Technical Report Archive & Image Library (TRAIL) - 470 Matching Results

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Effect of surface-active additives on physical properties of slurries of vapor-process magnesium

Description: The presence of 3 to 5 percent surface-active additive gave the lowest Brookfield apparent viscosity, plastic viscosity, and yield value that were obtained for slurry fuels containing approximately 50 percent vapor-process magnesium in JP-1 fuel. The slurries settled little and were easily remixed. A polyoxyethylene dodecyl alcohol was the most effective of 13 additives tested in reducing the Brookfield apparent viscosity and the yield value of the slurry. The seven most effective additives all… more
Date: November 3, 1955
Creator: Pinns, Murray L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Behavior of the Bell X-1A Research Airplane During Exploratory Flights at Mach Numbers Near 2.0 and at Extreme Altitudes

Description: Memorandum describing a flight program consisting of exploratory flights to determine the Mach number and altitude capabilities of the Bell X-1A research airplane. On two flights of X-1 airplane, one reaching a Mach number of about 2.44, the other a geometric altitude of about 90,000 feet, lateral stability difficulties were encountered which resulted in uncontrolled rolling motions of the airplane at Mach numbers near 2.0.
Date: September 1955
Creator: Drake, Hubert M. & Stillwell, Wendell H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance and Component Frontal Areas of a Hypothetical Two-Spool Turbojet Engine for Three Modes of Operation

Description: Engine performance is better for constant outer-spool mechanical-speed operation than for constant inner-spool mechanical-speed operation over most of the flight range considered. Combustor and afterburner frontal areas are about the same for the two modes. Engine performance for a mode characterized by a constant outer-spool equivalent speed over part of the flight range and a constant outer-spool mechanical speed over the rest of the flight range is better that that for constant outer-spool m… more
Date: December 19, 1955
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static Longitudinal and Lateral Stability and Control Characteristics of an Airplane Configuration Having a Wing of Trapezoidal Plan Form With Various Tail Airfoil Sections and Tail Arrangements at a Mach Number of 6.86

Description: Memorandum presenting an investigation carried out in the 11-inch hypersonic tunnel to determine the static longitudinal and lateral stability and control characteristics of an airplane configuration with a trapezoidal wing with a modified hexagonal airfoil section and equipped with various tail airfoil sections and tail arrangements. The tests were made at Mach number 6.86 and Reynolds number 343,000 based on the wing mean aerodynamic chord.
Date: August 15, 1955
Creator: Penland, Jim A.; Fetterman, David E., Jr. & Ridyard, Herbert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Determination of the Longitudinal Stability and Control Characteristics of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback

Description: Memorandum presenting the Bell X-5 research airplane tested at 58.7 degrees sweepback during the program to determine the characteristics of a variable-sweep fighter airplane at transonic speeds. This paper includes the stability and control characteristics in the stable lift range up to Mach numbers near 1.0 at an altitude of 40,000 feet and to slightly lower Mach numbers at altitudes of 25,000 feet and 15,000 feet. Results regarding general comments, static stability and control characteristi… more
Date: May 26, 1955
Creator: Finch, Thomas W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method for evaluating the loads and controllability aspects of the pitch-up problem

Description: Report presenting a procedure for estimating the range of peak airplane load factors and maneuvering tail loads likely to be experienced in pitch-up maneuvers. Results of computations indicated that though the load factors and maneuvering tail loads were not critical in pitch-up maneuvers at 35,000 feet, they were likely to exceed design levels at 15,200 feet.
Date: August 23, 1955
Creator: Sadoff, Melvin; Matteson, Frederick H. & Havill, C. Dewey
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Theoretical Investigation of a Compensating Network With Application to Roll Control Systems for Automatic Interceptors

