Download or read book Wind Tunnel Test of a Freefall Vehicle for Parachute Testing written by David Brian Landrum and published by . This book was released on 1984 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Tests of a Series of 18 foot diameter Parachutes with Extendable Flaps written by Berl Gamse and published by . This book was released on 1962 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Full scale Drop Tests and Scaled Model Wind Tunnel Tests of Ribbon Parachutes written by William B. Pepper and published by . This book was released on 1961 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sandia Corporation has been working on parachute systems for vehicle recovery since 1954. Our general approach has been to treat the parachute as we would other aerodynamic problems such as vehicle stability. We have endeavored to conduct scaled parachute model tests in the wind tunnel to study forces, pressures, and dynamic stability of vehicle-parachute systems.

Download or read book Wind tunnel Tests of a Series of Parachutes Designed for Controllable Gliding Flight written by James A. Weiberg and published by . This book was released on 1967 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transonic Wind tunnel Tests of a Lifting Parachute Model written by and published by . This book was released on 1976 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Test Fixture and Data Acquisition System for Wind Tunnel Testing of Parachutes written by Charles J. Silcot and published by . This book was released on 1968 with total page 235 pages. Available in PDF, EPUB and Kindle. Book excerpt: After the analysis of the means of measuring the force and stability characteristics of flexible, steerable, gliding parachutes in the AFFDL 12-foot open-throat vertical wind tunnel at Wright-Patterson Air Force Base, a system was designed, fabricated, installed, and tested for acceptance. This system consists of two major components: The first major component, a test fixture-balance assembly, provides the means of remotely operating model parachutes through various roll, pitch, and yaw angles. This assembly consists basically of a roll-traversing mechanism which supports a sting balance as it rolls and yaws along the inner perimeter of a semicircular trussed hoop. The hoop rests on a two-part structure designed for temporary installment above the tunnel lip. For the parachute attachment and positioning, the sting balance was selected in a preliminary study in preference to the wire or strut type of balance. The second major component, a data acquisition and readout system, displays and records in digital form the normal and axial forces and the moments at various canopy pitch, roll, and yaw attitudes. In the acceptance tests with a 9.375-foot steerable parachute canopy, lift, drag, and pitching moment were obtained at various angles of pitch and at air velocities ranging from 50 to 100 feet per second.

Download or read book Wind tunnel Tests of Modified Cross Hemisflo and Disk gap band Parachutes with Emphasis in the Transonic Range written by James T. Foughner and published by . This book was released on 1974 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic wind-tunnel studies were conducted with modified cross, hemisflo, and disk-gap-band parachute models in the wake of a cone-cylinder shape forebody. The basic cross design was modified with the addition of a circumferential constraining band at the lower edge of the canopy panels. The tests covered a Mach number range of 0.3 to 1.2 and a dynamic pressure range from 479 Newtons per square meter to 5746 Newtons per square meter. The parachute models were flexible textile-type structures and were tethered to a rigid forebody with a single flexible riser. Different size models of the modified cross and disk-gap-band canopies were tested to evaluate scale effects. Model reference diameters were 0.30, 0.61, and 1.07 meters (1.0, 2.0, and 3.5 ft) for the modified cross; and nominal diameters of 0.25 and 0.52 meter (0.83 and 1.7 ft) for the disk-gap-band; and 0.55 meter (1.8 ft) for the hemisflo. Reefing information is presented for the 0.61-meter-diameter cross and the 0.52-meter-diameter disk-gap-band. Results are presented in the form of the variation of steady-state average drag coefficient with Mach number. General stability characteristics of each parachute are discussed. Included are comments on canopy coning, spinning, and fluttering motions.

Download or read book Wind Tunnel Testing of Small Scale Parachute Models and Comparison with Theory written by Sonia Gulbankian and published by . This book was released on 1994 with total page 294 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Investigation of Drag and Stabili Ty of Parachutes at Supersonic Speeds written by Nickolai Charczenko and published by . This book was released on 1964 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Report on Vortex Ring Parachute Wind Tunnel Tests at United Aircraft Corporation written by David T. Barish and published by . This book was released on 1959 with total page 111 pages. Available in PDF, EPUB and Kindle. Book excerpt: The program consisted of testing of full scale parachutes in the 33 foot square settling section, and the measurement of the deployments of deceleration chutes in the 18 foot octagonal test section. Drag measurements on two versions of the Vortex Ring Chute 21.7 feet and 32.5 feet in diameter gave values of drag coefficient, more than 1.8 times that measured with a 28' diameter flat circular chute in the same test section. Correlations with small scale wind tunnel tests are also included. A large number of deployments of the 260" diameter drag chutes were conducted in the test section at speeds from 50 mph to 187 mph. Dynamic force measurements indicated rapid deployment, low shock factor and stable operation. A new pilot chute installation gave good deployment characteristics and stable operation.

Download or read book Wind tunnel Tests of a Series of 18 foot diameter Parachutes with Extendable Flaps written by Berl Gamse and published by . This book was released on 1962 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transonic Wind tunnel Tests of a Lifting Parachute Model written by Jerome T. Foughner and published by . This book was released on 1976 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel tests have been made in the Langley transonic dynamics tunnel on a 0.25-scale model of Sandia Laboratories 3.96-meter (13-foot), slanted ribbon design, lifting parachute. The lifting parachute is the first stage of a proposed two-stage payload delivery system. The lifting parachute model was attached to a foerbody representing the payload. The forebody was designed and installed in the test section in a manner which allowed rotational freedom about the pitch and yaw axes. Values of parachute axial force coefficient, rolling moment coefficient, and payload trim angles in pitch and yaw are presented through the transonic speed range. Data are presented for the parachute in both the reefed and full open conditions. Time history records of lifting parachute deployment and disreefing tests are included.

Download or read book Summary of Parachute Wind Tunnel Testing Methods at Sandia National Laboratories written by R. H. Croll and published by . This book was released on 1981 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt: At Sandia, wind tunnel testing of parachutes provides a useful and less expensive alternative to the more traditional flight test methods for the evaluation and development of candidate parachute systems for a wide variety of aerospace applications. The flexible, porous nature of parachutes and the requirement to operate over large and dynamic ranges of velocity and altitude provide challenging test requirements. The special wind tunnel hardware, test techniques, and novel instrumentation which have evolved to support these development programs on full- and quarter-scale parachutes will be presented.

Download or read book Full scale Wind tunnel Investigation of a Flexible wing Manned Test Vehicle written by Joseph L. Johnson and published by . This book was released on 1963 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Tests to Evaluate a Lifting Transonic Parachute written by R. E. Rychnovsky and published by . This book was released on 1975 with total page 7 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program to develop a two-step lifting parachute system for low altitude payload delivery at velocities up to Mach 1.2 is being conducted at Sandia Laboratories. Wind tunnel tests on scaled models have been used extensively in the development. The test objectives were to establish the feasibility of constructing a lifting parachute with the desired characteristics, to select the most promising design and construction technique from several candidate models, to optimize the performance of this model and to measure its aerodynamic coefficients. A description of the types of tests, the models and test hardware as well as pertinent results and future test plans are presented.

Download or read book Wind tunnel Investigation of the Static Aerodynamic Characteristics of a Multilobe Gliding Parachute written by George M. Ware and published by . This book was released on 1968 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Tests on Clusters of Parachutes written by E. I. Auterson and published by . This book was released on 1945 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: