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Investigation of performance of several double-shroud ejectors and effect of variable-area exhaust nozzle on single ejector performance

Description: Report presenting an investigation to determine the characteristics of a double-shroud cooling-air ejector. The performance of a single-shroud ejector with a clamshell-type variable-area actuating nozzle was compared with that of an ejector having a conical nozzle. Results regarding the mechanics of ejector flow systems, effect of variable-area primary nozzle on ejector performance, double-shroud-ejector performance, and application of data are provided.
Date: July 15, 1952
Creator: Ellis, C. W.; Hollister, D. P. & Wilsted, H. D.
Partner: UNT Libraries Government Documents Department

Experimental ablation cooling

Description: Report presenting the results of an experimental investigation on the ablation of a number of promising materials for heating conditions comparable to those which maybe encountered by unmanned reentry satellite vehicles or heating conditions associated with reentry ballistic missiles. Results regarding exploratory tests, further Teflon tests, and graphite testing are provided.
Date: July 15, 1958
Creator: Bond, Aleck C.; Rashis, Bernard & Levin, L. Ross
Partner: UNT Libraries Government Documents Department

Altitude-performance and Reynolds number investigation of centrifugal-flow-compressor turbojet engine

Description: From Introduction: "Altitude-chamber and wind-tunnel investigations of the performance of turbojet engines such as those reported in references 1 to 4 have shown that the conventional correction factors fail to generalize the engine performance variables at high altitudes. An investigation was therefore made at the NACA Lewis laboratory to determine the altitude performance of the J33-A-23 turbojet engine and to demonstrate the magnitude of departure of actual altitude performance from that predicted from sea-level performance."
Date: May 15, 1951
Creator: Wilsted, H. D. & Grey, R. E.
Partner: UNT Libraries Government Documents Department

Comparison of experimental with calculated results for the lifting effectiveness of a flexible 45 degree sweptback wing of aspect ratio 6.0 at Mach numbers from 0.8 to 1.3

Description: Report presenting tests conducted on models with 45 degree sweptback wings with varying degrees of flexibility to determine the effective lift-curve slopes in order to evaluate the usefulness of a general method for predicting effective lift ratio by a comparison of predicted values with test results.
Date: April 15, 1954
Creator: Walters, Richard E.
Partner: UNT Libraries Government Documents Department

Additional comparisons between computed and measured transonic drag-rise coefficients at zero lift for wing-body-tail configurations

Description: From Introduction: "This report makes further comparisons of the theoretical computing method with available experimental results, showing effects of wing plan-form changes, and the effect of an airfoil-section change on a wing of given plan form."
Date: August 15, 1955
Creator: Holdaway, George H.
Partner: UNT Libraries Government Documents Department

Observation of Laminar Flow on a Blunted 15 Degree Cone-Cylinder in Free Flight at High Reynolds Numbers and Free-Stream Mach Numbers to 8.17

Description: "A highly polished 15 degree included-angle cone-cylinder with hemispherical tip has been flown to obtain boundary-layer transition and heat-transfer data. The model was launched from a carrier plane at an altitude of 47,500 feet. Laminar flow existed at a Reynolds number greater than 38.5 x 10(exp) 6 on the cylinder when the model was at the peak free-stream Mach number of 8.17. The results indicate an appreciable and favorable effect of tip bluntness in raising the allowable skin temperature for a given boundary-layer transition Reynolds number" (p. 1).
Date: October 15, 1956
Creator: Disher, John H. & Rabb, Leonard
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 5: Effect of Reducing Inlet-Guide-Vane Turning on Over-All and Inlet-Stage Performance

Description: Report presenting an investigation in which the inlet-guide-vane setting of a 10-stage compressor was reduced in order to approximate more closely the design absolute entrance flow angles to the first rotor. In order to determine the effects of these changes, the performance of the inlet stage was obtained simultaneously with the overall compressor performance for both the original and reduced incidence angles. Results regarding the compressor performance, inlet-stage performance, and effect of guide-vane resetting on compressor performance are provided.
Date: March 15, 1954
Creator: Budinger, Ray E. & Serovy, George K.
Partner: UNT Libraries Government Documents Department

