Resource Type
Collection
Serial/Series Title
NACA Research Memorandums
49
Atomic Energy Commission Reports
14
NACA Technical Notes
11
United States Geological Survey Reports
7
University of California Radiation Laboratory Reports
7
Trace elements investigations report
6
Report (U.S. Atomic Energy Commission)
3
AEC research and development report
2
AECU (Series)
2
E.I. du Pont de Nemours & Company Reports
2
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179 Matching Results
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169 - 179 of
179
A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile
"A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios" (p. 1).
Date:
May 28, 1958
Creator:
Hall, James R. & Garland, Benjamine J.
Object Type:
Report
System:
The UNT Digital Library
Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01
Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Tests occurred at a range of angles of attack and control deflections. Results regarding basic pressure distributions, comparison of experimental and theoretical results, and experimental comparisons are provided.
Date:
May 16, 1958
Creator:
Lord, Douglas R. & Czarnecki, K. R.
Object Type:
Report
System:
The UNT Digital Library
Droplet Impingement and Ingestion by Supersonic Nose Inlet in Subsonic Tunnel Conditions
"The amount of water in cloud droplet form ingested by a full-scale supersonic nose inlet with conical centerbody was measured in the NACA Lewis icing tunnel. Local and total water impingement rates on the cowl and centerbody surfaces were also obtained. All measurements were made with a dye-tracer technique" (p. 1).
Date:
May 1958
Creator:
Gelder, Thomas F.
Object Type:
Report
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.
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
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
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
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
Health Protection in Beryllium Facilities Summary of Ten Years of Experience
From Introduction: "The purpose of this report is to summarize the information gathered during the design and operation of these facilities so that it may be used in providing for the safe handling of beryllium materials."
Date:
May 1, 1958
Creator:
Breslin, A. J. & Harris, W. B.
Object Type:
Report
System:
The UNT Digital Library