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Four in. three jaw type connector suitable for vertical mounting sample for job 11

Description: As authorized by purchase order No. 11-2532 dated March 11, 1949 of the Kellex Corp., the first sample of a 4 inch three jaw type connector for Job 11 was fabricated. The design of the connector was per Crane Co. drawing DR-25126-D except vertical mounting. The materials were per Crane Co. drawing A-24491-C. As instructed in verbal conversation with Dr. D.D. Jacobus and as requested in Mr. J.J. Cuniffe`s letter of May 6, 1949, and Ingersoll-Rand Company`s 1 1/4 inch 534 impact wrench with suitable socket to fit the hexagon head of the operating screw of the 4 inch connector was procured on loan to make some preliminary tests. Engineering drawings are listed in a second report on the data base.
Date: July 8, 1949
Creator: Grubbe, A.C.
Partner: UNT Libraries Government Documents Department

Preparation of bismuth powder

Description: The principal object of this report is to record results of tests made on equipment installed in Room 232 of ``T`` Building and used to prepare bismuth powder for process operations. Another object is to establish the most favorable operating conditions for the equipment and to prepare operating instructions therefor.
Date: March 8, 1949
Creator: Cox, G.C.; Grasso, J.A.; Hale, D. & Wright, J.W.
Partner: UNT Libraries Government Documents Department

Determination of the purity of polonium by means of the vacuum balance (Ad Interim Report)

Description: The assay technique is discussed in detail. The results of three purity determinations are: 94.92 per cent, 100.50 per cent, and 106.9 per cent. The errors present in each determination are stated. The inherent dangers in the present procedure are pointed out, and an improved method is outlined.
Date: March 8, 1949
Creator: Haring, M.M.
Partner: UNT Libraries Government Documents Department

On the Use of Residue Theory for Treating the Subsonic Flow of a Compressible Fluid

Description: "A new mathematical technique, due to Milne-Thomson, is used to obtain an improved form of the method of Poggi for calculating the effect of compressibility on the subsonic flow past an obstacle. By means of this new method, the difficult surface integrals of the original Poggi method can be replaced by line integrals. These line integrals are then solved by the use of residue theory. In this way an equation is obtained giving the second-order effect of compressibility on the velocity of the fluid" (p. 39).
Date: September 8, 1941
Creator: Kaplan, Carl
Partner: UNT Libraries Government Documents Department

Flight and Test-Stand Investigation of High-Performance Fuels in Pratt & Whitney R-1830-94 Engines 4: Comparison of Cooling Characteristics of Flight and Test-Stand Engines

Description: "The cooling characteristics of three R-1830-94 engines, two of which were mounted in a test stand and the other in a B-24D airplane, were investigated and the results were compared. The flight tests were made at a pressure altitude of 7000 feet; the test-stand runs were made at ground-level atmospheric conditions. Three cooling runs were made for each engine: variable cooling-air pressure drop, variable carburetor-air flow, and variable fuel-air ratio" (p. 1).
Date: October 8, 1946
Creator: Dandois, Marcel & Werner, Milton
Partner: UNT Libraries Government Documents Department

Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers

Description: Field measurements were made on a fighter airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of fluctuating tail loads in accelerated stalls.
Date: May 8, 1944
Creator: Flight Research Maneuvers Section
Partner: UNT Libraries Government Documents Department

Notes on Geared Tabs at Supersonic Speeds

Description: Memorandum presenting an analysis of the two-dimensional, geared, trailing-edge flap-tab combination at supersonic speeds to determine if the combination could be used to reduce the hinge moments to extremely small values while retaining a large part of the lift effectiveness of a plain flap with the same ratio of flap chord to wing chord.
Date: July 8, 1948
Creator: Tucker, Warren A.
Partner: UNT Libraries Government Documents Department

Estimated transonic flying qualities of a tailless airplane based on a model investigation

Description: Report presenting an analysis of the estimated flying qualities of a tailless airplane with the wing quarter-chord line swept back 35 degrees in a range of Mach numbers based on tests of a model of the airplane in the 7- by 10-foot tunnel. Results regarding performance, longitudinal stability and control, and lateral stability and control are provided.
Date: June 8, 1949
Creator: Donlan, Charles J. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

Newsmap. Monday, March 8, 1943 : week of February 26 to March 5, 182nd week of the war, 64th week of U.S. participation

