Search Results

[Letter from David S. Kennard to his father A. D. Kennard Jr, June 2, 1862]

Description: Letter from David S. Kennard to his father A.D. Kennard Jr. regarding his health recovery from fever. He tells of England sending two ministers and France one to settle peace, although David is not sure as to its authenticity. Travels 16-18 miles a day. Asks for Jennie to write him. He has inclosed some needles for Jennie as well.
Date: 1862-06-02~
Creator: Kennard, David S.
Partner: UNT Libraries Special Collections

[Letter from David Fentress to wife Clara, June 2, 1864]

Description: Letter from David Fentress to his wife Clara regarding the situation at home (the peach orchard, spinning, and a spinning wheel), how to send letters to him, his experience in the army (his need for more clothing, his health, what food the unit is eating, and statistics of his unit), and war news.
Date: June 2, 1864
Creator: Fentress, David
Partner: UNT Libraries Special Collections

[Postcard to Charles B. Moore, June 2, 1899]

Description: This is a document from the Charles B. Moore Collection. In this postcard, Moore is informed of the picnic which has been rescheduled due to the busy harvest season. It details that the picnic will now be held on June 10, 1899 near the Moore family's home.
Date: June 2, 1899
Partner: UNT Libraries Special Collections

[Letter from Mary Moore to Linnet and Birdie, June 2, 1901]

Description: Letter from Mary Moore to Linnet Moore and Birdie McGee. She was glad to hear Linnet made it and was feeling well. She asks Birdie to straighten out Linnet, Linnet hasn't been the same since the measles. She hasn't heard from anyone since Linnet left Mr. Druoy. She then talks about Mr. Druoy. She talks about what they have been eating and the state of the rum. She talks about Linnet's baby. She mentions that Linnet does not tell where she went. She then writes some news of what is happening at home.
Date: June 2, 1901
Creator: Moore, Mary
Partner: UNT Libraries Special Collections

Determination of the theoretical pressure distribution for twenty airfoils

Description: This report gives the theoretical distribution of pressure at lift coefficients of 0, 0.5, 1.0, and 1.5 for 20 airfoils, calculated on the basis of a rigorous potential theory of arbitrary airfoils. It also provides tables from which the characteristics of the airfoils for any angle of attack in 2-dimensional potential flow are readily calculable. The theoretical values of the angles of zero lift, the lift and moment coefficients, and the ideal angles of attack are listed and some comparisons with experiment are indicated. The results presented may be of value in predicting structural loads and also in a correlation of theoretical pressure gradients with profile resistance.
Date: June 2, 1933
Creator: Garrick, I. E.
Partner: UNT Libraries Government Documents Department

Cooling of airplane engines at low air speeds

Description: Report presents the results of a comprehensive experimental study carried out at full scale in the NACA 20-foot wind tunnel, the general purpose of which is to furnish information in regard to the functioning of the power plant and propeller unit under different conditions. This report deals particularly with the problem of the cooling of an airplane engines on the ground. The influence of different nose forms, skirts, flaps, propellers, spinners, and special blowers has been investigated.
Date: June 2, 1936
Creator: Theodorsen, Theodore; Brevoort, M. J. & Stickle, George W.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail with Stub Fuselage and Stub Horizontal Tail

Description: "A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage and stub horizontal tail was tested in the Langley stability tunnel to determine the aerodynamic characteristics of the model, The investigation included a study of the effects of boundary layer thickness, rudder area, and cover-plate alinement on the aerodynamic characteristics. Tuft studies were made in the vicinity of the junction of the vertical and stub horizontal tails" (p. 1).
Date: June 2, 1945
Creator: MacLachlan, Robert
Partner: UNT Libraries Government Documents Department

Blood changes in humans following total body irradiation

Description: A major problem encountered in the Manhattan Project was the protection of workers against damage resulting from acute or chronic exposure to external radiation. The problem of how to detect evidence of damage following exposure to total body radiation led to this study. These studies were conducted between January, 1942 and November, 1945. Three groups of persons were employed in this study. The first group of eight individuals harboring incurable neoplasms which was not extensive enough to influence general health, these patients were treated with 400 KV x-radiation while sitting in a wooden chair, doses were 27, 60, and 120r. Three persons having generalized illnesses chronic in nature were given total body radiation using 200 KV X-rays in multiple exposures totaling 100, 300, and 500r. A third group of normal volunteers from personnel of the Metallurgical Laboratory were treated with 200 KV x-rays in three divided doses totaling 21 r. Changes in peripheral blood in the fourteen individuals is reported. In group 1 the most persistent abnormality noted was a diminution in the number of lymphocytes after completion of the treatment. In group 2 a depression in the lymphocytes was also the most marked single change. In group 3 no alterations in peripheral blood was observed.
Date: June 2, 1947
Creator: Cantril, S.T.; Jacobson, L.O.; Schwartz, S. & Nickson, J.J.
Partner: UNT Libraries Government Documents Department

