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Loads And Performance Data From A Wind Tunnel Test Of Generic Model Helicopter Rotor Blades
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Book Synopsis Loads and Performance Data from a Wind-tunnel Test of Generic Model Helicopter Rotor Blades by : William T. Yeager
Download or read book Loads and Performance Data from a Wind-tunnel Test of Generic Model Helicopter Rotor Blades written by William T. Yeager and published by . This book was released on 2005 with total page 548 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721985265 Total Pages :554 pages Book Rating :4.9/5 (852 download)
Book Synopsis Loads and Performance Data from a Wind-Tunnel Test of Generic Model Helicopter Rotor Blades by : National Aeronautics and Space Administration (NASA)
Download or read book Loads and Performance Data from a Wind-Tunnel Test of Generic Model Helicopter Rotor Blades written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-27 with total page 554 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the NASA Langley Transonic Dynamics Tunnel to acquire data for use in assessing the ability of current and future comprehensive analyses to predict helicopter rotating-system and fixed-system vibratory loads. The investigation was conducted with a generic model helicopter rotor system using blades with rectangular planform, no built-in twist, uniform radial distribution of mass and stiffnesses, and a NACA 0012 airfoil section. Rotor performance data, as well as mean and vibratory components of blade bending and torsion moments, fixed-system forces and moments, and pitch link loads were obtained at advance ratios up to 0.35 for various combinations of rotor shaft angle-of-attack and collective pitch. The data are presented without analysis. Yeager, William T., Jr. and Wilbur, Matthew L. Langley Research Center 23-065-40-30...
Book Synopsis Loads and Performance Data from a Wind-Tunnel Test of Generic Model Helicopter Rotor Blades by : Nasa Technical Reports Server (Ntrs)
Download or read book Loads and Performance Data from a Wind-Tunnel Test of Generic Model Helicopter Rotor Blades written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 556 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the NASA Langley Transonic Dynamics Tunnel to acquire data for use in assessing the ability of current and future comprehensive analyses to predict helicopter rotating-system and fixed-system vibratory loads. The investigation was conducted with a generic model helicopter rotor system using blades with rectangular planform, no built-in twist, uniform radial distribution of mass and stiffnesses, and a NACA 0012 airfoil section. Rotor performance data, as well as mean and vibratory components of blade bending and torsion moments, fixed-system forces and moments, and pitch link loads were obtained at advance ratios up to 0.35 for various combinations of rotor shaft angle-of-attack and collective pitch. The data are presented without analysis.
Book Synopsis Performance and Vibratory Loads Data From a Wind-Tunnel Test of a Model Helicopter Main-Rotor Blade With a Paddle-Type Tip by : William T. Yeager (Jr.)
Download or read book Performance and Vibratory Loads Data From a Wind-Tunnel Test of a Model Helicopter Main-Rotor Blade With a Paddle-Type Tip written by William T. Yeager (Jr.) and published by . This book was released on 1997 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Loads and Performance Data from a Wind-tunnel Test of Model Articulated Helicopter Rotors with 2 Different Blade Torsional Stiffnesses by :
Download or read book Loads and Performance Data from a Wind-tunnel Test of Model Articulated Helicopter Rotors with 2 Different Blade Torsional Stiffnesses written by and published by . This book was released on 1983 with total page 326 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Evaluation of a Model Helicopter Main-Rotor Blade With Slotted Airfoils at the Tip by :
Download or read book Wind Tunnel Evaluation of a Model Helicopter Main-Rotor Blade With Slotted Airfoils at the Tip written by and published by . This book was released on 2001 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt: Data for rotors using unconventional airfoils are of interest to permit an evaluation of this technology's capability to meet the U.S. Army's need for increased helicopter mission effectiveness and improved safety and survivability. Thus, an experimental investigation was conducted in the Langley Transonic Dynamics Tunnel (TDT) to evaluate the effect of using slotted airfoils in the rotor blade tip region (85 to 100 percent radius) on rotor aerodynamic performance and loads. Four rotor configurations were tested in forward flight at advance ratios from 0.15 to 0.45 and in hover in-ground effect. The hover tip Mach number was 0.627, which is representative of a design point of 4000-ft geometric altitude and a temperature of 95 degrees F. The baseline rotor configuration had a conventional single element airfoil in the tip region. A second rotor configuration had a forward-slotted airfoil with a -6 degrees slat, a third configuration had a forward-slotted airfoil with a -10 degrees slat, and a fourth configuration had an aft-slotted airfoil with a 3 degrees flap (trailing edge down). The results of this investigation indicate that the -6 degrees slat configuration offers some performance and loads benefits over the other three configurations.