Description: Front: Text describes action on various war fronts: New Guinea -- Solomons -- Submarines -- Tunisia -- Russia -- Western Europe. Large world map is keyed to text and illustrates time zones around the world. Inset maps show Tunisia -- Moscow/Leningrad region. Includes photographs: Attack: A-20 Boston bombers in central Tunisia -- Jeep rider: South Sea islander hitches a ride on an Army jeep -- Loudspeaker on Guadalcanal -- Jap 75 on New Guinea. Back: German Navy uniforms and insignia. Includes color illustrations of uniforms and components, and insignia with informational text. Chart of German pronunciation of military ranks with equivalent ratings in U.S. and German navies.
Date: March 8, 1943
Creator: [United States.] Army Orientation Course.
Partner: UNT Libraries Government Documents Department

Tank Tests of a Powered Model of a Compression Plane, NACA Model 171A-2

Description: "The compression plane is intended for operation on or close to the surface of the water, and has a hull with a concave bottom which forms the upper surface of a tunnel into which air is forced under pressure to support part of the load. The results of the tests made in Langley tank no. 1 include values of the horizontal forces, trimming moment, and static pressure in the tunnel for a wide range of loads and speeds and two power conditions, and are presented in the form of curves against speed with load as a parameter. The results are scaled up to 10 times the model size for three conditions at which the model is self-propelled at a steady speed" (p. 1).
Date: July 8, 1948
Creator: Mottard, Elmo J. & Ruggles, Robert D.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-3 Airplane

Description: "Because previous work has indicated that jettisonable nose sections of airplanes may be inherently unstable, and thus may cause dangerous centripetal accelerations on a pilot after jettisoning during high-speed flight, an investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the behavior in descent of a model of the jettisonable nose section of the Douglas X-3 airplane. The effects of varying the center-of-gravity position, of attaching fins of various sizes, and of installing a stabilizing parachute were investigated. In the investigation the model descended with its front and trimmed 36 deg above the horizontal and rotated about a vertical wind axis while rolling about its longitudinal body axis" (p. 1).
Date: December 8, 1946
Creator: Scher, Stanley H.
Partner: UNT Libraries Government Documents Department

An empirical criterion for fin stabilizing jettisonable nose sections of airplanes

Description: "Investigations in the Langley 20-foot free-spinning tunnel of models of five jettisonable nose sections have shown that the airplane nose sections are inherently unstable but can be stabilized by the addition of suitable fins. An empirical criterion has been developed which indicates the fin area required for stabilizing an airplane jettisonable nose section" (p. 1).
Date: December 8, 1949
Creator: Scher, Stanley H.
Partner: UNT Libraries Government Documents Department

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 5: Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane

Description: Memorandum presenting wind-tunnel tests of a semispan model of a hypothetical supersonic airplane to determine the static longitudinal stability and control characteristics of the airplane throughout the range of subsonic Mach numbers up to 0.95. The model had a long slender fuselage and a wing and horizontal tail of aspect ratio 4 and taper ratio 0.5. Results regarding the force and moment characteristics, wing wake and effective downwash at the horizontal tail, effects of compressibility, and longitudinal characterisitcs with the flaps deflected are provided.
Date: December 8, 1949
Creator: Johnson, Ben H., Jr. & Rollins, Francis W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of effect of interference on lateral-stability characteristics of four NACA 23012 wings, an elliptical and a circular fuselage and vertical fins

Description: Report presents the results of a wind-tunnel investigation of the effect of wing-fuselage interference on lateral-stability characteristics made in the NACA 7 by 10-foot wind tunnel on four fuselages and two fins, representing high-wing, low-wing, and midwing monoplanes. The fuselages are of circular and elliptical cross section. The wings have rounded tips and, in plan form, one is rectangular and the three are tapered 3:1 with various amounts of sweep. The rate of change in the coefficients of rolling moment, yawing moment, and lateral force with angle of yaw is given in a form to show the increment caused by wing-fuselage interference for the model with no fin and the effect of wing-fuselage interference on fin effectiveness. Results for the fuselage-fin combination and the wing tested alone are also given.
Date: August 8, 1940
Creator: House, Rufus O. & Wallace, Arthur R.
Partner: UNT Libraries Government Documents Department

Smooth-Water Landing Stability and Rough-Water Landing and Take-Off Behavior of a 1/13-Scale Model of the Consolidated Vultee Skate 7 Seaplane, TED No. NACA DE 338

Description: A model of the Consolidated Vultee Aircraft Corporation Skate 7 seaplane was tested in Langley tank no. 2. Presented without discussion in this paper are landing stability in smooth water, maximum normal accelerations occurring during rough-water landings, and take-off behavior in waves.
Date: September 8, 1949
Creator: McKann, Robert F.; Coffee, Claude W. & Arabian, Donald D.
Partner: UNT Libraries Government Documents Department