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A Theoretical Investigation of the Dynamic Lateral Oscillatory Stability of an Airplane Having a 60 Degree Triangular Wing

Description: Report presenting a theoretical study of the dynamic lateral stability characteristics of an airplane with a 60 degree triangular wing. Calculations included the determination of the neutral-lateral-oscillatory-stability boundary, the period and time to damp to one-half amplitude of the lateral oscillation, and the time to damp to one-half amplitude for the spiral mode. The airplane was generally found to be stable for all conditions.
Date: March 8, 1950
Creator: Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

Measurement of the Static Stability and Control and the Damping Derivatives of a 0.13-Scale Model of the Convair XFY-1 Airplane, Ted No. NACA DE 368

Description: "An investigation has been conducted to determine the static stability and control and damping in roll and yaw of a 0.13-scale model of the Convair XFY-1 airplane with propellers off from 0 deg to 90 deg angle of attack. The tests showed that a slightly unstable pitch-up tendency occurred simultaneously with a break in the normal-force curve in the angle-of-attack range from about 27 deg to 36 deg. The top vertical tail contributed positive values of static directional stability and effective dihedral up to an angle of attack of about 35 deg. The bottom tail contributed positive values of static directional stability but negative values of effective dihedral throughout the angle-of-attack range" (p. 1).
Date: October 17, 1954
Creator: Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of Stability and Control Characteristics of a 1/10-Scale Model of a Canadian Tailless Glider in the Langley Free-Flight Tunnel

Description: "An investigation of the stability and control characteristics of a 1/10-scale model of a Canadian tailless glider has been conducted in the 10 Langley free-flight tunnel. The glider designated the N.R.L. tailless glider has a straight center section and outboard panels sweptback 43 deg. along the leading edge of the wing. The aspect ratio is 5.83 and the taper ratio is 0.323. From the results of the investigation and on the basis of comparison with higher-scale static tests of the National Research Council of Canada, it is expected that the longitudinal stability of the airplane will be satisfactory with flap up but unsatisfactory near the stall with flap down" (p. 1).
Date: March 29, 1949
Creator: Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

The Effect of Mass Distribution on the Low-Speed Dynamic Lateral Stability and Control Characteristics of a Model With a 60 Degree Triangular Wing

Description: Memorandum presenting an investigation to determine the effect of mass distribution on the dynamic lateral stability and control characteristics of a model with a 60 degree triangular wing in the free-flight tunnel. Flight tests and calculations were made for five different loading conditions. Results regarding the oscillatory stability, lateral control, and general flight behavior are provided.
Date: March 9, 1951
Creator: Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the static longitudinal stability and trim characteristics of a sweptback-wing jet-transport model equipped with an external-flow jet augmented flap

Description: Report presenting a wind-tunnel investigation to determine the static longitudinal stability and trim characteristics of a sweptback-wing jet-transport model equipped with an external-flow jet-augmented flap. Tests were also conducted to determine the effects of wing position, vertical position of the horizontal tail, and size of the horizontal tail.
Date: January 1958
Creator: Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

Damping in Yaw and Static Directional Stability of a Canard Airplane Model and of Several Models Having Fuselages of Relatively Flat Cross Section

Description: Report presenting an investigation to determine the damping in yaw and static directional stability characteristics for a flat-fuselage model with its major cross-sectional axis either horizontal or vertical, for a flat-fuselage model with its major axis horizontal in combination with a 45 degree sweptback wing, and for a canard model with a triangular control surface and 45 degree sweptback wing.
Date: October 16, 1950
Creator: Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speeds of flight characteristics of a sweptback-wing jet-transport airplane model equipped with an external-flow jet-augmented slotted flap

Description: Report presenting a wind-tunnel investigation at low speeds to determine the flight characteristics of a model of a sweptback-wing jet-transport airplane equipped with an external-flow jet-augmented slotted flap. Results regarding the longitudinal stability characteristics, longitudinal control characteristics, lateral stability characteristics, and lateral control characteristics are provided.
Date: July 1958
Creator: Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

Low-speed measurements of static stability, damping in yaw, and damping in roll of a delta, a swept, and an unswept wing for angles of attack from 0 degrees to 90 degrees