Description: Memorandum presenting a theoretical analysis of an airplane automatic control system incorporating a compensating network. The compensating network is a computing network that has characteristics that are the inverse of the airframe; consequently, airplane dynamics are eliminated from the system response. Results regarding the displacement control system, the velocity command system, and the acceleration control system are provided.
Date: July 21, 1955
Creator: Sherman, Windsor L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation at a Mach number of 2.01 of the effects of body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies of a given length and volume but various cross-section shapes were tested at a Mach number of 2.01. The results showed that changes in drag at zero lift due to changes in body cross-section shape from the basic circular shape are small and of the same order a… more
Date: July 21, 1955
Creator: Carlson, Harry W. & Gapcynski, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of effects of airplane characteristics and autopilot parameters on a roll-command system with aileron rate and deflection limiting

Description: From Summary: "The dynamic characteristics of an airplane with a proportional-gain roll-control autopilot are discussed. A comparison of three different high-speed fighter airplanes is presented. The dynamic effects of time lags and various gains in the system are described."
Date: September 2, 1955
Creator: Schy, Albert A. & Gates, Ordway B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Drag Coefficients of Round Noses With Conical Windshields at Mach Number 2.72

Description: "An exploratory investigation at Mach number 2.72 has been made to show the decrease in the drag of a round-nose model achieved by mounting a small cone on a rod ahead of the nose. The geometric parameters which were varied were the cone-base diameter, cone angle, and rod length. All models showed large decreases in drag compared to that of the round nose alone" (p. 1).
Date: June 28, 1955
Creator: Jones, Jim J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Study of the Correlation Between Flight and Wind-Tunnel Buffeting Loads

Description: Report presenting a comparison of the buffet loads measured on wind-tunnel models with loads measured in flight, which indicate that a simple strain-gage measurement can be used in wind tunnel testing that can be used to predict the wing buffet loads on the airplane. The technique appears to be usable for both unswept and swept configurations.
Date: July 19, 1955
Creator: Huston, Wilber B.; Rainey, A. Gerald & Baker, Thomas F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static longitudinal and lateral stability and control characteristics of an 0.065-scale model of the Chance Vought Regulus II missile at Mach numbers of 1.41, 1.61, and 2.01: TED No. NACA AD 398

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal and lateral stability and control characteristics of an 0.065-scale model of the Chance Vought Regulus II missile. The tests were made at three Mach and Reynolds numbers.
Date: June 6, 1955
Creator: Robinson, Ross B.; Driver, Cornelius & Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Load distributions on wings and wing-body combinations at high angles of attack and supersonic speeds

Description: Report presenting an investigation of aircraft which are required to maneuver rapidly at extreme altitudes, which involves reaching maximum loads at high angles of attack. Load information is necessary for that flight condition and for aircraft that reach their maximum loads at high speed and high dynamic pressures. Results regarding the wings and wing-body combinations are provided.
Date: July 21, 1955
Creator: Katzen, Elliott D. & Pitts, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Recent Experimental Data on Three-Dimensional Oscillating Air Forces

Description: Report presenting the status of oscillating air forces, including forces, moments, and their respective phase angles for a 45 degree swept wing of aspect ratio 2 and for two bodies of revolution. Derivatives based on available analyses were also demonstrated for those three configurations.
Date: June 27, 1955
Creator: Leadbetter, Sumner A. & Clevenson, Sherman A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the effects of body indentation and of wing-plan-form modification on the longitudinal characteristics of a 60 degree swept-wing-body combination at Mach numbers of 1.41, 1.61, and 2.10

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of body indentation on the minimum drag and maximum lift-drag ratio of a 60 degree swept-wing-body combination. A secondary goal of the tests was to determine the effect on the maximum lift-drag ratio of modifying the inboard plan form of the 60 degree swept wing. Lift, drag, and pitching-moment data are presented.
Date: July 25, 1955
Creator: Sevier, John R., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical investigation of the effects of configuration changes on the center of pressure shift of a body-wing-tail combination due to angle of attack and Mach number at transonic and supersonic speeds

Description: Report presenting a theoretical investigation to study the effects of systematic changes in configuration of a representative airframe on the center-of-pressure travel due to changes in angle of attack and in Mach number. The airframe was an unbanked canard missile configuration with low-aspect-ratio coplanar wing and tail surfaces of triangular plan form. Results regarding the center-of-pressure shift due to angle of attack, center-of-pressure shift due to Mach number, and combined effects of … more
Date: September 2, 1955
Creator: Spahr, J. Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of leading-edge radius on the longitudinal stability of two 45 degree sweptback wings as influenced by Reynolds numbers up to 8.20 x 10(exp 6) and Mach numbers up to 0.303

