2 edition of Wind-tunnel test of an articlulated helicopter rotor model with several tip shapes found in the catalog.
Wind-tunnel test of an articlulated helicopter rotor model with several tip shapes
John D Berry
by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va
Written in English
|Statement||John D. Berry and Raymond E. Mineck|
|Series||NASA technical memorandum -- 80080, AVRADCOM technical report -- 79-49|
|Contributions||Mineck, Raymond E, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, United States. Army Aviation Research and Development Command, Army Research and Technology Laboratories (U.S.). Structures Laboratory|
|The Physical Object|
|Pagination||92 p. :|
|Number of Pages||92|
Aerodynamic design optimization of helicopter rotor blades including airfoil shape for forward flight and airfoil on rotor performance. Their wind tunnel test demonstrates significant improvements that can be gained from planform The drag–divergence Mach number at zero lift is a measure of the usefulness of a section near the tip of a Cited by: COVID Resources. Reliable information about the coronavirus (COVID) is available from the World Health Organization (current situation, international travel).Numerous and frequently-updated resource results are available from this ’s WebJunction has pulled together information and resources to assist library staff as they consider how to handle coronavirus.
Model 35 has an area = 6 sq. in. and a rectangular planform with an AR = The cross section was called a "bird wing" section and involved multiple curves and a thickening near the leading edge. Model 35 should be compared to Model 12 and Model 9 for a . book The field of flow through a helicopter rotor obtained from wind tunnel smoke tests J Meijer Drees, W. P Hendal Published in in Amsterdam by NLLCited by:
The HART-II Test: Rotor Wakes and Aeroacoustics with Higher-Harmonic Pitch Control (HHC) Inputs - The Joint German/French/Dutch/US Project Yung H. Yu, Chee Tung Aeroflightdynamics Directorate (AFDD) US Army Aviation and Missile Command (AMCOM) Moffett Field, CA. From Summary: "A portion of a PV-2 helicopter rotor blade has been tested in the 6- by 6-foot test section of the Langley stability tunnel to determine if the aerodynamic characteristics were seriously affected by cross flow or fabric distortion. The outer portion of the blade was tested as a reflection plane model pivoted about the tunnel wall to obtain various angles of cross flow over the Author: William B. Kemp.
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Of a rotor, a wind-tunnel test has been conducted using a single articulated model rctor system with five interchangeable sets of blade tips. Subsequent to the first test, a sixth tip shape was evaluated for performance in c limited E-ange of flight conditions.
The first five tip shapes were evaluated fc;c acous. Wind-tunnel test of an articlulated helicopter rotor model with several tip shapes. Washington, D.C.: National Aeronautics and Space Administrat ion, Scientific and Technical Information Branch ; [Springfield, Va.: Fo r sale by the National Technical Information Service], Six interchangeable tip shapes were tested: a square (baseline) tip, an ogee tip, a subwing tip, a swept tip, a winglet tip, and a short ogee tip.
In hover at the lower rotational speeds the swept, ogee, and short ogee tips had about the same torque coefficient, and the subwing and winglet tips had a larger torque coefficient than the baseline square tip : R. Mineck and J.
Berry. Six interchangeable tip shapes were tested: a square (baseline) tip, an ogee tip, a subwing tip, a swept tip, a winglet tip, and a short ogee tip. In hover at the lower rotational speeds the swept, ogee, and short ogee tips had about the same torque coefficient, and the subwing and winglet tips had a larger torque coefficient than the baseline square tip blades.
Wind-tunnel test of an articlulated helicopter rotor model with several tip shapes / By John D. Berry, Raymond E. Mineck, Army Research and Technology Laboratories (U.S.). Abstract. Numerical studies of the tip vortex structure from a hovering rotor with and without various spoilers are presented.
A general multizone unsteady three-dimensional Navier-Stokes solver is developed to determine the by: 1. Development of a Wind Tunnel Test Apparatus for Horizontal Axis Wind Turbine Rotor Testing by Michael K.
McWilliam A thesis presented to the University of Waterloo in fulﬁllment of the thesis requirement for the degree of Master of Applied Science in Mechanical Engineering Waterloo, Ontario, Canada, °c Michael K.