Description: Report presenting a low-speed investigation to determine the static and damping derivatives of a 60 degree delta wing, a 45 degree swept wing, and an unswept wing from 0 to 90 degrees angle of attack. Results regarding the static longitudinal stability characteristics, static lateral stability characteristics, damping characteristics.
Date: April 13, 1956
Creator: Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Description: Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowable center-of-gravity travel are provided.
Date: January 21, 1953
Creator: Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

Free-flight-tunnel investigation of the low-speed stability and control characteristics of a model having a fuselage of relatively flat cross section

Description: Report presenting an experimental investigation in the free-flight tunnel to determine the low-speed stability and control characteristics of a model with a fuselage of relatively flat cross section. The model was found to exhibit an erratic behavior in pitch and yaw, which appeared to be due to random trim changes associated with the flow from the forward portion of the flat fuselage. Results regarding the longitudinal stability and control characteristics and lateral stability and control characteristics are provided.
Date: February 24, 1953
Creator: Paulson, John W. & Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

Experimental determination of the damping in roll and aileron rolling effectiveness of three wings having 2 degree, 42 degree and 62 degree sweepback

Description: Report presenting tests to determine the damping in roll and aileron rolling effectiveness of three wings with different degrees of sweepback. The results showed that the values of damping in roll decreased with increasing sweepback. The rolling effectiveness of the aileron of the sweptback wing was found to be predicted with fair accuracy from static aileron-rolling-moment tests and wing-damping tests.
Date: May 1947
Creator: Bennett, Charles V. & Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

A Theoretical Investigation of the Effect of Yawing Moment Due to Rolling on Lateral Oscillatory Stability

Description: Note presenting the effect on lateral oscillatory stability of varying the value of the stability derivative over a wide range of negative and positive values as determined theoretically for a sweptback fighter airplane with loading conditions simulating an airplane with and without wing-tip fuel tanks.
Date: October 1948
Creator: Johnson, Joseph L. & Sternfield, Leonard
Partner: UNT Libraries Government Documents Department

Free-flight-tunnel investigation of the low-speed stability and control characteristics of a canard airplane model

Description: From Summary: "Since canard configurations have been found to possess unusual static stability characteristics, an investigation has been conducted in the Langley free-flight tunnel to determine the dynamic stability and control characteristics of a model of this type. The characteristics of the model were unsatisfactory in the higher lift-coefficient range because of lightly damped lateral oscillations and because of erratic behavior in pitch and yaw which was apparently caused by random trim changes associated with the irregular fluctuations in the vortex flow from the horizontal tail."
Date: October 29, 1953
Creator: Johnson, Joseph L., Jr. & Paulson, John W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of an external-flow jet-augmented slotted flap suitable for application to airplanes with pod-mounted jet engines

Description: Report presenting a wind-tunnel investigation to determine the characteristics of an external-flow jet-augmented slotted flap which appears suitable for applications to pod-mounted jet engines. The investigation included tests of an unswept wing and of a model of a swept-wing jet transport or bomber. Results regarding the unswept wings, swept wings, longitudinal stability and trim, and estimated take-off and landing performance are provided.
Date: December 1956
Creator: Campbell, John P. & Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the Convair YF-102 Airplane in the Langley Free-Flight Tunnel

Description: From Summary: "An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the Convair YF-102 airplane has been made in the Langley free-flight tunnel. The model was flown over a lift-coefficient range from 0.5 to the stall in its basic configuration and with several modifications involving leading-edge slats and increases in vertical-tail size. Only relatively low-altitude conditions were simulated and no attempt was made to determine the effect of freeing the controls."
Date: November 18, 1953
Creator: Johnson, Joseph L., Jr. & Boisseau, Peter C.
Partner: UNT Libraries Government Documents Department

Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the Douglas XF4D-1 Airplane in the Langley Free-Flight Tunnel TED No. NACA DE 349

Description: An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the Douglas XF4D-1 airplane has been made in the Langley free-flight tunnel. The model was flown with leading-edge slats retracted and extended over a lift-coefficient range from 0.5 to the stall. Only relatively low-altitude conditions were simulated and no attempt was made to determine the effect on the stability characteristics of freeing the controls. The longitudinal stability and control characteristics of the model were satisfactory for all conditions investigated except near the stall with slats extended, where the model had a slight nosing-up tendency. The lateral stability and control characteristics of the model were considered satisfactory for all conditions investigated except near the stall with slats retracted, where a change in sign of the static- directional-stability parameter Cn(sub beta) caused the model to be directionally divergent. The addition of an extension to the top of the vertical tail did not increase Cn(sub beta) enough to eliminate the directional divergence of the model, but a large increase in Cn(sub beta) that was obtainable by artificial means appeared to eliminate the divergence and flights near the stall could be made. Artificially increasing the stability derivative-Cn(sub r) (yawing moment due to yawing) and Cn(sub p) (yawing moment due to rolling) had little effect on the divergence for the range of these parameters investigated. Calculations indicate that the damping of the lateral oscillation of the airplane with slats retracted or extended will be satisfactory at sea level but will be only marginally satisfactory at 40,000 feet.
Date: 1951
Creator: Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XP-85 Airplane While Attached to the Trapeze