Description: Report presenting an investigation to show the effects of systematic changes of leading-edge radius, aspect ratio, Reynolds number, and Mach number on the static longitudinal aerodynamic characteristics of sweptback wings in the 19-foot pressure tunnel. Results regarding the effects of leading-edge radius and aspect ratio and effect of Reynolds number and Mach number are provided.
Date: July 28, 1955
Creator: Foster, Gerald V. & Schneider, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of service-imposed maneuvers of four jet fighter airplanes in relation to their handling qualities and calculated dynamic characteristics

Description: Report presenting results from a flight program conducted to obtain information on the airplane response and actual rates and amounts of control motion used by service pilots to perform squadron operational training missions, which are correlated with the airplane handling qualities and calculated maximum dynamic response. Results regarding longitudinal characteristics, rolling characteristics, and sideslip characteristics are provided.
Date: August 15, 1955
Creator: Mayer, John P. & Hamer, Harold A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance characteristics of hemispherical target-type thrust reversers

Description: Report presenting an investigation to determine the reverse-thrust performance of hemispherical target-type thrust reversers over a wide range of geometric variables. Several factors were found that increased the flow turn angle and reverse-thrust ratio, primarily the hemisphere diameter. Results regarding operating characteristics, relation of flow turn angle and reverse-thrust ratio, reverse-flow velocities and pressures along boattail, effect of boattail shape on reverse-thrust ratio, and mo… more
Date: September 27, 1955
Creator: Steffen, Fred W.; McArdle, Jack G. & Coats, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Description: From Introduction: "The investigation reported herein was initiated to define further the effects on the aerodynamic characteristics and load distribution of a thin, sweptback wing of a low-pressure blowing system and also to provide information on which to base a more thorough study of a complete airplane configuration."
Date: September 20, 1955
Creator: Whittle, Edward F., Jr. & McLemore, H. Clyde
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary investigation at Mach number 1.9 of simulated wing-root inlets

Description: Report presenting an experimental investigation to study several wing-root inlet configurations at Mach number 1.9. The inlets were of triangular and rectangular shape and external compression was provided by two-dimensional wedge surfaces. Results regarding the pressure-recovery and mass-flow data, effect of inlet side plates and curved diffusers, exit and inlet total-pressure distributions, improvement of exit total-pressure profiles, and inlet tests at zero flight speed are provided.
Date: January 19, 1955
Creator: Piercy, Thomas G. & Weinstein, Maynard I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of string support interference on base pressure and forebody chord force at Mach numbers from 0.60 to 1.30

Description: Report presenting testing to determine the interference effects of various sting-support configurations on the base pressure and foredrag characteristics of a wing-fuselage combination with a turbulent boundary layer. The primary variable investigated was the length of the constant-diameter portion of a sting support. Results regarding the base-pressure interference and foredrag interference are provided.
Date: January 28, 1955
Creator: Tunnell, Phillips J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Steady-state and surge characteristics of a compressor equipped with variable inlet guide vanes operating in a turbojet engine

Description: Report presenting an investigation of a turbojet engine with variable inlet guide vanes in an altitude test facility to determine the steady-state compressor performance and surge characteristics. Compressor surge pressure ratios were found to be unaffected by changes in flight condition for either position of the inlet guide vanes. Decreasing the inlet Reynolds number was found to reduce the corrected fuel flow required for compressor surge.
Date: June 20, 1955
Creator: Wallner, Lewis E. & Lubick, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 2: Stage and Blade-Element Performance

Description: Memorandum presenting an investigation to determine the feasibility of increasing the specific weight flow of a transonic axial-flow compressor inlet stage by decreasing the hub-tip ratio. The current phase of the investigation was conducted to determine the blade-element and the overall performance of the complete stage. Results regarding the overall performance, blade-element performance, and stator-blade-element performance are provided.
Date: January 10, 1955
Creator: Montgomery, John C. & Glaser, Frederick W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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