EBookClubs

Read Books & Download eBooks Full Online

EBookClubs

Read Books & Download eBooks Full Online

Book Free Spinning Tunnel Tests of a 1 24 Scale Model of the North American Xp 86 Airplane

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.

Book Free Spinning Tunnel Investigation of a 1 24 Scale Model of the Grumman Af 2s 2w Airplane

Download or read book Free Spinning Tunnel Investigation of a 1 24 Scale Model of the Grumman Af 2s 2w Airplane written by Walter J. Klinar and published by BiblioGov. This book was released on 2013-07 with total page 44 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 Grumman AF-2S, -2W airplane was conducted in the Langley 20-foot free-spinning tunnel. The effects of controls on the erect and inverted spin and recovery characteristics for a range of possible loadings of the.airplane were determined. The effect of a revised-tail installation (small dual fins added to the stabilizer of the original tail and the vertical-tail height of the original tail increased) and the effect of various ventral-fin and antispin-fillet installations were determined. The investigation also included spin-recovery parachute tests.

Book Spin Investigation of a 1 29 Scale Model of the Republic Xf 91 Airplane with a Conventional Tail Installed

Download or read book Spin Investigation of a 1 29 Scale Model of the Republic Xf 91 Airplane with a Conventional Tail Installed written by Walter J. Klinar and published by BiblioGov. This book was released on 2013-06 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley 20-foot free-spinning tunnel of a 1/29-scale model of the Republic XF-91 airplane with a.conventional-tail arrangement installed. Previously, tests were made on the model with a vee tail installed. The erect spin and recovery characteristics of the model were determined for the normal loading with the wing installed at various amounts of incidence. The spin investigation also included inverted-spin tests, spin-recovery-parachute tests, tests with the center of gravity moved rearward, and tests with external fuel tanks added to the model. In addition, several tail.modifications were tested, on the model in an attempt, to improve the model's spin-recovery characteristics. The results indicate that any fully developed spin obtained on the airplane with the conventional tail installed will be satisfactorily terminated if rudder reversal is accompanied by moving the ailerons with the spin (stick right in a right spin).Decreasing the wing incidence from 6deg to -2deg should have a beneficial effect on the recovery characteristics of the airplane. Recovery characteristics by normal use of controls (full rudder reversal followed by moving the elevators down) will be satisfactory if the wing incidence, of the airplane is -2deg. Installation of external fuel tanks (with or without fuel) will have a somewhat adverse effect on the recovery characteristics of the airplane, but if the recovery technique includes movement of the ailerons to full with the spin, the spin rotation will be terminated rapidly. Varying the position of the center of gravity within the limits indicated to be possible on the airplane should not affect the recovery characteristic

Book Free Spinning Tunnel Tests of a 1 24 Scale Model of the Mcdonnell Xp 88 Airplane with a Conventional Tail

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.

Book Concluding Report of Free Spinning Tumbling and Recovery Characteristics of a 1 18 Scale Model of the Ryan X 13 Airplane Coord No Af 199

Download or read book Concluding Report of Free Spinning Tumbling and Recovery Characteristics of a 1 18 Scale Model of the Ryan X 13 Airplane Coord No Af 199 written by James S. Bowman and published by BiblioGov. This book was released on 2013-07 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine its spin, recovery, and tumbling characteristics, and to determine the minimum altitude from which a belly landing could be made in case of power failure in hovering flight. Model spin tests were conducted with and without simulated engine rotation. Tests without simulated engine rotation indicated two types of spins: one, a slightly oscillatory flat spin; and the other, a violently oscillatory spin. Tests with simulated engine rotation indicated that spins to the left were fast rotating and steep and those to the right were slow rotating and flat. The optimum technique for recovery is reversal of the rudder to against the spin and simultaneous movement of the ailerons to full with the spin followed by movement of the elevators to neutral after the spin rotation ceases. Tumbling tests made on the model indicated that although the Ryan X-13 airplane will not tumble in the ordinary sense (end-over-end pitching motion), it may instead tend to enter a wild gyrating'motion. Tests made to simulate power failure in hovering flight by dropping the model indicated that the model entered what appeared to be a right spin. An attempt should be made to stop this motion immediately by moving the rudder to oppose the rotation (left pedal), moving the ailerons to with the spin (stick right), and moving the stick forward after the spin rotation ceases to obtain flying speed for pullout. The minimum altitude required for a belly landing in case of power failure in hovering flight was indicated to be about 4,200 feet.

Book Free spinning Tunnel Tests of a Model of a Canard Airplane

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.

Book Wind tunnel Investigation of a Revised Horizontal Tail Surface for the Grumman TBF 1 Airplane

Download or read book Wind tunnel Investigation of a Revised Horizontal Tail Surface for the Grumman TBF 1 Airplane written by John W. McKee and published by . This book was released on 1943 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the LMAL 7- by 10-foot tunnel of the aerodynamic characteristics of a revised 0.5-scale model of the Grumman TBF-1 left horizontal tail surface. The investigation was undertaken to determine if a horizontal tail surface with a large overhang would reduce the high stick forces in maneuvers that the airplane had with the original horn-balanced elevator, without appreciably affecting the longitudinal stability characteristics of the airplane.