Description: "At the request of the Air Materiel Command, Army Air Forces, an investigation of the low-speed, power-off, stability and control characteristics of the McDonnell XP-85 airplane has been conducted in the Langley free-flight tunnel. The results of the portion of the investigation consisting of tests of a 1/10-scale model to study the stability of the XP-85 when attached to the trapeze and during retraction into the B-36 bomb bay are presented herein. In the power-off condition the stability was satisfactory with all oscillations well damped and the nose-restraining collar could be placed in position without difficulty" (p. 1).
Date: November 17, 1947
Creator: Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

Stability and Control Force Tests of Four- and Six-Unit Wing Designs of Low Aspect Ratio and 20 Degree Triangular Plan Form

Description: Report presenting an investigation to obtain force-test data on a wing design suitable for high-speed guided missiles, especially data on rolling moments produced in yawed and pitched attitudes. Force tests were conducted on two models of a wing design of low aspect ratio and 20 degree triangular plan form. Results regarding the application of results, four-unit wing design, and six-unit wing design are provided.
Date: May 1946
Creator: Paulson, John W.; Varney, Elizabeth P. & Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

Preliminary Evaluation of the Low-Speed Stability and Control Characteristics of the McDonnell XP-85 Airplane from Tests of an Unballasted 1/5-Scale Model in the Langley Free-Flight Tunnel

Description: "At the request of the Air Material Command, Army Air Forces an investigation of the low-speed, power-off stability and control characteristics of the McDonnell XP-85 airplane is being conducted in the Langley free-flight tunnel. The XP-85 airplane is a jet propelled, parasite fighter with a 34 deg sweepback at the wing quarter chord. It was designed to be carried in a bomb bay of the B-36 air plane. The first portion of the investigation consists of a preliminary evaluation of the stability and control characteristics of the airplane from force and fight tests of an unballasted 1/5-scale model. The second portion of the investigation consists of test of a properly balasted 1/10-scale model which will include a study of the stability of the XP-85 when attached to the trapeze for retraction into the B-36 bomb bay" (p. 1).
Date: March 19, 1947
Creator: Paulson, John W. & Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department

Low-speed study of the effects of frequency on the stability derivatives of wings oscillating in yaw with particular reference to high angle of attack conditions

Description: Report presenting a low-speed investigation in the free-flight tunnel to provide basic information regarding the effect of frequency on wings oscillating in yaw. The investigation consisted of both free-oscillation tests and forced-oscillation tests of a 60 delta wing, a 45 degree sweptback wing of aspect ratio 2.61, and an unswept wing of aspect ratio 3 over a range of angles of attack. Results regarding the static force test results, directional stability, cross derivative, effective dihedral, and flow separation are provided.
Date: November 1, 1955
Creator: Campbell, John P.; Johnson, Joseph L., Jr. & Hewes, Donald E.
Partner: UNT Libraries Government Documents Department

Force Tests of a 1/5-Scale Model of the McDonnell XP-85 Airplane with Conventional Tail Assembly in the Langley Free-Flight Tunnel

Description: At the request of the Air Materiel Command, Army Air Forces an investigation of the low-speed, power-off stability and control characteristics of the McDonnell XP-85 airplane is being conducted in the Langley free-flight tunnel. The XP-85 airplane is a parasite fighter carried in a bomb bay of the B-36 airplane. As a part of the investigation a few force tests were made of a 1/5 scale model of the XP-85 with a conventional tail assembly installed in place of the original design five-unit tail assembly. The total area of the conventional assembly was approximately 80 percent of the area of the five-unit assembly. The results of this investigation showed that the conventional tail assembly gave about the same longitudinal stability characteristics as the original configuration and improved the directional and lateral stability.
Date: March 19, 1947
Creator: Paulson, John W. & Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department