Altitude Free-Jet Investigation of Dynamics of a 28-Inch-Diameter Ram-Jet Engine

Description: From Introduction: "The feasibility of closed-loop control of ram-jet-engine thrust is demonstrated in references 1 and 2. The dynamic behavior of a 28-inch-diameter ram-jet engine designed to operate in Mach number range of 2.35 to 2.70 is evaluated herein."
Date: January 15, 1957
Creator: Wentworth, Carl B.; Dunbar, William R. & Crowl, Robert J.
Partner: UNT Libraries Government Documents Department

Altitude Performance of a 20-Inch-Diameter Ram-Jet Engine Investigated in a Free Jet Facility at Mach Number 3.0

Description: Report presenting an investigation of the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 in a free-jet facility over a range of simulated altitudes. Results regarding the diffuser characteristics, combustor performance, thrust output, and operational characteristics are provided.
Date: June 15, 1953
Creator: Smolak, George R. & Wentworth, Carl B.
Partner: UNT Libraries Government Documents Department

Longitudinal Characteristics at Transonic and Supersonic Speeds of a Rocket-Propelled Airplane Model Having a 60-Degree Delta Wing and Low Swept Horizontal Tail

Description: Report presenting measurements of the longitudinal stability, lift, and drag characteristics of an airplane configuration with a 60 degree delta wing and a swept horizontal tail mounted near the wing plane extended at a range of Mach numbers using the rocket-model technique. Comparisons are made to data form a similar model with the tail mounted above the wing plane.
Date: September 15, 1955
Creator: Peck, Robert F. & Coltrane, Lucille C.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Effect of Fuel Composition, Engine Operating Variables, and Spark-Plug Type and Condition on Preignition-Limited Performance of an R-2800 Cylinder

Description: The preignition characteristics of the R-2800 cylinder, as effected by fuel consumption, engine operating variables, and spark plug type and condition, were evaluated. The effects on preignition-limited performance of various percentages of aromatics (benzene, toluene, cumene, xylene) in a base fuel of triptane were investigated. Two paraffins (triptane and S + 6.0 ml TEL/gal) and two refinery blends (28-R and 33-R) were preignition rated. The effect of changes in the following engine operating variables on preignition limit was determined: inlet-air temperature, rear spark plug gasket temperature, engine speed, spark advance, tappet clearance, and oil consumption. Preignition limits of the R-2800 cylinder using Champion C34S and C35S and AC-LS86, LS87, and LS88 spark plugs were established and the effect of spark plug deterioration was investigated.
Date: November 15, 1946
Creator: Pfender, John F.
Partner: UNT Libraries Government Documents Department

Initial flight investigation of a twin engine supersonic ram jet

Description: From Summary: "A flight investigation was made of a supersonic twin-ram-jet test vehicle using short-flame-length burners. The test demonstrated a maximum acceleration of 3.6g and a maximum flight Mach number of 3.02. Data were obtained over a Mach number range from about 1.9 to 3.0, an altitude range from 1,800 to 40,900 feet, and a fuel-air-ratio range from 0.012 to 0.065."
Date: September 15, 1950
Creator: Faget, Maxime A. & Dettwyler, H. Rudolph
Partner: UNT Libraries Government Documents Department

Investigation of power extraction characteristics and braking requirements of a windmilling turbojet engine

Description: Report presenting an investigation in an altitude chamber to determine the power extraction and braking characteristics of a windmilling single-spool axial-flow turbojet engine of the 5000-pound thrust class over a range of altitudes and Mach numbers. Results regarding extractable horsepower from a windmilling engine, total pressure gradient through a windmilling engine, contribution of a compressor to extracted horsepower, and braking of the windmilling engine are provided.
Date: July 15, 1952
Creator: Walker, Curtis L. & Fenn, David B.
Partner: UNT Libraries Government Documents Department

Investigation of a variable Mach number supersonic tunnel with nonintersecting characteristics

Description: Report presenting a method for the design of supersonic-wind-tunnel nozzles that produce uniform flow over a continuously variable Mach number range without the use of flexible walls. Experimental results from a preliminary investigation of the tunnel are included, including calibration survey of flow, Mach number distributions, and pressure gradients are provided.
Date: November 15, 1948
Creator: Evvard, John C. & Wyatt, DeMarquis D.
Partner: UNT Libraries Government Documents Department

