National Advisory Committee for Aeronautics (NACA) - 523 Matching Results

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Ditching Investigation of a 1/10-Scale Model of the North American F-86 Airplane

Description: "An investigation was made of a 1/10-scale dynamically similar model of the North American F-86 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings" (p. 1).
Date: 1954
Creator: Fisher, Lloyd J. & McBride, Ellis E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary drag measurements of the consolidated Vultee XF-92A delta-wing airplane in flight tests to a Mach number of 1.01

Description: Report presenting preliminary drag data obtained for the XF-92A delta wing airplane during demonstration tests after it had been modified to use the J33-A-29 turbojet engine. Drag data, lift coefficients, and lift-curve slopes are provided.
Date: January 4, 1954
Creator: Bellman, Donald R. & Sisk, Thomas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Free-Flight Measurements of the Zero-Lift Drag Rise of Six Airplane Configurations and Their Equivalent Bodies of Revolution at Transonic Speeds

Description: "Free-flight drag measurements are presented which show the practicability of duplicating the zero-lift drag rise of many airplane configurations by simple bodies of revolution. The results confirm the transonic area rule for straight wings, and for delta and modified-delta wings with and without nacelles. The results showed that the area rule did not apply to one swept-wing configuration and an explanation is advanced to explain why it does not apply" (p. 1).
Date: January 5, 1954
Creator: Hall, James Rudyard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect on Transonic and Supersonic Drag of a Fuselage Protuberance of an Essential Unswept Wing-Fuselage Combination

Description: "An investigation of the effect on transonic and supersonic drag of a fuselage protuberance designed to improve the overall longitudinal distribution of cross-sectional area of an essentially unswept wing-fuselage combination has been made with free-flight rocket models. The wing-fuselage configuration was tested with and without a fuselage protuberance designed to relieve the steep area gradient over the rear portion of the wing" (p. 1).
Date: January 5, 1954
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Investigation of the Effects of Location of a Delta and a Straight Tail on the Longitudinal Stability and Control of a Thin Delta Wing With Extended Double Slotted Flaps

Description: Report presenting an investigation to determine the effects of horizontal-tail location and plan form on the longitudinal stability and control characteristics of a fuselage and thin delta wing with extended double slotted flaps. Several configurations of the aircraft, including flaps with the tail off, extended double slotted flaps, and canard with extended double slotted flap and delta tail are explored.
Date: January 5, 1954
Creator: Riebe, John M. & Graven, Jean C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of leading-edge chord extensions and an all-movable horizontal tail on the aerodynamic characteristics of a wing-body combination employing a triangular wing of aspect ratio 3 mounted in a high position at subsonic and supersonic speeds

Description: Report presenting the results of an experimental investigation of the effect of leading-edge chord extensions on the aerodynamic characteristics of a wing-body-tail combination employing a 3-percent-thick triangular wing of aspect ratio 3 in conjunction with an unswept, all-movable, horizontal tail located below the wing-chord plane. Lift, drag, pitching moment, and hinge moment were measured a range of Mach numbers and a constant Reynolds number.
Date: January 6, 1954
Creator: Wetzel, Benton E. & Pfyl, Frank A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of performance and starting characteristics of liquid fluorine: Liquid oxygen mixtures with jet fuel

Description: From Summary: "The performance of jet fuel with an oxidant mixture containing 70 percent liquid fluorine and 30 percent liquid oxygen by weight was investigated in a 500-pound-thrust engine operating at a chamber pressure of 300 pounds per square inch absolute. A one-oxidant-on-one-fuel skewed-hole impinging-jet injector was evaluated in a chamber of characteristic length equal to 50 inches. A maximum experimental specific impulse of 268 pound-seconds per pound was obtained at 25 percent fuel, … more
Date: January 6, 1954
Creator: Rothenberg, Edward A. & Ordin, Paul M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Study of the physical properties of petrolatum-stabilized magnesium-hydrocarbon slurry fuels