Analysis of Performance of Jet Engine From Characteristics of Components 2: Interaction of Components as Determined From Engine Operation

Description: "In order to understand the operation and the interaction of jet-engine components during engine operation and to determine how component characteristics may be used to compute engine performance, a method to analyze and to estimate performance of such engines was devised and applied to the study of the characteristics of a research turbojet engine built for this investigation. An attempt was made to correlate turbine performance obtained from engine experiments with that obtained by the simpler procedure of separately calibrating the turbine with cold air as a driving fluid in order to investigate the applicability of component calibration. The system of analysis was also applied to prediction of the engine and component performance with assumed modifications of the burner and bearing characteristics, to prediction of component and engine operation during engine acceleration, and to estimates of the performance of the engine and the components when the exhaust gas was used to drive a power turbine" (p. 1).
Date: June 2, 1948
Creator: Goldstein, Arthur W.; Alpert, Sumner; Beede, William & Kovach, Karl
Partner: UNT Libraries Government Documents Department

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 1: Characteristics of a Plain Wing

Description: Memorandum presenting wind-tunnel tests of a semispan model of an unswept wing of aspect ratio 4 and taper ratio 0.5 at Mach numbers up to 0.94 to determine its aerodynamic characteristics as influenced by Mach number, Reynolds number, and modification of the basic diamond profile by rounding the ridge. Lift, drag, and pitching-moment data are presented for a range of Reynolds and Mach numbers. The results indicated that no severe static-longitudinal-stability problems up to Mach number 0.94.
Date: June 2, 1948
Creator: Johnson, Ben H., Jr.
Partner: UNT Libraries Government Documents Department

An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane

Description: Report presenting wind-tunnel testing of submerged air inlets on the fuselage of a scale model of a typical fighter-type airplane. The results are presented for ramp plan forms with parallel and with diverging walls and show the effect of the duct-entrance location, internal ducting efficiency, and deflectors.
Date: June 2, 1948
Creator: Delany, Noel K.
Partner: UNT Libraries Government Documents Department

Altitude-Test-Chamber Investigation of McDonnell Afterburner on J34 Engine

Description: "An altitude-test-chamber investigation was conducted to determine the operational and performance characteristics of a McDonnell afterburner with a fixed-area exhaust nozzle on a J34 engine. At rated engine speed, the altitude limit, as determined by combustion blow-out, occurred as a band of unstable operation of about 6000-foot altitude in width with minimum altitude limits from 31,000 feet at a simulated flight Mach number of 0.40 to about 45,500 feet at a simulated flight Mach number of 1.00. Considerable difficulty was experienced in attempting to establish or maintain balanced-cycle engine operation at altitudes above 36,000 feet" (p. 1).
Date: June 2, 1949
Creator: Reller, John O. & Dowman, Harry W.
Partner: UNT Libraries Government Documents Department

Comparison of performance of AN-F-58 and AN-F-32 fuels in J33-A-23 turbojet engine

Description: Report presenting an investigation using a 4600 pound-thrust turbojet engine as part of a program to determine the comparative performance of fuels conforming to specifications AN-F-58 and AN-F-32. Results regarding the altitude performance, altitude low-speed blow-out limits, idling limits of fuel-metering control, altitude windmilling starts, carbon-deposition rates, and iron oxide contamination are provided.
Date: June 2, 1949
Creator: Wilsted, H. D. & Armstrong, J. C.
Partner: UNT Libraries Government Documents Department

Flight Investigation of the Jettisonable-Nose Method of Pilot Escape Using Rocket-Propelled Models

Description: Report discussing testing using two rocket-propelled models to test the jettisonable-nose method of pilot escape. The nose was jettisoned successfully on the second attempt and the accelerations produced were found to be within human tolerance. The first test ended with a collision of the nose and wing, indicating that this is a possible risk during power-on flight.
Date: June 2, 1949
Creator: Lundstrom, Reginald R. & O'Kelly, Burke R.
Partner: UNT Libraries Government Documents Department