Investigation of a missile airframe with control surfaces consisting of projecting quadrants of the nose cone

Description: Report presenting the results of an investigation of a missile model with extensible control surfaces and small-span fins. Normal-force, axial-force, and pitching-moment coefficients based on body cross-sectional area and diameter are given for various control deflections up to a maximum of 30 degrees.
Date: March 15, 1954
Creator: Lazzeroni, Frank A.
Partner: UNT Libraries Government Documents Department

Effect on Drag of Longitudinal Positioning of Half-Submerged and Pylon-Mounted Douglas Aircraft Stores on a Fuselage with and without Cavities between Mach Numbers 0.9 and 1.8

Description: From Summary: "The effect on drag of positioning symmetrically mounted Douglas Aircraft Company, Inc. stores in pairs on a parabolic fuselage of fineness ratio 10.0 has been determined by flight tests of rocket-propelled, zero-lift models through a range of Mach number from 0.9 to 1.8. The stores were mounted in half-submerged positions and on pylons and were tested in three longitudinal locations on the fuselage with the forward position being located at the maximum diameter of the fuselage. The effects on drag of removing the half-submerged stores or extending them outward on pylons also was investigated by tests of models with half-submerged-store cavities on the fuselage. Two pylons differing in airfoil section and thickness were tested at the forward position of the stores on the fuselage with cavities."
Date: July 15, 1954
Creator: Hoffman, Sherwood & Wolff, Austin L.
Partner: UNT Libraries Government Documents Department

Tests in the Ames 40- by 80-foot wind tunnel of the effects of varying wing modifications on the longitudinal characteristics of two-triangular wing airplane models with and without horizontal tails

Description: Report presenting an investigation with the objective of eliminating destabilizing changes of pitching moment through the use of wing modifications for two airplane models with triangular wings of aspect ratio 2 and 3. Models were tested with horizontal tails above the extended wing chord plane and with the tail off.
Date: April 15, 1954
Creator: Koenig, David G.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of a technique for stability studies of a self-propelled model of a submerged submarine

Description: Report presenting the initial development of a technique for the qualitative study of the stability and control characteristics of a free, self-propelled dynamic submarine model in Langley tank no. 1. Two types of control systems were evaluated, but only one provided satisfactory results at the desired test speeds. Results regarding the qualitative analysis of the control systems, dive paths, equations of motion, and comparison with experimental paths are provided.
Date: April 15, 1954
Creator: McKann, Robert E. & Petynia, William W.
Partner: UNT Libraries Government Documents Department

Effect of leading-edge-flap deflection on the wing loads, load distributions , and flap hinge moments of the Douglas X-3 research airplane at transonic speeds

Description: Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the wing of the Douglas X-3 research airplane with various leading-edge-flap deflections. The load and hinge-moment characteristics of the leading-edge flap are presented for a range of Mach numbers with and without flap deflection. Results regarding chordwise load distributions, wing-section and wing-panel characteristics, span load and pitching-moment distributions, leading-edge-flap characteristics, and a comparison with wind-tunnel data are provided.
Date: July 15, 1958
Creator: Keener, Earl R.; McLeod, Norman J. & Taillon, Norman V.
Partner: UNT Libraries Government Documents Department

The longitudinal characteristics at Mach numbers up to 0.92 of a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10

Description: Report presenting an investigation of a sweptback wing in combination with a fuselage of a type considered suitable for long-range, high-speed airplanes in the 12-foot pressure wind tunnel. The investigations included tests of the wing alone, the wing-fuselage combination, and the effects of fences.
Date: September 15, 1952
Creator: Edwards, George G.; Tinling, Bruce E. & Ackerman, Arthur C.
Partner: UNT Libraries Government Documents Department

Full-scale performance study of a prototype crash-fire protection system for reciprocating-engine-powered airplanes

Description: Report presenting an experimental airplane crash in order to study the performance of a prototype crash-fire inerting system for reciprocating-engine-powered airplanes. A fire did not occur during this crash, indicating that the crash-fire inerting system functioned satisfactorily as a complete unit. Further improvements in the crash-fire system are also provided.
Date: November 15, 1955
Creator: Black, Dugald O. & Moser, Jacob C.
Partner: UNT Libraries Government Documents Department