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A wind-tunnel test technique for measuring the dynamic rotary stability derivatives at subsonic and supersonic speeds

Description: "A method is described for measuring the dynamic stability derivatives of a model airplane in a wind tunnel. The characteristic features of this system are that single-degree-of-freedom oscillations were used to obtain combinations of rolling, yawing and pitching motions; that the oscillations were excited and controlled by velocity feedback which permitted operation under conditions unfavorable for more conventional types of oscillatory testing; and that data processing was greatly simplified … more
Date: September 20, 1954
Creator: Beam, Benjamin H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Free-Flight Technique for Measuring Damping in Roll by Use of Rocket-Powered Models and Some Initial Results for Rectangular Wings

Description: Report presenting a simplified method for obtaining free-flight measurements of damping in roll through the use of rocket-powered models. Initial configurations have been tested for a range of Mach numbers. Results regarding the rolling velocity with two different airfoil sections and damping-in-roll coefficient are provided.
Date: December 20, 1949
Creator: Edmondson, James L. & Sanders, E. Claude, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal-Stability Investigation of High-Lift and Stall-Control Devices on a 52 Degree Sweptback Wing With and Without Fuselage and Horizontal Tail at a Reynolds Number of 6.8 X 10 (Exp 6)

Description: Contains low-speed longitudinal stability characteristics of a 52 degree sweptback wing of aspect ratio 2.88, taper ratio 0.625, and NACA 64 (sub 1)-112 airfoil sections normal to the 0.282-chord line, in combination with split flaps, leading-edge flaps, and upper-surface fences. Low-wing and midwing-fuselage aerodynamic characteristics are presented with and without a horizontal tail at various vertical locations. Tests were conducted at a Reynolds number of 6.8 x 10(exp 6).
Date: December 20, 1948
Creator: Foster, Gerald V. & Fitzpatrick, James E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability, Control Effectiveness, and Drag Characteristics at Transonic Speeds of a Rocket-Propelled Model of an Airplane Configuration Having an Unswept Tapered Wing of Aspect Ratio 3.0 and NACA 65A004.5 Airfoil Sections

Description: Report presenting an investigation of an airplane configuration with an unswept tapered wing of aspect ratio 3.0 with NACA 65A004.5 airfoil sections. Static and dynamic longitudinal stability, control effectiveness, and drag characteristics are included. The results of this investigation are compared to similar models with wings of the same plan-form dimensions but with hexagonal airfoil sections.
Date: January 20, 1953
Creator: McFall, John C., Jr. & Hollinger, James A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Determination of the Static Longitudinal Stability Boundaries of the Bell X-5 Research Airplane with 59 Degrees Sweepback

Description: "During the flight program on the Bell X-5 airplane with 59 degrees sweepback to determine the practical Mach number and normal-force coefficient limits of this configuration, a reduction in static longitudinal stability was encountered in maneuvering flight. A determination of the boundary for reduction of longitudinal stability extending to a Mach number of 0.98 is presented in this paper. A reduction of static longitudinal stability existed for all elevator and all stabilizer-executed maneuv… more
Date: February 20, 1953
Creator: Finch, Thomas W. & Walker, Joseph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of mass distribution on the lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel

Description: The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing moments of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the m… more
Date: July 20, 1943
Creator: Campbell, John P. & Seacord, Charles L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects on dynamic lateral stability and control of large artificial variations in the rotary stability derivatives

Description: This report presents the results of an investigation conducted in the Langley free-flight tunnel to determine the effects of large artificial variations of several rotary lateral-stability derivatives on the dynamic lateral stability and control characteristics of a 45 degree sweptback-wing airplane model. Calculations of the period and damping of the lateral motions and of the response to roll and yaw disturbances were made for correlation with the experimental results. The calculated results … more
Date: June 20, 1952
Creator: Schade, Robert O. & Hassell, James L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of spanwise location of sweep discontinuity on the low-speed longitudinal stability characteristics of a complete model with wings of M and W plan form

Description: Report presenting an investigation of the low-speed static longitudinal stability characteristics of a complete model with a series of M- or W-wings. They were obtained through modification of a basic 45 degree swept wing and had several spanwise locations of sweep discontinuity. Results regarding pitching-moment characteristics, drag due to lift, aerodynamic parameters at zero lift, and possible configurations of airplanes with M- and W-wings are provided.
Date: January 20, 1955
Creator: Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal and Lateral Stability, Control Characteristics, and Vertical-Tail-Load Measurements for 0.03-Scale Model of the Avro CF-105 Airplane at Mach Number 1.41

Description: "An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.41 to determine the aerodynamic characteristics of an 0.03-scale model of the Avro CF-105 airplane. The investigation included the determination of the static longitudinal and lateral stability, the control and the hinge-moment characteristics of the elevator, the aileron, and the rudder, as well as the vertical-tail-load characteristics. The results indicated a minimum drag coefficient … more
Date: August 20, 1956
Creator: Spearman, M. Leroy; Robinson, Ross B. & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight transonic model investigation of jet effects on a fighter-type configuration employing a tail boom and three horizontal-tail positions

Description: Report presenting the results of a limited research program initiated to study the effects of a hot propulsive jet on the longitudinal stability characteristics of a fighter-type airplane configuration. The data was obtained from a rocket-boosted free-flight model investigation over a range of Mach numbers using four models that differed only in the position and size of the horizontal tail. Results regarding the time histories, trim, normal force, pitching moment, aerodynamic-center location, d… more
Date: February 20, 1958
Creator: Jackson, Bruce G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Trim and Tumble Characteristics of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane, TED NO. NACA DE311

Description: Based on results of longitudinal trim and tumble tests of a 0.057-scale model of the Chance Vought XF7U-1 airplane, the following conclusions regarding the trim and tumble characteristics of the airplane have been drawn: 1. The airplane will not trim at any unusual or uncontrolled angles of attack. 2. The airplane will not tumble with the center of gravity located forward of 24 percent of the mean aerodynamic chord. When the center of gravity is located at 24 percent of the mean aerodynamic cho… more
Date: July 20, 1948
Creator: Bryant, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the rolling stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model. Most of the tests were made through an angle-of-attack range from … more
Date: May 20, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Wind-Tunnel Investigation of the Effect of Horizontal Tail on Longitudinal Stability of Two 60 Degree Sweptback-Wing-Body Configurations with Aspect Ratios of 2.67 and 4.00

Description: Memorandum presenting an investigation of the effect of a 60 degree sweptback horizontal tail at two vertical locations on the static longitudinal stability of two 60 degree sweptback wing-body configurations with aspect ratios of 2.67 and 4.00 in the 8-foot transonic pressure tunnel. Tests were made at Mach numbers from 0.80 to 1.18 for angles of attack from -3 degrees to about 15 degrees.
Date: February 20, 1958
Creator: Brooks, Joseph D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of lateral controls in producing motion of an airplane as computed from wind-tunnel data

Description: This report presents the results of an analytical study of the lateral controllability of an airplane in which both the static rolling and yawing moments supplied by the controls and the reactions due to the inherent stability of the airplane have been taken into account. The investigation was undertaken partly for the purpose of coordinating the results of a long series of wind-tunnel investigations with phenomena observed in flight tests; for this reason a hypothetical average airplane, embod… more
Date: April 20, 1936
Creator: Weick, Fred E. & Jones, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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