Serial/Series Title
NACA Research Memorandums
391
NACA Technical Notes
347
Atomic Energy Commission Reports
330
GJBX
187
United States Department of Energy Grand Junction Office Reports
173
United States Geological Survey Reports
139
NACA Technical Memorandums
108
Argonne National Laboratory Reports
100
NACA Technical Reports
97
NACA Wartime Reports
93
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2,246 Matching Results
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Note on the Pressure Distribution Over the Hull of Elongated Airships With Circular Cross Section
"This note, prepared for the National Advisory Committee for Aeronautics, contains the demonstration that the pressure around the circular cross section of an elongated airship, plotted against the diameter of symmetry, can be expected to be represented by a straight line" (p. 1).
Date:
May 1924
Creator:
Munk, Max M.
Object Type:
Report
System:
The UNT Digital Library
High Altitude Flying
This note investigates the effect of high altitude or low atmospheric pressure upon the operation of an engine and the effect of the low pressure and lack of oxygen and of the very low temperatures upon the pilot and upon the performance of the airplane itself.
Date:
May 1924
Creator:
King, Paul B. & Carroll, Thomas
Object Type:
Report
System:
The UNT Digital Library
A method of determining the dimensions and horsepower of an airship for any given performance
A simple and easily applied method of calculating the dimensions and horsepower necessary for an airship to have any given performance is described and illustrated by examples. The method includes means for estimating the changes in performance or in size when modifications or new features are introduced into a design, involving increase or saving in weights, or changes in resistance or propulsive efficiency.
Date:
May 1924
Creator:
Burgess, C. P.
Object Type:
Report
System:
The UNT Digital Library
Investigation of an All-Movable Control Surface at a Mach Number of 6.86 for Possible Flutter
Memorandum presenting results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane. Tests at Mach number 6.86 were made on the scaled model and on several other configurations with lower stiffnesses.
Date:
May 8, 1958
Creator:
Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder
"A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037" (p. 1).
Date:
May 11, 1955
Creator:
Rayle, Warren D.; Smith, Ivan D. & Wentworth, Carl B.
Object Type:
Report
System:
The UNT Digital Library
Some Transonic Aerodynamic Characteristics of a Model Similar to the McDonnell F3H-2N Airplane
Report discussing testing of a model of the McDonnell F3H-2N to determine its pitch-up and buffet boundaries and its longitudinal stability and control data obtainable with the pulse-tail technique. Stability was found to be less at low trim angles of attack than at high trim angles of attack up to a point. The buffet boundary was not obtainable through this testing.
Date:
May 15, 1956
Creator:
Crabill, Norman L. & Jackson, Bruce G.
Object Type:
Report
System:
The UNT Digital Library
High Mach Number, Low-Cowl-Drag, External-Compression Inlet With Subsonic Dump Diffuser
Low cowl drag, external compression inlet with subsonic dump diffuser for high Mach number application.
Date:
May 12, 1958
Creator:
Connors, James F. & Flaherty, Richard J.
Object Type:
Report
System:
The UNT Digital Library
Performance of a 28-Inch Ramjet Utilizing Gaseous Hydrogen at a Mach Number of 3.6, Angles of Attack Up to 12 Degrees, and Pressure Altitudes Up to 110,000 Feet
Memorandum presenting an investigation conducted in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results of the investigation showed that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to a pressure altitude of 110,000 feet with no adverse effect on combustion efficiency.
Date:
May 19, 1958
Creator:
Musial, Norman T.; Ward, James J. & Wasserbauer, Joseph F.
Object Type:
Report
System:
The UNT Digital Library
An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control
Memorandum presenting a study of an acceleration-limiting control on a turbojet engine in order to determine its feasibility as an acceleration control. A proportional-plus-integral type of controller was used in the investigation. Results regarding the one-loop control and two-loop control are provided.
Date:
May 12, 1958
Creator:
Gerus, Theodore F.; Powers, Albert G. & Heppler, Herbert J.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder
Free jet tests of 48 inch diameter ramjet combustor with annular can-type flame holder.
Date:
May 11, 1955
Creator:
Wentworth, Carl B.; Dobson, Wilbur F. & Rayle, Warren D.
Object Type:
Report
System:
The UNT Digital Library
Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen
Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.
Date:
May 9, 1955
Creator:
Jonash, Edmund R.; Smith, Arthur L. & Hlavin, Vincent F.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Afterburner Combustion Screech and Methods of Its Control at High Combustor Pressure Levels
Memorandum presenting an experimental investigation of various methods for the control of afterburner combustion screech at afterburner-inlet total pressures from 4000 to 6400 pounds per square foot absolute. Generally, the range of afterburner fuel-air ratios in which screech occurred and the intensity of screech did not vary appreciably in the range of pressures covered.
Date:
May 14, 1956
Creator:
Trout, Arthur M.; Koffel, William K. & Smolak, George R.
Object Type:
Report
System:
The UNT Digital Library
A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations
Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approach speed, comparison of flight and predicted approach speeds, and comparison of test pilots' and service pilots' approach speed are provided.
Date:
May 8, 1958
Creator:
White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Object Type:
Report
System:
The UNT Digital Library
Effect of Nose Shape and Wing Thickness Ratio on the Drag at Zero Lift of a Missile Having Triangular Wings and Tails
"Free-flight tests have been made to determine the drag at zero lift of several configurations of a missile having triangular wings and tails. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8" (p. 1).
