National Advisory Committee for Aeronautics (NACA) - 371 Matching Results

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Transonic Wind-Tunnel Tests of the Launch, Jettison, and Longitudinal Characteristics of an Airplane and Missile Model Combination

Description: Report presenting tests of an airplane model equipped with missiles to investigate the capability of that combination to achieve satisfactory launching and jettisoning of the missiles. Information about pylon modifications, missiles in launch positions, missile trajectory, and missiles in jettison positions is provided.
Date: November 20, 1957
Creator: Cleary, Joseph W.; Frank, Joseph L. & Dewey, C. Forbes, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of turbojet and ram-jet engine cycles using various fuels

Description: From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."
Date: November 27, 1956
Creator: Wilcox, E. Clinton; Weber, Richard J. & Tower, Leonard K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Thrust and Pumping Characteristics of a Series of Ejector-type Exhaust Nozzles at Subsonic and Supersonic Flight Speeds

Description: Report presenting an investigation in the supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Results indicated that the free-stream Mach number had no effect on those characteristics of the ejectors in the range for which the secondary flow was choked.
Date: November 17, 1954
Creator: Hearth, Donald P. & Valerino, Alfred S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing Pressure Distributions Over the Lift Range of the Convair XF-92A Delta-Wing Airplane at Subsonic and Transonic Speeds

Description: Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distribution, and elevon-section loads are provided.
Date: November 30, 1955
Creator: Keener, Earl R. & Jordan, Gareth H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability and Control Characteristics at Low Speed of a Modified 1/10-Scale Model of the MX-1554A Design

Description: Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stabilit… more
Date: November 9, 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53

Description: Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coe… more
Date: November 30, 1956
Creator: Turner, Kenneth L. & Fournier, Roger H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane

Description: Report presenting an investigation of the low-speed stability and control characteristics of a 1/15-scale free-flying model of the Convair XB-58 airplane. Results regarding the longitudinal stability and control and a pod-drop investigation are provided.
Date: November 14, 1957
Creator: Paulson, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of Pressure Drop with No Heat Addition on Mockup Segments of the General Electric Air-Cooled Aircraft Reactor

Description: "An investigation was conducted at the NACA Lewis laboratory to obtain pressure-drop data for flow of air with no heat addition through mockups of two reactor segments of the proposed General Electric Company aircraft reactor. Pressure-drop data were obtained over a range of Reynolds numbers from 4000 to 80,000, air inlet Mach numbers from 0.02 to 0.40, inlet pressures up to about 40 inches of mercury absolute, and ambient air temperatures. factors, corrected for entrance, vena contracta, momen… more
Date: November 7, 1952
Creator: Sams, Eldon W. & Nagey, Tibor F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Free-Stream Reynolds Number, Engine Installation, and Model Scale on Stability Characteristics of a Translating-Spike Inlet at Mach 2.0

Description: Memorandum presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data were taken at a free-stream Mach number of 2.0 and angles of attack from 0 to 6 degrees. Results regarding free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.
Date: November 13, 1957
Creator: Musial, Norman T. & Bowditch, David
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a 1/4 Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Longitudinal Stability and Control and Horizontal-Tail Hinge-Moment and Normal-Force Characteristics of the Model Equipped With a Drooped Supersonic-Type Elliptical Wing-Root Inlet

Description: Report presenting testing of the Republic F-105 at low speeds to determine the results of additional longitudinal stability tests of measurements of the hinge moments and normal force of the all-movable horizontal tail on a model equipped with a supersonic-type elliptical wing-root inlet.
Date: November 14, 1955
Creator: Cancro, Patrick A. & Kelly, H. Neale
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Investigation at Low Speed of the Aerodynamic Characteristics of the Army Chemical Corps Model E112 Bomblets

Description: Report discussing an experimental investigation to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. From Summary: "A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration." A large amount of data collected from testing and photographs of the model are provided.
Date: November 4, 1955
Creator: Letko, William & Williams, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compilation and Analysis of U.S. Turbojet and Ram-Jet Engine Characteristics

Description: Report presenting a compilation of sea-level static and flight-performance data for existing and designed U.S. axial-flow turbojet and ram-jet engines. Factors considered include engine size, performance, and weight, and actual and theoretical performances are compared.
Date: November 27, 1956
Creator: Cesaro, Richard S. & Walker, Curtis L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Results of the Flight Test of a 0.13-Scale Rocket-Boosted Model of the McDonnell F4H-1 Airplane Between Mach Numbers of 0.20 and 1.90

Description: Report discussing tests performed with a rocket-boosted model of the McDonnell F4H-1 airplane at transonic and supersonic speeds. Special attention is given to the external drag coefficient at various Mach numbers. Large pitching oscillations were also noted at Mach numbers between 0.20 and 1.17, which made it impossible to determine the drag at that range.
Date: November 8, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Airborne Simulator Investigation of the Accuracy of an Optical Track Command Missile Guidance System

Description: Memorandum presenting an airborne missile simulator used to represent visually the predicted flight behavior of the Navy XASM-N-7 Bullpup air-to-surface missile, which is guided along the line of sight to the target by bang-bang radio signals controlled by the pilot of the launch airplane. Quantitative response measurements showed that the simulator gave a good representation of the trajectory and control characteristics predicted for the Bullpup missile, and the simulation appeared plausible t… more
Date: November 23, 1956
Creator: Douvillier, Joseph G., Jr.; Foster, John V. & Drinkwater, Fred J., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Low-Temperature Nuclear-Powered Ramjet Missile for High Altitudes

