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Experimental investigation of the effect of vertical-tail size and length of fuselage shape and length on the static lateral stability characteristics of a model with 45 degree sweptback wing and tail surfaces

Description: Report presenting an investigation to determine the effects of vertical-tail size and length and of fuselage shape and length on the lateral static stability characteristics of a model with a wing and vertical tails with the quarter-chord line swept back 45 degrees. Results indicated that the directional instability of the fuselage was about two-thirds as large as that predicted by classical theory. Results regarding wing characteristics, fuselage characteristics, vertical-tail effectiveness, and interference effects are provided.
Date: August 1950
Creator: Queijo, M. J. & Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the effect of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with 45 degree sweptback wing and tail surfaces

Description: An investigation was made to determine the effects of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with wing and vertical tails having the quarter-chord lines swept back 45 degrees. The results indicate that the directional instability of the various isolated fuselages was about two-thirds as large as that predicted by classical theory.
Date: June 5, 1950
Creator: Queijo, M. J. & Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department

Some effects of amplitude and frequency on the aerodynamic damping of a model oscillating continuously in yaw

Description: Report presenting a fuselage-vertical-tail combination continuously oscillated in yaw through a range of reduced frequencies and amplitudes corresponding to the amplitudes of the sustained lateral oscillation of certain airplanes. An indication of a reduction in damping in yaw appeared as the amplitude of oscillation was reduced through the range of small amplitudes investigated. Results regarding the phase angle, probable error of phase angle, damping in yaw, and probable error in the damping in yaw are provided.
Date: September 1952
Creator: Fisher, Lewis R. & Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the low-speed longitudinal and lateral control characteristics of a triangular-wing model of aspect ratio 2.31 having constant-chord control surfaces

Description: Report presenting a wind-tunnel investigation to determine the low-speed longitudinal and lateral control characteristics of a model with a triangular wing with NACA 65(06)-006.5 airfoil sections, aspect ratio 2.31, and constant-chord control surfaces. The values of the hinge-moment parameters were found to be of somewhat greater magnitude than would be expected on unswept wings with the same aspect ratio.
Date: September 6, 1950
Creator: Wolhart, Walter D. & Michael, William H., Jr.
Partner: UNT Libraries Government Documents Department

Static longitudinal and lateral stability characteristics at low speed of unswept-midwing models having wings with an aspect ratio of 2, 4, or 6

Description: Report presenting an investigation to determine the effects of the various components and combinations of components on the static longitudinal and lateral stability characteristics of unswept-midwing models having wings with a variety of aspect ratios for a range of angles of attack. Results regarding static longitudinal stability characteristics and static lateral stability characteristics are provided.
Date: May 1956
Creator: Wolhart, Walter D. & Thomas, David F., Jr.
Partner: UNT Libraries Government Documents Department

Static longitudinal and lateral stability characteristics at low speed of 45 degree sweptback-midwing models having wings with an aspect ratio of 2, 4, or 6

Description: Results are presented of tests conducted in the Langley stability tunnel to determine the effects of various components and combinations of components on the static longitudinal and lateral stability characteristics at low speed of a series of 45 degree sweptback-midwing-airplane configurations having wings with an aspect ratio of 2, 4, or 6. The tests were made at a dynamic pressure of 24.9 pounds per square foot which corresponds to a Mach number of 0.13 and Reynolds numbers of 1.00 x 10(exp 6), 0.71 x 10 (exp 6), and 0.58 x 10 (exp 6) based on the respective wing mean aerodynamic chords. The angle-of-attack range covered was from -4 degrees to 32 degrees and the sideslip angles used for the lateral-derivative tests were 5 degrees and -5 degrees. An increasing loss in tail contribution to directional stability both with increasing wing aspect ratio and increasing angle of attack was found to be a principal cause of all the complete models becoming directionally unstable in the high angle-of-attack range.
Date: September 1957
Creator: Thomas, David F., Jr. & Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of the rolling stability derivatives of a 1/10-scale model of the Douglas A4D-1 airplane

Description: Report discussing an experimental investigation of the low-speed rolling stability derivatives of a model of the Douglas A4D-1. The model was tested under a variety of conditions, including in clean and landing configurations and with the horizontal and vertical tails on and off, and the study also explored the effects of slats and flaps on the derivatives of the wing. No analysis of the data is provided.
Date: October 7, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane

Description: Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.
Date: August 25, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

Effect of sweepback on the low-speed static and rolling stability derivatives of thin tapered wings of aspect ratio 4

Description: Report discussing an investigation to determine the effect of sweepback on the static and rolling stability derivatives of a series of wings with a taper ratio of 0.6 and an aspect ratio of 4. The influence on the straight-flow characteristics, rolling-flow characteristics, and aileron characteristics are provided.
Date: August 9, 1949
Creator: Letko, William & Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Yawing, Pitching, and Static Stability Characteristics of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

Description: From Summary: "An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution."
Date: April 13, 1955
Creator: Wolhart, Walter D. & Thomas, David F., Jr.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

Description: From Summary: "An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution."
Date: May 2, 1955
Creator: Wolhart, Walter D. & Thomas, David F., Jr.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of the effects of chordwise wing fences and horizontal-tail position on the static longitudinal stability characteristics of an airplane model with a 35 degree sweptback wing

Description: From Summary: "Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal tail located well above the extended wing-chord plane indicated static longitudinal instability at moderate angles of attack for all configurations tested. An investigation therefore was made to determine whether the longitudinal stability could be improved by the use of chordwise wing fences, by lowering the horizontal tail, or by a combination of both."
Date: November 24, 1954
Creator: Queijo, M. J.; Jaquet, Byron M. & Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of the yawing stability derivatives of a 1/10-scale model of the Douglas A4D-1 airplane: TED No. NACA DE 389

Description: Report presenting an experimental investigation to determine the low-speed yawing stability derivatives of a model of the Douglas A4D-1 airplane. The model was tested in clean and landing configurations with horizontal and vertical tails on and off. Results are provided without analysis.
Date: September 13, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of the rolling stability derivatives of a 1/10-scale model of the Douglas A4D-1 airplane: TED No. NACA DE 389

Description: Report presenting an experimental investigation to determine the low-speed rolling stability derivatives of a scale model of the Douglas A4D-1. The model was tested in clean and landing configurations with horizontal and vertical tails on and off. The data is presented without analysis.
Date: October 7, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Pitching 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 pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.
Date: July 23, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

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 about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.
Date: May 20, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department