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Effects of wing elasticity on the aerodynamic characteristics of an airplane configuration having 45 degrees sweptback wings as obtained from free-flight rocket-model tests at transonic speeds

Description: Flight testing at transonic speeds occurred on two rocket-propelled models of an airplane configuration with 45 degree sweptback wings of aspect ratio 4 and with different stiffnesses. Longitudinal stability, lift, and drag characteristics were determined by analysis of the response of the models to disturbances in pitch. Results regarding lift, model vibrations, aeroelastic effects on lift, static stability, damping in pitch, and drag are provided.
Date: January 28, 1953
Creator: Vitale, A. James
Partner: UNT Libraries Government Documents Department

Characteristics of loads in rough air at transonic speeds of rocket-powered models of a canard and a conventional-tail configuration

Description: Report presenting results from flight tests at transonic speeds for a canard and a conventional-tail rocket-powered model in continuous rough air. The use of an airspeed-fluctuation instrument for measuring the turbulence intensity experienced is described as well as the resulting improvement in the technique of testing rocket models in rough air. The short-period frequency was dominant in the center-of-gravity normal-acceleration response for both models.
Date: March 1, 1955
Creator: Vitale, A. James
Partner: UNT Libraries Government Documents Department

Longitudinal stability characteristics at transonic speeds of a canard configuration having a 45 degree sweptback wing of aspect ratio 6.0 and NACA 65A009 airfoil section

Description: Report presenting an investigation to determine the longitudinal stability, lift, and drag characteristics of a rocket-powered model of a canard configuration with a 45 degree sweptback wing of aspect ratio 6.0, taper ratio of 0.6, and NACA 65A009 airfoil section. The variations with Mach number of lift, drag, and longitudinal stability were compared with a tailless and a conventional model with the same wing.
Date: November 15, 1954
Creator: Vitale, A. James & McFall, John C., Jr.
Partner: UNT Libraries Government Documents Department

Free-flight investigation of the control effectiveness of a differentially deflected horizontal tail at Mach numbers from 0.8 to 1.6

Description: Report presenting a free-flight investigation of the control effectiveness of a differentially deflected horizontal tail. The results were compared with and found to be in general agreement with estimates derived from other free-flight tests, wind tunnel tests, and theory. Results regarding the rolling moment, yawing moment, and overall rolling effectiveness are provided.
Date: April 26, 1956
Creator: Mitchell, Jesse L. & Vitale, A. James
Partner: UNT Libraries Government Documents Department

Wing-on and wing-off longitudinal characteristics of an airplane configuration having an thin unswept tapered wing of aspect ratio 3, as obtained from rocket-propelled models at Mach numbers from 0.8 to 1.4

Description: Report presenting flight tests at Mach numbers from 0.8 to 1.4 on three rocket-propelled general research models of airplane configurations. Two models had thin unswept tapered wings of aspect ratio 3 and hexagonal airfoil sections, two wings had different structural stiffness characteristics, and the third model had no wing. Results regarding the static and dynamic longitudinal stability, control, trim, and drag characteristics are provided.
Date: March 14, 1951
Creator: Gillis, Clarence L. & Vitale, A. James
Partner: UNT Libraries Government Documents Department

Experimental results from a test in rough air at high subsonic speeds of a tailless rocket model having cruciform triangular wings, and a note on the calculation of mean square loads of aircraft in continuous rough air

Description: Report presenting results of testing of a rocket model with cruciform 60 degree triangular wings in continuous rough air at transonic speeds. The wing arrangement tested appears to be useful for improving the accuracy of the results. Results regarding the characteristics of the rough-air response, variation of acceleration with Mach number, and evaluation of the cruciform arrangement are provided.
Date: April 13, 1956
Creator: Vitale, A. James & Mitchell, Jesse L.
Partner: UNT Libraries Government Documents Department

Lateral stability investigation at Mach numbers from 0.8 to 1.7 of two rocket-boosted models of an airplane configuration with a 45 degree swept wing and a low horizontal tail

Description: From Summary: "Rocket-boosted free-flight tests of two models of an airplane configuration having a 45 degree swept wing and a low horizontal-tail position have provided lateral stability derivatives and control effectiveness data for a Mach number range from 0.8 to 1.7. The experimental lateral stability derivatives presented are corrected to rigid conditions and compared with theoretically calculated rigid derivatives. The results are presented without detailed analysis."
Date: September 30, 1957
Creator: McFall, John C., Jr.; Mitchell, Jesse L. & Vitale, A. James
Partner: UNT Libraries Government Documents Department

Longitudinal stability and drag characteristics at Mach numbers from 0.75 to 1.5 of an airplane configuration having a 60 degree swept wing of aspect ratio 2.24 as obtained from rocket-propelled models

Description: Report discussing testing of a rocket-propelled airplane configuration model and a drag model, each with a 60 degree swept wing of aspect ratio 2.24, and different fuselages, at a Mach number range of 0.75 to 1.50. Information about the longitudinal stability, control, and drag characteristics and minimum-drag characteristics is presented.
Date: April 11, 1952
Creator: Vitale, A. James; McFall, John C., Jr. & Morrow, John D.
Partner: UNT Libraries Government Documents Department

An investigation of the use of rocket-powered models for gust-load studies with an application to a tailless swept-wing model at transonic speeds

Description: Report presenting the results obtained in an investigation of the use of rocket-powered models for gust-load studies. A technique for testing in continuous rough air which incorporated the use of a survey airplane evolved.
Date: June 1954
Creator: Vitale, A. James; Press, H. & Shufflebarger, C. C.
Partner: UNT Libraries Government Documents Department