Description: From Summary: "The reactor operating conditions were varied to enable selection of values giving a good compromise between low uranium investment and loss gross weight at each altitude and flight Mach number considered. The corresponding values of reactor and missile operating conditions are presented in the report."
Date: November 9, 1955
Creator: Rom, F. E. & Sams, E. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Large-Scale Wind-Tunnel Tests of an Airplane Model With a 45 Degree Sweptback Wing of Aspect Ratio 2.8 With Area Suction Applied to Trailing-Edge Flaps and With Several Wing Leading-Edge Modifications

Description: Memorandum presenting an investigation of an airplane model to determine the effect of area suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. The wing had an aspect ratio of 2.8 and a taper ratio of 0.17.
Date: November 2, 1956
Creator: Koenig, David G. & Aoyagi, Kiyoshi
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation of the Stability of the Antisubmarine Rocket Mk 1 Mod 0

Description: Report discussing an investigation to determine the cause and provide a fix for the instability in flight of the antisubmarine rocket Mk 1 Mod 0. The Magnus effects and their nonlinear variation with angle of attack were found to affect the stability, so reducing the Magnus effects should reduce instability in the missiles. The greatest reduction of Magnus effects was found through a combination of nose-ring spoiler and the original direction of the propeller rotation, but the nose ring increas… more
Date: November 13, 1952
Creator: Lichtenstein, Jacob H. & Williams, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Performance Data Obtained in a Full-Scale Free-Jet Investigation of a Side-Inlet Supersonic Diffuser

Description: Report discussing an investigation into the performance of several modifications of a side-inlet ramjet engine diffuser. Total-pressure-recovery profiles, Mach number profiles, longitudinal wall static pressure distributions, and variation of the average-static to average-total pressure are presented.
Date: November 30, 1954
Creator: Farley, John M. & Smith, Ivan D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a 1/4-Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Lateral Control and Directional Stability and Control Characteristics of Model Equipped With Drooped, Supersonic-Type, Elliptical Wing-Root Inlet

Description: Report presenting low-speed testing of the Republic F-105 airplane in the pressure tunnel to determine the plane's lateral control and directional stability and control characteristics. Various combinations of components were tested, including tares, spoilers, ailerons, and wing fences.
Date: November 10, 1955
Creator: Cancro, Patrick A. & Kelly, H. Neale
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of Reflections of Oblique Waves from a Porous Wall

Description: "A porous wall was used in an attempt to eliminate reflections of oblique waves from a tunnel wall. Calculations were made of the required resistance characteristics of a wall in order that the flow through the wall, due to the pressure difference across a shock wave, would equal the component normal to the wall of the flow behind the shock wave. The resistance characteristic of a sintered bronze wall was measured and the reflections of waves impinging on the wall were observed at a Mach number… more
Date: November 9, 1950
Creator: Davis, Don D., Jr. & Wood, George P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Thermal Stability of Decaborane and of a Commercial Ethyl Decaborane (HEF-3) in the Range 202 Degrees to 252 Degrees C

Description: Report discussing an investigation of the thermal stabilities of a commercial grade of ethyl decaborane and decaborane at two temperatures. Equations developed from the results of the experiment are also provided. Ethyl decaborane was found to be more stable to pyrolysis than pentaborane but less stable than decaborane.
Date: November 29, 1956
Creator: McDonald, G. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method for Calculating the Lift and Center of Pressure of Wing-Body-Tail Combinations at Subsonic, Transonic, and Supersonic Speeds

Description: Report presenting a method for calculating the lift and pitching-moment characteristics of circular cylindrical bodies in combination with triangular, rectangular, or trapezoidal wings or tails through the subsonic, transonic, and supersonic speed ranges. A computing table and set of design charts are presented to reduce the calculations to routine operations. Information about lift, center of pressure, effects of wing incidence, and limitations and extensions of the method is provided.
Date: November 12, 1953
Creator: Nielsen, Jack Norman; Kaattari, George E. & Anastasio, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of a High Subsonic Mach Number Turbine Having High Rotor Blade Suction-Surface Diffusion

Description: Memorandum presenting a high subsonic Mach number turbine with high suction-surface diffusion investigated experimentally. The subject turbine was designed for a high weight flow per unit frontal area, a high specific work output, and a relative critical velocity ratio of 0.82 at the rotor hub input.
Date: November 20, 1956
Creator: Nusbaum, William J. & Hauser, Cavour H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of Pentaborane, Pentaborane - JP-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-scale Turbojet Engine

Description: Report presenting summaries of full-scale engine tests of pentaborane, pentaborane-JP-4 fuel mixtures, and trimethylborate-methyl-alcohol-azeotrope fuels. Tests were conducted at an altitude of 50,000 feet and Mach number of 0.8. Results regarding the fuel effects on overall performance, effects on component performance, effect of turbine-outlet temperature on engine performance, and miscellaneous observations are provided.
Date: November 20, 1956
Creator: Breitwieser, Roland & Useller, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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