Download or read book Free Spinning Tunnel Tests of a 1 27 Scale Model of the Douglas Xf3d 1 Airplane Ted No Naca De 312 written by Stanley H. Scher and published by BiblioGov. This book was released on 2013-07 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Free-spinning-tunnel tests have been made on a 1/27-scale model of the Douglas XF3D-1 airplane to confirm a preliminary evaluation made of the airplane spin and recovery characteristics and previously reported. Recovery characteristics were satisfactory for erect and inverted spins when the model was in the clean condition. When the slow-down brakes were open, recoveries were slow. The pedal force necessary to reverse the airplane rudder during a spin will be within the physical capabilities of the pilot. A 10-foot-diameter parachute attached to the tail of the airplane (laid-out-flat diameter, drag coefficient 0.7) or a 4.5-foot-diameter parachute attached to the outboard wing tip will be satisfactory for emergency spin recovery from demonstration spins. If it becomes necessary for the crew to abandon the airplane during a spin, they should leave from the outboard side of the cockpit. The test results indicated spin and recovery characteristics generally similar to those indicated in the preliminary evaluation.
Download or read book Free spinning Tunnel Investigation of a 1 20 scale Model of the Douglas X 3 Airplane written by Burton E. Hultz and published by . This book was released on 1951 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free spinning Wind tunnel Tests of a 1 23 75 scale Model of the Douglas DC 3 Airplane written by Oscar Seidman and published by . This book was released on 1942 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free spinning tunnel Tests of a 1 23 75 scale Model of the Douglas DC 3 Airplane written by Oscar Seidman and published by . This book was released on 1942 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A model of the Douglas DC-3 airplane was tested in the 20-foot free-spinning tunnel for several loading conditions. The load factor for the airplane as a whole, the load on the horizontal tail, and the force required to start moving the elevator downward were estimated for some of the steady spins. The altitude loss in the recovery from a spin and in the pull-out from the ensuing dive was also determined. Although recoveries were fairly rapid, it was concluded that, because of possible structural overload and high control forces, it would not be safe to put the DC-3 airplane into an established spin.
Download or read book Free Spinning Tunnel Investigation of a 1 20 Scale Model of an Unswept Wing Jet Propelled Trainer Airplane written by and published by . This book was released on 1960 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free Spinning Tunnel Tests of a 1 24 Scale Model of the North American Xp 86 Airplane written by Theodore Berman and published by BiblioGov. This book was released on 2013-07 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the North American XP-86 airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the design gross weight loading. The long-range loading was also investigated and the effects of extending slats and dive flaps were determined. In addition, the investigation included the determination of the size of spin-recovery parachute required for emergency recovery from demonstration spins, the rudder force required to move the rudder for recovery, and the best method for the pilot to escape if it should become necessary to do so during a spin. The results of the investigation indicated that the XP-86 airplane will probably recover satisfactorily from erect and inverted spins for all possible loadings. It was found that fully extending both slats would be beneficial but that extending the dive brakes would cause unsatisfactory recoveries. It was determined that a 10.0-foot-diameter tail parachute with a drag coefficient of 0.7 and with a towline 30.0 feet long attached below the jet exit or a 6.0-foot-diameter wingtip parachute opened on the outer wing tip with a towline 6.0 feet long would insure recoveries from any spins obtainable. The rudder-pedal force necessary to move the rudder for satisfactory recovery was found to be within the physical capabilities of the pilot.
Download or read book Ditching Investigation of a 1 12 Scale Model of the Douglas F4d 1 Airplane Ted No Naca De 384 written by John O. Windham and published by BiblioGov. This book was released on 2013-07 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A ditching investigation was made of a l/l2-scale dynamically similar model of the Douglas F4D-1 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tables, sequence photographs, time-history acceleration curves, and attitude curves. From the results of the investigation, it was concluded that the airplane should be ditched at the lowest speed and highest attitude consistent with adequate control (near 22 deg) with landing gear retracted. In a calm-water ditching under these conditions the airplane will probably nose in slightly, then make a fairly smooth run. The fuselage bottom will sustain appreciable damage so that rapid flooding and short flotation time are likely. Maximum longitudinal deceleration will be about 4g and maximum normal acceleration will be about 6g in a landing run of about 420 feet, In a calm-water ditching under similar conditions with the landing gear extended, the airplane will probably dive. Maximum longitudinal decelerations will be about 5-1/2g and maximum normal accelerations will be about 3-1/2g in a landing run of about 170 feet.
