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 Ditching Tests with a 1 10 size Model of the Army A 20A Airplane written by John R. Dawson and published by . This book was released on 1943 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: The tests reported herein are the first in a series of tests requested by the Army Air Forces to determine the behavior of landplanes when they are forced to land on the water. (The emergency landing of a landplane on water is called "ditching.") The tests are being made in NACA tank no. 2 with scale dynamic models (models having scale weight and scale moment of inertia about all axes).

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 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 Ditching Tests of a 1 20 Scale Model of the Northrop B 35 Airplane written by Lloyd J. Fisher and published by BiblioGov. This book was released on 2013-07 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests of a 1/20-scale dynamically similar model of the Northrop B-35 airplane were made to study its ditching characteristics. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated during the investigation. The ditching characteristics were determined by visual observation and from motion-picture records and time-history acceleration records. Both longitudinal and lateral accelerations were measured. Results are given in tabular form and time-history acceleration curves and sequence photographs are presented. Conclusions based on the model investigation are as follows: 1. The best ditching of the B-35 airplane probably can be made by contacting the water in a near normal landing attitude of about 9 deg with the landing flaps full down so as to have a low horizontal speed. 2. The airplane usually will turn or yaw but the motion will not be violent. The maximum lateral acceleration will be about 2g. 3. If the airplane does not turn or yaw immediately after landing, it probably will trim up and then make a smooth run or porpoise slightly. The maximum longitudinal decelerations that will be encountered are about 6g or 7g. 4. Although the decelerations are not indicated to be especially large, the construction of the airplane is such that extensive damage is to be expected, and it probably will be difficult to find ditching stations where crew members can adequately brace themselves and be reasonably sure of avoiding a large inrush of water

Download or read book Ditching Tests with a 1 12 size Model of the Army B 26 Airplane in NACA Tank No 2 and on an Outdoor Catapult written by Lloyd J. Fisher and published by . This book was released on 1944 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were made at the Langley Memorial Aeronautical Laboratory with a 1/12-size dynamic model of the Army B-26 airplane to determine its behavior when landed on water.

Download or read book Take Off and Landing Characteristics of a 0 13 Scale Model of the Convair Xfy 1 Vertically Rising Airplane in Steady Winds Ted No Naca De 368 written by Robert O. Shade and published by BiblioGov. This book was released on 2013-07 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation has been conducted to determine the stability and control characteristics of a 0.13-scale free-flight model of the Convair XFY-1 airplane during take-offs and landings in steady winds. The tests indicated that take-offs in headwinds up to at least 20 knots (full scale) will be fairly easy to perform although the airplane may be blown downstream as much as 3 spans before a trim condition can be established. The distance that the airplane will be blown down-stream can be reduced by restraining the upwind landing gear until the instant of take-off. The tests also indicated that spot landings in headwinds up to at least 30 knots (full scale) and in crosswinds up to at least 20 knots (full scale) can be accomplished with reasonable accuracy although, during the landing approach, there will probably be an undesirable nosing-up tendency caused by ground effect and by the change in angle of attack resulting from vertical descent. Some form of arresting gear will probably be required to prevent the airplane from rolling downwind or tipping over after contact. This rolling and tipping can be prevented by a snubbing line attached to the tip of the upwind' wing or tail or by an arresting gear consisting of a wire mesh on the ground and hooks on the landing gear to engage the mesh.

Download or read book Ditching Tests with a 1 10 size Model of the Army A 204 Airplane in Langley Tank No 2 and on an Outdoor Catapult written by George A. Jarvis and published by . This book was released on 1944 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Subsonic Flight Tests of a 1 7 scale Radio controlled Model of the North American X 15 Airplane with Particular Reference to High Angle of attack Conditions written by Donald E. Hewes and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Ditching Tests with a 1 10 size Model of the Army A 20A Airplane in Langley Tank No 2 and on an Outdoor Catapult written by George A. Jarvis and published by . This book was released on 1944 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests with a dynamically similar model of the army A-20A airplane were made to determine the best way to land the airplane in calm and rough water and to determine its probable ditching performance. The behavior was studied by making visual operations, by recording longitudinal decelerations, and by taking motion pictures of the landings.

Download or read book Flight Tests of a 0 13 Scale Model of the Convair Xfy 1 Vertically Rising Airplane with the Lower Vertical Tail Removed Ted No de 368 written by Powell M. Lovell and published by BiblioGov. This book was released on 2013-07 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation has been conducted to determine the dynamic stability and control characteristics in hovering and transition flight of a 0.13-scale flying model of the Convair XFY-1 vertically rising airplane with the lower vertical tail removed. The purpose of the tests was to obtain a general indication of the behavior of a vertically rising airplane of the same general type as the XFY-1 but without a lower vertical tail in order to simplify power-off belly landings in an emergency. The model was flown satisfactorily in hovering flight and in the transition from hovering to normal unstalled forward flight (angle of attack approximately 30deg). From an angle of attack of about 30 down to the lowest angle of attack covered in the flight tests (approximately 15deg) the model became progressively more difficult to control. These control difficulties were attributed partly to a lightly damped Dutch roll oscillation and partly to the fact that the control deflections required for hovering and transition flight were too great for smooth flight at high speeds. In the low-angle-of-attack range not covered in the flight tests, force tests have indicated very low static directional stability which would probably result in poor flight characteristics. It appears, therefore, that the attainment of satisfactory directional stability, at angles of attack less than 10deg, rather than in the hovering and transition ranges of flight is the critical factor in the design of the vertical tail for such a configuration.

Download or read book Ditching Tests of a 1 8 size Model of the Navy SB2C 1 Airplane Army A 25 in Langley Tank No 2 and on an Outdoor Catapult written by George A. Jarvis and published by . This book was released on 1946 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Tests in the NACA 19 foot Pressure Tunnel of a 1 10 75 scale Model of the Northrop XB 35 Tailless Airplane written by James C. Sivells and published by . This book was released on 1944 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Ditching Tests of Model CL 28 Aircraft written by E. S. Turner and published by . This book was released on 1958 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Model Tests on the Ditching of Landplanes in Waves and Across Wind written by D. C. MacPhail and published by . This book was released on 1943 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book High speed Wind tunnel Tests of a 1 16 Scale Model of the D 558 Research Airplane written by John B. Wright and published by . This book was released on 1948 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Stability and Control Tests of a 3 4 Scale Model of the KP 69 Airplane in the NACA Full Scale Tunnel written by and published by . This book was released on 1943 with total page 133 pages. Available in PDF, EPUB and Kindle. Book excerpt: