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Comparison of Injectors With a 200-Pound-Thrust Ammonia-Oxygen Engine

Description: "Characteristic exhaust velocity was measured for a small range of mixture ratios with four different injectors. Performances of parallel-sheet, like-on-like, and triplet injectors were about the same, but a parallel-jet injector had a much lower performance. Performance values for ammonia-oxygen were slightly lower than for heptane-oxygen" (p. 1).
Date: September 4, 1958
Creator: Priem, Richard J. & Clark, Bruce J.
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control of High-Speed Airplanes With Particular Reference to Dive Recovery

Description: "An analysis of the effects of compressibility on the longitudinal stability, control, and trim of airplanes flying at high subsonic speeds and a discussion of the causes of and the means for lessening or preventing the diving tendency are presented. Wind-tunnel results for Mach numbers up to 0.90 are included for purposes of illustration and cover several investigations of longitudinal stability and control, airfoil characteristics, dive-recovery aids, and elevator characteristics. Methods are… more
Date: September 4, 1947
Creator: Axelson, John A.
Partner: UNT Libraries Government Documents Department
open access

Design and Experimental Performance of a 0.35 Hub-Tip Radius Ratio Transonic Axial-Flow-Compressor Rotor Designed for 40 Pounds Per Second Per Unit Frontal Area

Description: Memorandum presenting an investigation to determine the feasibility of a high-performance transonic axial-flow compressor stage with a weight flow of 40 pounds per second per square foot of frontal area. A transonic axial-flow inlet stage with a hub-tip ratio of 0.35 and an axial Mach number of approximately 0.75 was designed and fabricated. Results regarding overall rotor performance, flow parameters, radial matching of blade-element sections, and comparison of blade-element parameters with de… more
Date: September 4, 1958
Creator: Montgomery, John C. & Yasaki, Paul T.
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the McDonnell XP-88 Airplane with a Conventional Tail

Description: "An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the normal loading were determined. Tests of the model in the long-range loading also were made" (p. 1).
Date: September 4, 1947
Creator: Berman, Theodore
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of the 1/25-Scale Powered Model of the Martin JRM-1 Airplane. 4 - Tests with Ground Board and with Modified Wing and Hull - TED No. NACA 232, Part 4, Tests with Ground Board and with Modified Wing and Hull, TED No. NACA 232

Description: From Summary: "Wind-tunnel tests were made of a 1/25 scale model of the Martin JRM-1 airplane to determine: (1) The longitudinal stability and control characteristics of the JRM-1 model near the water and lateral and directional stability characteristics with power while moving on the surface of the water, the latter being useful for the design of tip floats; (2) The stability and stalling characteristics of the wing with a modified airfoil contour; (3) Stability characteristics of a hull of la… more
Date: September 4, 1947
Creator: Lockwood, Vernard E. & Smith, Bernard J.
Partner: UNT Libraries Government Documents Department
open access

Performance Characteristics at Mach Numbers to 2.0 of Various Types of Side Inlets Mounted on Fuselage of Proposed Supersonic Airplane 2: Inlets Utilizing Half of a Conical Spike

Description: Report presenting an investigation to determine the performance of twin-scoop side inlets mounted on the fuselage of a proposed supersonic aircraft. The inlets had half of a conical spike as the compression surface and a ram-type boundary-layer-removal system. Results regarding the first inlet and redesigned inlet are provided.
Date: September 4, 1952
Creator: Allen, J. L. & Simon, P. C.
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Fixed-Area Exhaust Nozzle

Description: Report presenting an investigation to determine the overall performance of a prototype model of the J47D (RX1-1) turbojet engine with a fixed-area exhaust nozzle. Data was obtained for a range of engine speeds, altitudes, and Mach numbers. Results regarding the effect of those variables and generalization in terms of pumping characteristics are provided.
Date: September 4, 1951
Creator: Saari, M. J. & Wintler, J. T.
Partner: UNT Libraries Government Documents Department
open access

Investigation of low-pressure performance of experimental tubular combustors differing in air-entry-hole geometry

Description: Report presenting an investigation to determine, by experiments within the scope of air-entry-hole geometry, design criteria for tubular combustors with good low-pressure performance. Combustion efficiency, operable fuel-air-ratio and pressure ranges, and minimum ignition pressures were determined for several combustor configurations at conditions simulating a 5.2-pressure-ratio turbojet engine operating at 85 percent of rated rotor speed, a flight Mach number of 0.6, and altitudes from 56,000 … more
Date: September 4, 1953
Creator: Dittrich, Ralph T.
Partner: UNT Libraries Government Documents Department
open access