Download or read book Free Spinning Tunnel Investigation of a 1 25 Scale Model of the Chance Vought F8U 1P Airplane written by and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free spinning Tunnel Tests of a Model of a Canard Airplane written by Philip W. Pepoon and published by . This book was released on 1943 with total page 8 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of tests was made in the NACA 15-Foot free-spinning tunnel to study the spin characteristics of a 1/24-scale model of a hypothetical canard airplane, which was designed to be the same size and to have the same general aerodynamic characteristics as a Boeing B-247 airplane. The model had a single fin and rudder at the rear of the fuselage.
Download or read book Free Spinning Tunnel Tests of a 1 24 Scale Model of the Mcdonnell Xp 88 Airplane with a Conventional Tail written by Theodore Berman and published by BiblioGov. This book was released on 2013-07 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the normal loading were determined. Tests of the model in the long-range loading also were made. The investigation included tail-modification, spin-recovery parachute, pilot-escape, and rudder-pedal-force tests. Recoveries were generally satisfactory for spins in the normal loading provided the ailerons were not held against the spin. Satisfactory recoveries were obtained regardless of the aileron setting when the leading-edge flaps were deflected and normal recovery technique was used or when the horizontal tail was raised 70 inches, full scale. Recoveries were rapid from all inverted spins obtained. In the long-range loading with tanks on, it may be necessary to jettison the tanks in order to obtain recovery. A 12.0-foot spin-recovery parachute at the tail or a 4.0-foot parachute opened on the outer wing tip (drag coefficient of 0.66) was found to be effective for recoveries from demonstration spins. Test results showed that in an emergency the pilot should attempt to escape from the outboard side of the spinning airplane. The rudder-pedal forces in a spin were indicated to be within the capabilities of the pilot.
Download or read book Free Spinning Tunnel Investigation of a 1 30 Scale Model of a Twin Jet Swept Wing Fighter Airplane written by and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Spin tunnel Tests of a 1 57 33 scale Model of the Northrop XB 35 Airplane written by Robert W. Kramm and published by . This book was released on 1944 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 1/57.33-scale model of the Northrop XB-35 airplane has been tested in the NACA free-spinning tunnel in order to determine the spin characteristics and the tumbling tendencies of the airplane. The XB-35 airplane is a large four-engine bomber of the flying-wing type. It has elevon control surfaces which are used as ailerons or elevators. The airplane is equipped with conventional split flaps whose pitching moments are trimmed out by pitch flaps at the wing tips. The rear portions of the pitch flaps are split and can be deflected as rudders.
Download or read book Spinning Tunnel Tests of a 1 12 Scale Model Cornell Aircraft written by L. T. Conlin and published by . This book was released on 1944 with total page 8 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free Spinning Tunnel Investigation of a 1 20 Scale Model of the North American T2J 1 Airplane written by and published by . This book was released on 1959 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Spinning tunnel Tests on a 1 12th Scale Model Fleet Frontier 4 place Aircraft written by L. T. Conlin and published by . This book was released on 1946 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Ditching Tests of a 1 24 Scale Model of the Lockheed Xr60 1 Airplane Ted No Naca 235 written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The ditching characteristics of the Lockheed XR60-1 airplane were determined by tests of a 1/24-scale dynamic model in calm water at the Langley tank no. 2 monorail. Various landing attitudes, flap settings, speeds, and conditions of damager were investigated. The ditching behavior was evaluated from recordings of decelerations, length of runs, and motions of the model. Scale-strength bottoms and simulated crumpled bottoms were used to reproduce probable damage to the fuselage. It was concluded that the airplane should be ditched at a landing attitude of about 5 deg with flaps full down. At this attitude, the maximum longitudinal deceleration should not exceed 2g and the landing run will be bout three fuselage lengths. Damage to the fuselage will not be excessive and will be greatest near the point of initial contact with the water.
Download or read book The Cutting Edge written by Mark A. Lorell and published by Rand Corporation. This book was released on 1998 with total page 247 pages. Available in PDF, EPUB and Kindle. Book excerpt: The proposition that innovation is critical in the cost-effective design and development of successful military aircraft is still subject to some debate. RAND research indicates that innovation is promoted by intense competition among three or more industry competitors. Given the critical policy importance of this issue in the current environment of drastic consolidation of the aerospace defense industry, the authors here examine the history of the major prime contractors in developing jet fighters since World War II. They make use of an extensive RAND database that includes nearly all jet fighters, fighter-attack aircraft, and bombers developed and flown by U.S. industry since 1945, as well as all related prototypes, modifications, upgrades, etc. The report concludes that (1) experience matters, because of the tendency to specialize and thus to develop system-specific expertise; (2) yet the most dramatic innovations and breakthroughs came from secondary or marginal players trying to compete with the industry leaders; and (3) dedicated military R&D conducted or directly funded by the U.S. government has been critical in the development of new higher-performance fighters and bombers.