Description: Magnesium-hydrocarbon slurries containing a moderate proportion of petrolatum have physical properties such that they offer promise as experimental aircraft fuels. The settling of the magnesium is greatly retarded by the petrolatum, and the slurries can easily be remixed to their original condition after storage. Successive batches which have closely similar properties can be prepared readily. The apparent viscosity of these slurries increased rapidly with increasing magnesium concentration, wi… more
Date: January 6, 1954
Creator: Pinns, Murray L. & Goodman, Irving A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effects of Operating Propellers on the Longitudinal Characteristics at High Subsonic Speeds of a Four-Engine Tractor Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10

Description: Report presenting an investigation at high subsonic speeds to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Testing was conducted at a range of angles of attack, propeller thrust coefficients, Mach numbers, and Reynolds numbers.
Date: January 7, 1954
Creator: Sutton, Fred B. & Demele, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Speed-Brake Investigation at Low Speed of a 1/10-Scale Model of the MX-1554A Airplane With a Circular Jet Nozzle

Description: Report discussing an investigation of the effect of curved speed brakes on the drag characteristics and longitudinal stability and control characteristics of a model of the MX-1554A with a circular jet nozzle. The speed brakes were tested at several deflections, gaps, and locations in the landing configuration and clean configuration. Results of a lateral- and directional-stability study due to reduction in the vertical tail area are also provided.
Date: January 7, 1954
Creator: Solomon, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Speed-Brake Investigation at Low Speed of a 1/10-Scale Model of the MX-1554A Airplane With a Circular Jet Nozzle

Description: Memorandum presenting data from an investigation of the effect of curved speed brakes on the drag characteristics and on the longitudinal stability and control characteristics of a scale model of the MX-1554A airplane redesigned to incorporate a circular jet nozzle. The speed brakes were tested at several deflections,gaps, and locations on the landing configuration and the clean configuration.
Date: January 7, 1954
Creator: Solomon, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical and experimental studies of a divided-flow ram-jet combustor

Description: From Introduction: "The investigation reported herein is a continuation of a ram-jet-combustor design program being conducted at the NACA Lewis laboratory. The purpose of this broad program is to establish basic design criteria for combustors operating over wide range of fuel-air ratio with low pressure losses and high combustion efficiency, and to utilize these design criteria in the development of practical ram-jet combustors."
Date: January 11, 1954
Creator: Dangle, E. E.; Friedman, Robert & Cervenka, Adolph J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Transonic Speeds of the Lateral-Control and Hinge-Moment Characteristics of a Flap-Type Spoiler Aileron on a 60 Degree Delta Wing

Description: This paper present results of an investigation of the lateral-control and hinge-moment characteristics of a 0.67 semispan flap-type spoiler aileron on a semispan thin 60 degree delta wing at transonic speeds by the reflection-plane technique. The spoiler-aileron had a constant chord of 10.29 percent mean aerodynamic chord and was hinged at the 81.9-percent-wing-root-chord station. Results indicated reasonably linear variations of rolling-moment and hinge-moment coefficients with spoiler project… more
Date: January 11, 1954
Creator: Wiley, Harleth G. & Taylor, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measured and Estimated Lateral Static and Rotary Derivatives of a 1/12-Scale Model of a High-Speed Fighter Airplane With Unswept Wings

Description: Report presenting a low-speed investigation to determine the lateral static and rotary derivatives of a model of a high-speed fighter airplane. The purpose was to compare experimental stability derivatives with derivatives estimated for a wing-fuselage combination, a vertical- and horizontal-tail combination, and a complete model.
Date: January 11, 1954
Creator: Williams, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Several Jet-Engine Air-Inlet Configurations on the Low-Speed Static Longitudinal Stability Characteristics and Quantity Flow of a 1/6-Scale Model of the MX-1764 Airplane

Description: Memorandum presenting an investigation in the 7- by 10-foot tunnel to determine the effect of wing-root leading-edge and scoop-type jet-engine air-inlet configurations on the static longitudinal stability characteristics and the duct-flow characteristics of a scale model of the MX-1764 airplane. The addition of the inlet configurations to the model generally resulted in slight reductions in longitudinal stability and increases of maximum lift coefficient.
Date: January 12, 1954
Creator: Croom, Delwin R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of several jet-engine air-inlet configurations on the low-speed static longitudinal stability characteristics and quantity flow of a 1/6-scale model of the MX-1764 airplane