Book Synopsis Loads and Performance Data from a Wind-tunnel Test of Model Articulated Helicopter Rotors with Two Different Blade Torsional Stiffnesses by : William T. Yeager
Download or read book Loads and Performance Data from a Wind-tunnel Test of Model Articulated Helicopter Rotors with Two Different Blade Torsional Stiffnesses written by William T. Yeager and published by . This book was released on 1983 with total page 326 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722479060 Total Pages :30 pages Book Rating :4.4/5 (79 download)
Book Synopsis Performance and Vibratory Loads Data from a Wind-Tunnel Test of a Model Helicopter Main-Rotor Blade with a Paddle-Type Tip by : National Aeronautics and Space Administration (NASA)
Download or read book Performance and Vibratory Loads Data from a Wind-Tunnel Test of a Model Helicopter Main-Rotor Blade with a Paddle-Type Tip written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-09 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley Transonic Dynamics Tunnel to obtain data to permit evaluation of paddle-type tip technology for possible use in future U.S. advanced rotor designs. Data was obtained for both a baseline main-rotor blade and a main-rotor blade with a paddle-type tip. The baseline and paddle-type tip blades were compared with regard to rotor performance, oscillatory pitch-link loads, and 4-per-rev vertical fixed-system loads. Data was obtained in hover and forward flight over a nominal range of advance ratios from 0.15 to 0.425. Results indicate that the paddle-type tip offers no performance improvements in either hover or forward flight. Pitch-link oscillatory loads for the paddle-type tip are higher than for the baseline blade, whereas 4-per-rev vertical fixed-system loads are generally lower. Yeager, William T., Jr. and Noonan, Kevin W. and Singleton, Jeffrey D. and Wilbur, Matthew L. and Mirick, Paul H. Langley Research Center RTOP 505-63-36-02...
Book Synopsis Performance Data from a Wind-tunnel Test of Two Main-rotor Blade Designs for a Utility-class Helicopter by : Jeffrey D. Singleton
Download or read book Performance Data from a Wind-tunnel Test of Two Main-rotor Blade Designs for a Utility-class Helicopter written by Jeffrey D. Singleton and published by DIANE Publishing. This book was released on 1990 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance and Vibratory Loads Data from a Wind-tunnel Test of a Model Helicopter Main-rotor Blade with a Paddle-type Tip by :
Download or read book Performance and Vibratory Loads Data from a Wind-tunnel Test of a Model Helicopter Main-rotor Blade with a Paddle-type Tip written by and published by . This book was released on 1997 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance Data from a Wind-tunnel Test of Two Main-rotor Blade Designs for a Utility-class Helicopter by : Jeffrey D. Singleton
Download or read book Performance Data from a Wind-tunnel Test of Two Main-rotor Blade Designs for a Utility-class Helicopter written by Jeffrey D. Singleton and published by . This book was released on 1990 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Helicopter Blade Dynamic Loads Measured During Performance Testing of Two Scaled Rotors by : John D. Berry
Download or read book Helicopter Blade Dynamic Loads Measured During Performance Testing of Two Scaled Rotors written by John D. Berry and published by . This book was released on 1987 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test to determine the performance differences between the 27-percent-scale models of two rotors for the U.S. Army AH-64 helicopter was conducted in the Langley 14- by 22-Foot Subsonic Tunnel. One rotor, referred to as the baseline rotor, simulated the geometry and dynamic characteristics of the production baseline rotor, and the other rotor, referred to as the advanced rotor, was designed to have improved hover performance. During the performance test, the dynamic pitch-link forces and blade bending and torsion moments were also measured. Dynamic data from the forward flight investigation have been reduced and are presented herein. The advanced blade set was designed to have dynamic characteristics similar to those of the baseline rotor so that test conditions would not be limited by potential rotor instability and blade resonances and so that the measured performance increments could be considered to be due purely to aerodynamic causes. Data show consistent trends with advance ratio for both blade sets with generally higher oscillatory loads occurring for the advanced blade set when compared with the baseline blade set.
Book Synopsis Wind-tunnel Evaluation of an Advanced Main-rotor Blade Design for a Utility-class Helicopter by : William T. Yeager (Jr.)
