportation, and energy alike.

Download or read book Computing Induced Velocity Perturbations Due to a Helicopter Fuselage in a Free Stream written by John D. Berry and published by . This book was released on 1989 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Feasibility Study of Collaborative Multi facility Windtunnel Testing for CFD Validation written by and published by . This book was released on 1999 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Between 1997 and 1999, a Working Group on the feasibility of collaborative, multi-facility windtunnel testing for the validation of Computational Fluid Dynamics Codes (CFD) has established the following results: Wintunnel tests are the main source of CFD validation but all have specific bias errors. Testing of the same model in several facilities can better establish the level of uncertainty in windtunnel tests and hence help assess possible differences between CFD and windtunnel tests. The Working Group, after an initial inquiry, established the need for CFD validation for fighter aircraft, transport type aircraft, missiles and helicopters. Effort and cost can be controlled efficiently and would permit the improvement of CFD Codes for considerable cost saving in future developments.

Download or read book Steady and Periodic Pressure Measurements on a Generic Helicopter Fuselage Model in the Presence of a Rotor written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-13 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel test of a generic helicopter fuselage model with an independently mounted rotor has been conducted to obtain steady and periodic pressure data on the helicopter body. The model was tested at four advance ratios and three thrust coefficients. The periodic unsteady pressure coefficients are marked by four peaks associated with the passage of the four rotor blades. Blade passage effects are largest on the nose and tail boom of the model. The magnitude of the pulse increases with rotor thrust coefficient. Tabular listings of the unsteady pressure data are included to permit independent analysis. A CD-rom containing the steady and unsteady pressure data presented in the report is available from the authors. Mineck, Raymond E. and Gorton, Susan A. Langley Research Center RTOP 581-10-11-01

Download or read book Journal of the American Helicopter Society written by American Helicopter Society and published by . This book was released on 1998 with total page 376 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Unsteady Velocity Measurements Taken Behind a Model Helicopter Rotor Hub in Forward Flight written by John D. Berry and published by . This book was released on 1997 with total page 262 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Application of an Unstructured Grid Navier Stokes Solver to a Generic Helicopter Boby Comparison of Unstructured Grid Results with Structured Grid Results and Experimental Results written by and published by . This book was released on 1999 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Blade Planform Variation on a Small scale Hovering Rotor written by Susan L. Althoff and published by . This book was released on 1990 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Investigation of Effects of Fuselage Cross sectional Shape Fuselage Bend and Vertical tail Size on Directional Characteristics of Nonoverlap type Helicopter Fuselage Models Without Rotors written by James L. Williams and published by . This book was released on 1956 with total page 736 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed investigatio was made in the Langley stability tunnel to determine the directional stability characteristics of tandem nonoverlap-type helicopter fuselages without rotors. The investigation consisted of a study of both bent and straight fuselages having either circular or essentially elliptical cross sections and with two vertical-tail sizes.

Download or read book Navier Stokes and Potential Theory Solutions for Ahelicopter Fuselage and Comparison with Experiment written by and published by . This book was released on 1994 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 564 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Planform Geometry on Hover Performance of a 2 meter diameter Model of a Four bladed Rotor written by and published by . This book was released on 1986 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Planform Geometry on Hover Performance of a 2 meter diameter Model of a Four bladed Rotor written by Arthur E. Phelps and published by . This book was released on 1986 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Comparison of Interactional Aerodynamics Methods for a Helicopter in Low Speed Flight written by John D. Berry and published by . This book was released on 1998 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Recent advances in computing subsonic flow have been applied to helicopter configurations with various degrees of success. This paper is a comparison of two specific methods applied to a particularly challenging regime of helicopter flight, very low speeds, where the interaction of the rotor wake and the fuselage are most significant. Comparisons are made between different methods of predicting the interactional aerodynamics associated with a simple generic helicopter configuration. These comparisons are made using fuselage pressure data from a Mach-scaled powered model helicopter with a rotor diameter of approximately 3 meters. The data shown are for an advance ratio of 0.05 with a thrust coefficient of 0.0066. The results of this comparison show that in this type of complex flow both analytical techniques have regions where they are more accurate in matching the experimental data.

Download or read book Aeronautical Engineering written by and published by . This book was released on 1991 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).