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Book Wind tunnel Investigation of the Drag and Static Stability Characteristics of Four Helicopter Fuselage Models

Download or read book Wind tunnel Investigation of the Drag and Static Stability Characteristics of Four Helicopter Fuselage Models written by George E. Sweet and published by . This book was released on 1962 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book A Wind tunnel Investigation of the Longitudinal Aerodynamic Charachteristics of Two Full scale Helicopter Fuselage Models with Appendages

Download or read book A Wind tunnel Investigation of the Longitudinal Aerodynamic Charachteristics of Two Full scale Helicopter Fuselage Models with Appendages written by Julian L. Jenkins and published by . This book was released on 1962 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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

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.

Book Aerodynamic Characteristics of Several Current Helicopter Tail Boom Cross Sections Including the Effect of Spoilers

Download or read book Aerodynamic Characteristics of Several Current Helicopter Tail Boom Cross Sections Including the Effect of Spoilers written by John C. Wilson and published by . This book was released on 1986 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic characteristics were determined of three cylindrical shapes representative of tail boom cross sections of the AH-64, UH-60, and UH-1H helicopters. Forces and pressures were measured in a wind-tunnel investigation. Data was obtained for a flow incidence range from -45 to 90 deg and a dynamic pressure range from 1.5 to 50 psf. These ranges provided data representative of full-scale Reynolds numbers and the full range of flow incidence to which these helicopter tail boom shapes would be subjected at low flight speeds. The effects of protuberances such as tail rotor drive-shaft covers and spoilers were evaluated. The data indicate that significant side loads on tail booms of helicopters can be generated and that the addition of spoilers can beneficially alter the side loads. Although an increase in vertical drag occurs, the net effect through reduction of tail rotor thrust required can be an improvement in helicopter performance. Keywords: Rotorcraft; Aerodynamics; Stability and control; Helicopters; Tail booms.

Book Full scale Wind tunnel Tests of a Small Unpowered Jet Aircraft with a T Tail

Download or read book Full scale Wind tunnel Tests of a Small Unpowered Jet Aircraft with a T Tail written by Paul T. Soderman and published by . This book was released on 1971 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.

Book Upgrade of a LabVIEW Based Data Acquisition System for Wind Tunnel Test of a 1 10 Scale OH 6A Helicopter Fuselage

Download or read book Upgrade of a LabVIEW Based Data Acquisition System for Wind Tunnel Test of a 1 10 Scale OH 6A Helicopter Fuselage written by Philipp A. Lines and published by . This book was released on 2003-06-01 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: For over half a century the NPS Aerolab Low Speed Wind Tunnel located in Halligan Hall of the Naval Postgraduate school has served to provide students and facility with meaningful aerodynamic data for research and problem analysis. New data acquisition hardware was installed three years ago but never fully verified, and contained no integrated software program to collect data from the strain-gauge balance pedestal. Existing National Instruments based hardware for the NPS low-speed wind tunnel was reconfigured to obtain data from the strain- gauge pedestal. Additionally, a data acquisition software program was written in LabVIEW(C) to accommodate the hardware. The Virtual Instruments (VI) program collects and plots accurate data from all four strain gauges in real-time, producing non-dimensional force and moment coefficients. A research study on the performance of an OH-6A helicopter fuselage was conducted. NPS Aerolab wind tunnel tests consisted of drag, lift, and pitching moment measurements of the OH-6A along yaw and angle-of attack sweeps. The results of the NPS wind tunnel data were compared against testing conducted on a full-scale OH-6A helicopter in NASA Ames' 40 ft. x 80ft. wind tunnel, along with the U.S. Army's Light Observation Helicopter (LOH) wind tunnel tests. Results of current testing substantiate the LabVIEW(C) code.

Book Wind Tunnel flight Data Correlation u

Download or read book Wind Tunnel flight Data Correlation u written by James A. Behal and published by . This book was released on 1971 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.

Book Two dimensional Aerodynamic Characteristics of Several Polygon shaped Cross sectional Models Applicable to Helicopter Fuselages

Download or read book Two dimensional Aerodynamic Characteristics of Several Polygon shaped Cross sectional Models Applicable to Helicopter Fuselages written by Henry L. Kelley and published by . This book was released on 1992 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind tunnel Investigation of the Aerodynamic and Structural Deflection Characteristics of the Goodyear Inflatoplane

Download or read book Wind tunnel Investigation of the Aerodynamic and Structural Deflection Characteristics of the Goodyear Inflatoplane written by Bennie W. Cocke (Jr.) and published by . This book was released on 1958 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation has been conducted in the Langley full-scale tunnel to determine the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane over a range of test velocities from minimum stall speed up to speeds giving load factors for wing buckling. Tests were conducted over a range of speeds from approximately 41 to 70 mph with wing-guy-cable loads, wing-distortion photographs, and aerodynamic-force data recorded at each speed for a full range of angle of attack.