Date:
May 31, 1950
Creator:
Hall, James R. & Sandahl, Carl A.
Object Type:
Report
System:
The UNT Digital Library
Relation of Currently Estimated ANP Performance to Required ANP Performance
Memorandum presenting an investigation of performance estimates of aircraft nuclear propulsion (ANP) systems. This paper includes a relation of current estimated ANP performance to the future requirements that nuclear propulsion systems will be required to meet.
Date:
May 16, 1957
Creator:
Rothrock, Addison M. & Cesaro, Richard S.
Object Type:
Report
System:
The UNT Digital Library
Analysis of a liquid-metal turbine-propeller cycle for propulsion of low-speed nuclear- powered aircraft
From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature."
Date:
May 27, 1952
Creator:
Rom, F. E. & Wachtl, W. W.
Object Type:
Report
System:
The UNT Digital Library
Induction System Characteristics and Engine Surge Occurrence for Two Fighter-Type Airplanes
Memorandum presenting an investigation conducted to measure and compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbojet engines, but with dissimilar inlets. The total-pressure recovery was relatively independent of angle of attack and mass-flow ratio for both airplanes except for a significant decrease in pressure recovery with angle of attack for airplane B at the highest Mach numbers tested.
Date:
May 26, 1958
Creator:
Larson, Terry J.; Thomas, George M. & Bellman, Donald R.
Object Type:
Report
System:
The UNT Digital Library
High-Altitude Performance of J71-A-11 Turbojet Engine and Its Components Using JP-4 and Gaseous-Hydrogen Fuels
Report presenting data to determine the component and overall engine performance up to an altitude limit for the J71-A-11 (600-B36) turbojet engine. Engine operation using JP-4 fuel at Mach number 0.8 was satisfactory up to an altitude of about 60,000 to 65,000 feet, and engine operation with marginal combustion stability was maintained to an altitude of about 80,000 feet. Results regarding the altitude operating limits, component performance, overall engine performance, contribution of individual component losses to overall engine performance losses, exhaust-nozzle-area requirements, and altitude performance at rated engine conditions are provided.
Date:
May 29, 1957
Creator:
Smith, Ivan D. & Saari, Martin J.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59
Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a Convair F-106A airplane. Results regarding pitching moment, ejections, release conditions, and missile trajectory are provided.
Date:
May 20, 1957
Creator:
Lee, John B.
Object Type:
Report
System:
The UNT Digital Library
Spin Tests of a Low-Wing Monoplane to Investigate Scale Effect in the Model Test Range
"Concurrent tests were performed on a 1/16 and a 1/20 scale model (wing spans of 2.64 and 2.11 ft. respectively) of a modern low wing monoplane in the NACA 15 foot free-spinning wind tunnel. Results are presented in the form of charts that afford a direct comparison between the spins of the two models for a number of different conditions. Qualitatively, the same characteristic effects of control disposition, mass distribution, and dimensional modifications were indicated by both models" (p. 1).
Date:
May 1941
Creator:
Donlan, Charles J.
Object Type:
Report
System:
The UNT Digital Library
Propeller Design: Practical Application of the Blade Element Theory 1
"This report is the first of a series of four on propeller design and contains a description of the blade elements or modified Drzewiecke theory as used in the Bureau of Aeronautics, U.S. Navy Department. Blade interference corrections are used which were taken from R.& M. NO. 639 of the British Advisory Committee for Aeronautics. The airfoil characteristics used were obtained from tests of model propellers, not from tests of model wings" (p. 1).
Date:
May 1926
Creator:
Weick, Fred E.
Object Type:
Report
System:
The UNT Digital Library
The Estimation of Airplane Performance From Wind Tunnel Tests on Conventional Airplane Models
Calculations of the magnitude of the correction factors and the range of their variations for wind tunnel models used in making aircraft performance predictions were made for 23 wind tunnel models. Calculated performances were compared with those actually determined for such airplanes as have been built and put through flight test. Except as otherwise noted, all the models have interplane struts and diagonal struts formed to streamwise shape. Wires were omitted in all cases. All the models were about 18 inches in span and were tested in a 4-foot wind tunnel. Results are given in tabular form.
Date:
May 1925
Creator:
Warner, Edward P. & Ober, Shatswell
Object Type:
Report
System:
The UNT Digital Library
Propeller Design: Extension of Test Data on a Family of Model Propellers by Means of the Modified Blade Element Theory 2
This report is the second of a series of four on propeller design, and describes the method used to extend the data obtained from tests on a family of thirteen model propellers to include all propellers of the same form likely to be met in practice. This necessitates the development of a method of propeller analysis which when used to calculate the powers and efficiencies gives results which check the tests throughout their range.
Date:
May 1926
Creator:
Weick, Fred E.
Object Type:
Report
System:
The UNT Digital Library
The comparison of well-known and new wing sections tested in the variable density wind tunnel
Three groups of airfoils have been tested in the variable density wind tunnel. The first group contains three airfoils. The second group is a systematic series of twenty-seven airfoils. The third group consists of several frequently used wing sections.
Date:
May 1925
Creator:
Higgins, George J.
Object Type:
Report
System:
The UNT Digital Library