Some Low Speed Wind Tunnel Experiments Pertaining To The Longitudinal Stability Characteristics Of A 35c Swept Wing Model And An Unswept Wing Model PDF Download
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Author | : Arthur Henderson |
Publisher | : |
Total Pages | : 94 |
Release | : 1956 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download Wind-tunnel Investigation of the Static Longitudinal and Lateral Stability of a 1/62-scale Model of the X-1E at Supersonic Speeds Book in PDF, ePub and Kindle
An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the X-1E has been conducted in the Langley 9-inch supersonic tunnel. Tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete model configurations. Detailed analysis of the test results has not been made.
Author | : Rodger L. Naeseth |
Publisher | : |
Total Pages | : 88 |
Release | : 1963 |
Genre | : Aerodynamics |
ISBN | : |
Download Low-speed Investigation of the Effects of Wing Sweep on the Aerodynamic Characteristics of Parawings Having Equal-length Leading Edges and Keel Book in PDF, ePub and Kindle
An investigation has been made in the Langley 300-MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a related series of parawings in which wing sweep was the primary variable. The leading-edge sweep angles varied from 400 to 750 and the three basic parawings had flat-planform sweep angles of 350, 450, and 550. The canopies of the wings were made of fabric. Tests were made at an airspeed of 38.6 mph and a Reynolds number of approximately 1.5 X 106. The maximum angle-of-attack range was from 140 to 530 for the wings having a canopy of 350 flat-planform sweep. A limited investigation of lateral characteristics was made for sideslip angles from approximately -50 to 160 for two angles of attack, and lateral stability derivatives were obtained for some configurations through a angle-of-attack range. Forces and moments acting on the wing and apex hinge moments were measured.
Author | : Paul G. Fournier |
Publisher | : |
Total Pages | : 42 |
Release | : 1958 |
Genre | : Stability of airplanes, Longitudinal |
ISBN | : |
Download Wind-tunnel Investigation of the High-subsonic Static Longitudinal Stability Characteristics of Several Wing-body Configurations Designed for High Lift-drag Ratios at a Mach Number of 1.4 Book in PDF, ePub and Kindle
Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at a Mach number of 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65A-series airfoil sections. Other configurations included bodies modified by two types of indentation and two other wings, one wing without camber but with 4 degrees linear twist (washout) and a second wing with both camber and twist.
Author | : Paul T. Soderman |
Publisher | : |
Total Pages | : 108 |
Release | : 1971 |
Genre | : Airplanes |
ISBN | : |
Download Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail Book in PDF, ePub and Kindle
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.
Author | : Arthur R. Wallace |
Publisher | : |
Total Pages | : 29 |
Release | : 1947 |
Genre | : Airplanes |
ISBN | : |
Download Wind-tunnel Investigation of the Effect of Power and Flaps on the Static Longitudinal Stability Characteristics of a Single-engine Low-wing Airplane Model Book in PDF, ePub and Kindle
As part of a comprehensive investigation of the effect of power, flaps, and wing position on static stability, tests were made in the Langley 7- by 10-foot tunnel to determine the longitudinal stability of characteristics with and without power of a typical low-wing, single-engine airplane model with flaps neutral, with a full-span single slotted flap, and with a full-span double slotted flap. The horizontal tail incorporated a leading-edge slot for the flap-deflected conditions and was placed high to avoid the slipstream. Some data are presented for the isolated horizontal tail. With the double slotted flap deflected some air-flow surveys were made in the region of the tail and the wing stall was studied by means of tufts.
Author | : Isidore G. Recant |
Publisher | : |
Total Pages | : 36 |
Release | : 1942 |
Genre | : Airplanes |
ISBN | : |
Download Wind Tunnel Investigation of Effect of Yaw on Lateral-stability Characteristics Book in PDF, ePub and Kindle
Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.
Author | : |
Publisher | : |
Total Pages | : 26 |
Release | : 1987 |
Genre | : |
ISBN | : |
Download Low-speed Wind Tunnel Study of Longitudinal Stability and Usable-lift Improvement of a Cranked Wing Book in PDF, ePub and Kindle
Author | : James A. Weilberg |
Publisher | : |
Total Pages | : 64 |
Release | : 1952 |
Genre | : |
ISBN | : |
Download Wind Tunnel Investigation at Low Speed of a Twisted and Cambered Wing Swept Back 63 Degrees with Vortex Generators and Fences Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 52 |
Release | : 1960 |
Genre | : |
ISBN | : |
Download Low-speed Wind Tunnel Investigation of the Aerodynamic Characteristics of an Airplane Having a Cambered Arrow Wing with a 75 Deg Swept Leading Edge Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 94 |
Release | : 1974 |
Genre | : |
ISBN | : |
Download Low Speed Wind Tunnel Tests of a 1/9-scale Model of a Variable-sweep Advanced Supersonic Transport Book in PDF, ePub and Kindle