Books on the topic 'Helicopter rotor blade design'

Yeager, William T. Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter. Hampton, Va: Langley Research Center, 1987.

Chattopadhyay, Aditi. Performance of an optimized rotor blade at off-design flight conditions. Washington, DC: National Aeronautics and Space Administration, 1990.

Singleton, Jeffrey D. Performance data from a wind-tunnel test of two main-rotor blade designs for a utility-class helicopter. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

Chattopadhyay, Aditi. Minimum design of rotorcraft blades with multiple frequency and stress constraints. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

Bielawa, Richard L. Analytic investigation of helicopter rotor blade appended aeroelastic devices. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

Zhao, Xin. A study of helicopter stability and control including blade dynamics. [Princeton, N.J.]: Princeton University, Dept. of Mechanical nad Aerospace Engineering, 1988.

Kvaternik, Raymond G. Airframe structural dynamic considerations in rotor design optimization. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

King, Robert L. Nonlinear dynamics in the modeling of helicopter rotor blade lead/lag motion. Monterey, Calif: Naval Postgraduate School, 1999.

Connor, Andrew B. Correlation of helicopter impulsive noise from blade-vortex interaction with rotor mean inflow. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

Acoustic source and data acquisition system for a helicopter rotor blade-vortex interaction (BVI) noise reduction experiment. Monterey, Calif: Naval Postgraduate School, 1996.

Lance, Michael B. Low-speed wind-tunnel test of an unpowered high-speed stoppable rotor concept in fixed-wing mode. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

Lance, Michael B. Low-speed wind-tunnel test of an unpowered high-speed stoppable rotor concept in fixed-wing mode. Hampton, Va: Langley Research Center, 1991.

Chen, Robert T. N. Acoustic flight tests of rotorcraft noise-abatement approaches using local differential GPS guidance. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1995.

Chen, Robert T. N. Acoustic flight tests of rotorcraft noise-abatement approaches using local differential GPS guidance. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1995.

L, Walsh Joanne, Young Katherine C, and United States. National Aeronautics and Space Administration., eds. Application of response surface techniques to helicopter rotor blade optimization procedure. [Washington, DC]: National Aeronautics and Space Administration, 1995.

Application of response surface techniques to helicopter rotor blade optimization procedure. [Washington, DC]: National Aeronautics and Space Administration, 1995.

T, Yaeger William, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., eds. Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

T, Yaeger William, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., eds. Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. Performance of an optimized rotor blade at off-design flight conditions. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

Optimization methods applied to the aerodynamic design of helicopter rotor blades. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

Y, Chu Alphonse, Talbot Peter D, and United States. National Aeronautics and Space Administration., eds. Synthesis of individual rotor blade control system for gust alleviation: Final report. [Washington, D.C: National Aeronautics and Space Administration, 1990.

An enhanced integrated aerodynamic load/dynamic optimization procedure for helicopter rotor blades. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

T, Yeager William, Wilbur Matthew L, United States. Army Aviation Research and Technology Activity., and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Performance data from a wind-tunnel test of two main-rotor blade designs for a utility-class helicopter. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

L, Walsh Joanne, and Langley Research Center, eds. Minimum design of rotorcraft blades with multiple frequency and stress constraints. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

Analysis, design and elastic tailoring of composite rotor blades: Final report. Atlanta, Ga: Center for Rotary Wing Aircraft Technology, Georgia Institute of Technology, 1987.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., ed. Preliminary structural design of composite main rotor blades for minimum weight. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

Investigation of helicopter rotor blade/wake interactive impulsive noise. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

Shau-Tak, Chou, and United States. National Aeronautics and Space Administration., eds. Helicopter tail rotor blade-vortex interaction noise: Final technical report. [Washington, DC: National Aeronautics and Space Administration, 1989.

Effects of planform geometry on hover performance of a 2-meter-diameter model of a four-bladed rotor. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

Sreekanta, Murthy T., and Langley Research Center, eds. Airframe structural dynamic considerations in rotor design optimization. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

J, Shamroth S., Buggeln R. C, and Ames Research Center, eds. Calculation of helicopter rotor blade/vortex interaction by Navier-Stokes procedures. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

N, Duque Earl P., and United States. National Aeronautics and Space Administration., eds. Helicopter rotor blade computation in unsteady flows using moving overset grids. Washington, DC: American Institute of Aeronautics and Astronautics, 1996.

Vandenbos, Bruce A. Computer program for conceptual tandem rotor helicopter design. 1987.

H, Mirick Paul, Langston Chester W, and Langley Research Center, eds. Rotating shake test and modal analysis of a model helicopter rotor blade. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

H, Yu Yung, and United States. National Aeronautics and Space Administration., eds. Reduction of helicopter blade-vortex interaction noise by active rotor control technology. [Washington, D.C: National Aeronautics and Space Administration, 1997.

Nonlinear Dynamics in the Modeling of Helicopter Rotor Blade Lead/Lag Motion. Storming Media, 1999.

G, Bousman William, and Ames Research Center, eds. Aerodynamic limitations of the UH-60A rotor. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1996.

L, Wells Valana, Lanananen David H, and United States. National Aeronautics and Space Administration., eds. The potential of genetic algorithms for conceptual design of rotor systems. [Washington, DC: National Aeronautics and Space Administration, 1993.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. Aerodynamic performance of a 0.27-scale model of an AH-64 helicopter with baseline and alternate rotor blade sets. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

1936-, Smith Charles D., LeMasurier Phillip, and Langley Research Center, eds. Helicopter far-field acoustic levels as a function of reduced main-rotor advancing blade-tip Mach number. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

I, Pritchard Jocelyn, United States. Army Aviation Research and Technology Activity., and Langley Research Center, eds. Optimizing tuning masses for helicopter rotor blade vibration reduction including computed airloads and comparison with test data. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

Acoustic Source and Data Acquisition System for a Helicopter Rotor Blade-Vortex Interaction (BVI) Noise Reduction Experiment. Storming Media, 1996.

Helicopter far-field acoustic levels as a function of reduced main-rotor advancing blade-tip Mach number. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

1936-, Smith Charles D., LeMasurier Phillip, and Langley Research Center, eds. Helicopter far-field acoustic levels as a function of reduced main-rotor advancing blade-tip Mach number. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. Prediction of helicopter rotor discrete frequency noise: A computer program incorporating realistic blade motions and advanced acoustic formulation. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

Facility, Dryden Flight Research, ed. Higher harmonic control analysis for vibration reduction of helicopter rotor systems. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1994.

Facility, Dryden Flight Research, ed. Higher harmonic control analysis for vibration reduction of helicopter rotor systems. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1994.

T, Yeager William, and Langley Research Center, eds. Performance and vibratory loads data from a wind-tunnel test of a model helicopter main-rotor blade with a paddle-type tip. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

Center, Ames Research, ed. Symbolic generation of elastic rotor blade equations using a FORTRAN processor and numerical study on dynamic inflow effects on the stability of helicopter rotors. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1987.