Tests of the NACA 0010-1.50 40/1.051 Airfoil Section at High Subsonic Mach Numbers

Description: Memorandum presenting the aerodynamic characteristics of the NACA 0010-1.50 40/1.051 airfoil section as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. The results are compared with those of the effects of leading-edge-radius variation from 0.27 to 1.10 percent of the chord on the characteristics of a 10-percent-thick, symmetrical airfoil section at high subsonic Mach numbers. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristic… more
Date: September 4, 1953
Creator: Hemenover, Albert D.
Partner: UNT Libraries Government Documents Department
open access

A Comparison of Several Systems of Boundary-Layer Removal Ahead of a Typical Conical External-Compression Side Inlet at Mach Numbers of 1.88 and 2.93

Description: Report presenting an investigation at Mach numbers 1.88 and 2.93 to determine the performance characteristics of a conical external-compression side inlet model with a swept-leading-edge boundary-layer-removal scoop. Two other boundary-layer-removal systems were also investigated, which used a deflection wedge and cowl-lip scoops. Results regarding swept-scoop inlets, scoop performance, alternative boundary-layer-removal systems at Mach 1.88, and a comparison of the boundary layer removal syste… more
Date: September 4, 1953
Creator: Piercy, Thomas G. & Johnson, Harry W.
Partner: UNT Libraries Government Documents Department
open access

The Calculated and Experimental Incremental Loads and Moments Produced by Split Flaps of Various Spans and Spanwise Locations on a 45 Degrees Sweptback Wing of Aspect Ratio 8

Description: Report presenting the incremental lift and pitching moments produced by 20-percent-chord split flaps of various spans at various spanwise positions on two 45 degree sweptback wings of aspect ratio 8.02 as obtained by pressure-distribution testing. Inboard flaps were found to be far more effective in producing lift than outboard flaps. Results regarding spanwise loading and pitching moment are provided.
Date: September 4, 1953
Creator: Kelly, H. Neale
Partner: UNT Libraries Government Documents Department
open access

Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades

Description: From Summary: "Average spanwise blade temperatures and cooling-air pressure losses through a small (1.4-in, span, 0.7-in, chord) air-cooled turbine blade were calculated and are compared with experimental nonrotating cascade data. Two methods of calculating the blade spanwise metal temperature distributions are presented. The method which considered the effect of the length-to-diameter ratio of the coolant passage on the blade-to-coolant heat-transfer coefficient and assumed constant coolant pr… more
Date: September 4, 1958
Creator: Stepka, Francis S.
Partner: UNT Libraries Government Documents Department
open access

Thermal reaction of diborane with trimethylborane

Description: Report presenting testing of diborane and trimethylbornae in a tube at 235 to 300 degrees Celsius in the presence of hydrogen. Methylpentaboranes were produced and separated in a specially designed vacuum fractionation column. Results indicated that two isomers of monomethylpentaborane were isolated and that one had not been previously reported on.
Date: September 4, 1958
Creator: Lamneck, John H., Jr. & Kaye, Samuel
Partner: UNT Libraries Government Documents Department
open access

Investigation of Turbines for Driving Supersonic Compressors 5: Design and Performance of Third Configuration With Nontwisted Rotor Blades

Description: Report presenting the design and performance of a turbine with nontwisted rotor blades designed to drive a high-speed, high-specific-mass-flow supersonic compressor. Results regarding turbine performance, entrance Mach number, radial temperature surveys, and loading are provided.
Date: September 4, 1953
Creator: Whitney, Warren J.; Stewart, Warner L. & Monroe, Daniel E.
Partner: UNT Libraries Government Documents Department
open access

Investigation of thrust augmentation using water-alcohol injection on a 5200-pound-thrust axial-flow-type turbojet engine at static sea-level conditions

Description: Report presenting an investigation to evaluate the thrust augmentation available with various types of water-alcohol injection system on a 5200-pound-thrust axial-flow-type turbojet engine at sea-level, zero-ram conditions. Results regarding engine performance and operational characteristics are provided.
Date: September 4, 1952
Creator: Boman, David S. & Mallett, William E.
Partner: UNT Libraries Government Documents Department
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