McWilliam Wind Tunnel Testing to Determine Unsteady Loads on a Helicopter Fuselage in a Ship Airwake trol Frigate (CPF) used in previous airwake experi-ments . Small structures located in front of the he-licopter hangar, such as wire antennas, handrails, a small lattice radar-mast, and 57 mm cannon, were not included inthe model.
Froman aerodynamic. Such vortical structures at a helicopter rotor model in a wind tunnel has been studied by optical measurement techniques, since only non-intrusive techniques are capable to obtain velocity data. Then, rotor blade tip shapes that have been used, or suggested for use, on past and present rotorcraft are examined to obtain a better understanding of the helicopter tip design problem.
have also been reported from numerous model and full-scale rotor wind tunnel tests. On-blade active control using smart materials has recently been applied in a number of model scale [10 16] and full-scale rotor experimental programs [8,17,18].
Piezoelectric materials are used for high frequency actuation at small amplitudes. Wind Tunnel Evaluation of a Model Helicopter Main-Rotor Blade With Slotted Airfoils at the Tip Kevin W. Noonan Joint Research Program Office Aeroflightdynamics Directorate U.S.
Army Aviation and Missile Command Langley Research Center, Hampton, Virginia William T. Yeager, Jr., Jeffrey D. Singleton, Matthew L. Wilbur, and Paul H. Mirick. The tunnel test section is m The model rotor test pvesented some unusual hurdles to overcome in the tunnel entry.
Person- nel in the control room or other acce:slviewing areas to the test section had to be protected from the potential catastrophic failure of the rotating hardware. A set of armor plates onFile Size: 6MB.
This video highlights research into flow fields generated from rotorcraft to better understand their aerodynamic properties and enable the design of next gen. SMART helicopter Rotor Wind Tunnel Test. The benefits of high frequency, helicopter blade pitch control have been pursued under the DOD and NASA rotary wing technology programs for decades.
Yet mechanical implementation of higher harmonic control is limited in blade pitch frequencies and requires substantial hydraulic power to dynamically alter the blade pitch around the azimuth.
CONCLUDING REMARKS Wind-tunnel tests were performed on a four-bladed articulated rotor model to determine the effects on rotor dynamic response and aerodynamic performance of modifying the blade tip design. The aeroelastic rotor model was constructed such that the outboard 8 percent of the blade could be altered.
Wind Tunnel Testing of an Advanced UH‐1 Type Rotor System Journal of the American Helicopter Society, Vol. 28, No. 2 V/STOL Aircraft Model in Wind-Tunnel Testing from Model Cited by: 9. than 10% of the rotor thrust. Wind Tunnel Test Results. The test results reported here consist of four runs (described in table 1), at nominal longitudinal separation distances of x/D =, and (two runs at x/D = ).
The wind tunnel speed gave an advance ratio of µ Cited by: Full-Scale Wind Tunnel Test of a Modern Helicopter Main Rotor - Investigation of Tip Mach Number Effects and Comparisons of Four Tip Shapes Robert M. Stroub Your Path: Home > Full-Scale Wind Tunnel Test of a Modern Helicopter Main Rotor - Investigation of Tip Mach Number Effects and Comparisons of Four Tip ShapesCited by: 3.
Wind-tunnel test of an articlulated helicopter rotor model with several tip shapes / (Washington, D.C.: National Aeronautics and Space Administrat ion, Scientific and Technical Information Branch ; [Springfield, Va.: Fo r sale by the National Technical Information Service], ), by John D.
Berry, Raymond E. Mineck, Army Research and. SMART Rotor Development and Wind Tunnel Test 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) The Boeing Company,Mesa,AZ, 8.
PERFORMING ORGANIZATION REPORT NUMBER by: by DLR of a set of 5 “series” blades (including one spare blade) for the wind-tunnel tests . The latest main step of the ABC project was the test campaign in December in S1 Modane wind-tunnel of this active flap-equipped rotor model which is described in details in.
High Advance Ratio Test conducted by Continuum Dynamics at University of Maryland. Wind Speed: ft/s, I think this advance ratio is between 1 and