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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 model of the Convair F-106A airplane with its fin tips retracted at a simulated altitude of 18,670 feet. Successful ejections of the rocket were made at supersonic speeds by applying a combination of ejection velocity and nose-down pitching moment at release.
Date:
May 20, 1957
Creator:
Lee, John B.
System:
The UNT Digital Library
De-Icing and Runback Characteristics of Three Cyclic Electric, External De-Icing Boots Employing Chordwise Shedding
Memorandum presenting an icing investigation conducted to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The overall de-icing characteristics of two of the boots investigated were quite similar. Results regarding boot surface temperatures and general de-icing and runback characteristics are provided.
Date:
May 25, 1953
Creator:
Ruggeri, Robert S.
System:
The UNT Digital Library
Longitudinal Aerodynamic Characteristics of Various Configurations of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01
Report presenting an investigation of a model of the Republic F-105 airplane to determine the static longitudinal aerodynamic characteristics of a revised configuration. The revisions included a lengthened fuselage, a relocated canopy, a contoured fuselage afterbody, a ventral fin, and an enlarged vertical tail. Results regarding the effect of stores, effect of dive-brake flaps, effect of forebody modifications, gun blisters, and duct air bleed, and a comparison of the modified model with the original are provided.
Date:
May 4, 1956
Creator:
Foster, Gerald V.
System:
The UNT Digital Library
An Electric Thrust Meter Suitable for Flight Investigation of Propellers
A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.
Date:
May 9, 1949
Creator:
Perkins, Porter J., Jr. & Millenson, Morton B.
System:
The UNT Digital Library
Fabrication and Properties of Hot-Pressed Molybdenum Disilicide
Report presenting an investigation of hot-pressed molbdenum disilicide bodies produced by industrial processes at a temperature of 2950 degrees and a pressure of 3000 pounds per square inch. Results regarding the short-time tensile strength, stress-rupture data, compression strength, air-corrosion resistance, hardness, coefficient of linear thermal expansion, thermal conductivity, and density are provided.
Date:
May 26, 1950
Creator:
Long, Roger A.
System:
The UNT Digital Library
Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results
"A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling chamber was constructed to measure gas temperature at and beyond the limit of thermocouples. This probe consisted of a subsonic flat-plate orifice for the first restriction and a sonic-flow converging-diverging nozzle for the second restriction. The effect of variation in gas constants on the calibration is examined for common engine-exhaust gases" (p. 1).
Date:
May 21, 1952
Creator:
Scadron, Marvin D.
System:
The UNT Digital Library
Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Tail Attached to a Segment of the Foreshortened Body
"An investigation has been made of a partial-span model of the tail surface designed for use on the Hughes Falcon (MX-904) missile to determine the aerodynamic characteristics of the tail and elevator including elevator hinge moment. Data obtained at Mach numbers of 1.62 and 1.96 in the Langley 9- by 12-inch supersonic blowdown tunnel are presented for the condition where the tail was attached to a segment of the foreshortened body" (p. 1).
Date:
May 4, 1950
Creator:
Conner, D. William & Guy, Lawrence D.
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Aerodynamic Characteristics of a 0.07-Scale Model of the North American MX-770 Missile
Report presenting the results of an investigation at supersonic speeds to determine the aerodynamic characteristics of a model of the North American MX-770 missile at several designated Mach numbers. No analysis is provided. Information about the longitudinal aerodynamic characteristics with trimmer and elevon deflected and lateral aerodynamic characteristics are described.
Date:
May 7, 1952
Creator:
Pfyl, Frank A.
System:
The UNT Digital Library
Experimental Investigation of Extreme Internal Flow Turning at the Cowl Lip of an Axisymetric Inlet at a Mach Number of 2.95
Memorandum presenting an experimental investigation of the pressure-recovery performance of a fixed-geometry, two-cone, two-drag inlet at Mach number 2.95. Low drag was achieved by use of an internally cylindrical cowl with rapid flow turning that was within 4 degrees of the wedge angle for shock detachment. Results regarding the inlet performance and evaluation of inlet performance are provided.
Date:
May 13, 1958
Creator:
Weston, Kenneth C. & Kowalski, Kenneth L.
System:
The UNT Digital Library
Performance at High Temperatures and Pressures of an Annular Turbojet Combustor Having Articulated Liner Walls
Report discussing the performance of an experimental quarter-sector annular combustor at conditions simulating supersonic flight of a cooled-turbine engine, as well as 20 different modification to the design. The final configuration was found to show no structural failures and little or no warping of liner parts after 40 hours of operation.
Date:
May 10, 1957
Creator:
McCafferty, Richard J.; Wear, Jerrold D. & Cook, William P.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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
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.
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.
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.
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.
System:
The UNT Digital Library