Download or read book Wind-tunnel Evaluation of an Advanced Main-rotor Blade Design for a Utility-class Helicopter written by William T. Yeager (Jr.) and published by . This book was released on 1987 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley Transonic Dynamics Tunnel to evaluate differences between an existing utility-class main-rotor blade and an advanced-design main-rotor blade. The two rotor-blade designs were compared with regard to rotor performance, oscillatory pitch-link loads, and 4-per-rev vertical fixed-system loads. Tests were conducted in hover and over a range of simulated full-scale gross weights and density altitude conditions at advance ratios from 0.15 to 0.40. Results indicate that the advanced-blade design offers performance improvements over the baseline blade in both hover and forward flight. Pitch-link oscillatory loads for the baseline rotor were more sensitive to the test condition than those of the advanced blade was larger than that produced by the baseline blade at all test conditions.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721101931 Total Pages :132 pages Book Rating :4.1/5 (19 download)
Book Synopsis Wind Tunnel Evaluation of a Model Helicopter Main-Rotor Blade with Slotted Airfoils at the Tip by : National Aeronautics and Space Administration (NASA)
Download or read book Wind Tunnel Evaluation of a Model Helicopter Main-Rotor Blade with Slotted Airfoils at the Tip written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt: Data for rotors using unconventional airfoils are of interest to permit an evaluation of this technology's capability to meet the U.S. Army's need for increased helicopter mission effectiveness and improved safety and survivability. Thus, an experimental investigation was conducted in the Langley Transonic Dynamics Tunnel (TDT) to evaluate the effect of using slotted airfoils in the rotor blade tip region (85 to 100 percent radius) on rotor aerodynamic performance and loads. Four rotor configurations were tested in forward flight at advance ratios from 0.15 to 0.45 and in hover in-ground effect. The hover tip Mach number was 0.627, which is representative of a design point of 4000-ft geometric altitude and a temperature of 95 F. The baseline rotor configuration had a conventional single-element airfoil in the tip region. A second rotor configuration had a forward-slotted airfoil with a -6 deg slat, a third configuration had a forward-slotted airfoil with a -10 slat, and a fourth configuration had an aft-slotted airfoil with a 3 deg flap (trailing edge down). The results of this investigation indicate that the -6 deg slat configuration offers some performance and loads benefits over the other three configurations. Noonan, Kevin W. and Yeager, William T., Jr. and Singleton, Jeffrey D. and Wilbur, Matthew L. and Mirick, Paul H. Langley Research Center RTOP 581-10-11-01
Book Synopsis Wind-tunnel Evaluation of an Advanced Main-rotor Blade Design for a Utility-class Helicopter by :
Download or read book Wind-tunnel Evaluation of an Advanced Main-rotor Blade Design for a Utility-class Helicopter written by and published by . This book was released on 1987 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Vibratory Loads Data from a Wind-tunnel Test of Structurally Tailored Model Helicopter Rotors by : William T. Yeager
Download or read book Vibratory Loads Data from a Wind-tunnel Test of Structurally Tailored Model Helicopter Rotors written by William T. Yeager and published by . This book was released on 1991 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-Tunnel Testing of Aeroelastically Scaled Helicopter Rotor Models by : Charles Eugene Hammond
Download or read book Wind-Tunnel Testing of Aeroelastically Scaled Helicopter Rotor Models written by Charles Eugene Hammond and published by . This book was released on 1976 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: The use of aeroelastically scaled helicopter rotor wind-tunnel models in establishing or verifying the dynamic characteristics of new or existing rotor designs is discussed. A model, termed the generalized rotor aeroelastic model (GRAM), which has been developed for testing aeroelastically scaled rotor models is described, and the utility of the model in being able to test a variety of rotor systems to meet a broad range of test objectives is demonstrated though presentation of data from recent tests. Data are presented from tests of an AH-1G Cobra model to determine whether or not the two-blade teetering rotor can experience stall flutter, tests of two wide chord teetering rotors to evaluate the effect of the wide chord on blade loads and rotor performance, and tests of a new four-blade flex-hinge rotor configuration to provide information for the designer relative to its dynamic characteristics. Since the GRAM was developed for testing in a wind tunnel which has the capability of using Freon-12 as a test medium, some of the advantages of Freon-12 for testing of aeroelastically scaled models are also discussed. (Author).