Description: Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the effect of wing-root leading-edge and scoop-type jet-engine air-inlet configurations on the static longitudinal stability characteristics and the duct-flow characteristics of a model of the MX-1764 airplane. The inlet configurations generally resulted in slight reductions in longitudinal stability and increases of maximum lift coefficient.
Date: January 12, 1954
Creator: Croom, Delwin R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of the Oscillating Forces and Moments on a Two-Dimensional Wing Equipped With an Oscillating Circular-Arc Spoiler

Description: Report presenting an investigation in the flutter research tunnel to determine the oscillating forces and moments on a two-dimensional wing equipped with an oscillating circular-arc spoiler. The study indicated that force and moment coefficients and their phase angles are affected by Reynolds number, Mach number, and reduced frequency.
Date: January 12, 1954
Creator: Clevenson, Sherman A. & Tomassoni, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A summary of information on support interference at transonic and supersonic speeds

Description: From Summary: "A compilation has been made of available information on the problem of support interference at transonic and supersonic speeds. This compilation indicates that at supersonic speeds there are sufficient experimental data to design properly sting supports and shrouds having negligible interference. At transonic speeds the interference problem becomes more acute, and more experimental information is needed."
Date: January 12, 1954
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of the Rolling Effectiveness of Fingered Semaphore Spoilers on a Tapered 45 Sweptback Wing Between Mach Numbers 0.6 and 1.3

Description: Report discussing an investigation of a fingered semaphore spoiler and an equivalent solid spoiler configuration to determine the effects of spoiler projection, porosity, and chordwise position on the rolling effectiveness and drag of spoiler arrangements at a range of Mach numbers. The fingered semaphore spoilers were found to have less rolling effectiveness and drag than the solid spoilers.
Date: January 14, 1954
Creator: Church, James D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of rocket-model tests at zero lift of an arrow-wing missile configuration from Mach numbers of 0.9 to 1.8

Description: Report presenting flight tests conducted between Mach numbers of 0.9 to 1.8 over a range of Reynolds numbers to determine the zero-lift drag and some rolling-effectiveness characteristics of a proposed long-range, supersonic, ground-to-ground missile. Results regarding the longitudinal trim, drag, rolling effectiveness, and instability due to roll are provided.
Date: January 14, 1954
Creator: Arbic, Richard G. & Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Dynamic Corrosion in an Iron - Stainless Steel Toroid by Sodium at 900 Degrees F

Description: Memorandum presenting a corrosion investigation conducted with molten sodium flowing at a velocity of 25 feet per second in a toroid of AISI type 347 stainless steel with an insert consisting of seven Globeiron tubes in parallel at the hot zone. A 500-hour test was run at a nominal outer wall temperature of 500 degrees Fahrenheit with a temperature difference between the hot and cold sections of 40 degrees.
Date: January 15, 1954
Creator: Lad, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of the effects of horizontal-tail height, moment of inertia, and control effectiveness on the pitch-up characteristics of a 35 degree swept-wing fighter airplane at high subsonic speeds

Description: Report presenting a flight investigation conducted on a 35 degree swept-wing fighter airplane with two different horizontal-tail heights. The longitudinal stability and buffet characteristics were compared for the two configurations. Results regarding longitudinal stability, buffet, and pitch-up intensity are provided.
Date: January 18, 1954
Creator: McFadden, Norman M. & Heinle, Donovan R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds

Description: At the request of the Bureau of Aeronautics, Department of the Navy, National Advisory Committee for Aeronautics has conducted a preliminary investigation at high subsonic speeds of the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane. The tests covered a Mach number range from 0.5 to 0.94 and corresponding Reynolds numbers, based on the wing mean aerodynamic chord, from 3.3 x 10(exp 6) to 4.3 x 10(exp 6). The maxi… more
Date: January 18, 1954
Creator: Spreemann, Kenneth P. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison at supersonic speeds of translating spike inlets having blunt- and sharp-lip cowls

Description: Report presenting an investigation of two translating spike inlets with blunt- and sharp-lip cowls in the supersonic wind tunnel at a range of free-stream Mach numbers and angles of attack. Results regarding the inlet stability, critical inlet performance at zero angle of attack, and inlet-engine matching are provided.
Date: January 19, 1954
Creator: Gorton, Gerald C. & Dryer, Murray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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