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Medical and Health Divisions Quarterly Report October 1947 To Jan. 1948

Description: This quarterly report discusses the following topics: (1) the metabolic properties of plutonium and allied materials; (2) biological studies of radiation effects; (3) biological effects of radiation from external and internal zones; and (4) health chemistry.
Date: February 4, 1948
Creator: Authors, Various
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Two-Dimensional Wind-Tunnel Investigation at High Reynolds Numbers of an NACA 65A006 Airfoil With High-Lift Devices

Description: Report presenting an investigation of an NACA 65A006 airfoil equipped with high-lift devices, including a 0.15-chord drooped-nose flap and a 0.20-chord plain trailing-edge flap. Airfoil section lift, pitching-moment, and drag characteristics obtained at high Reynolds numbers and low Mach numbers with the flaps deflected individually and simultaneously are presented. At Reynolds numbers up to 9.0 x 10(exp 6), the optimum combination of drooped-nose and plain trailing-edge flaps increased the max… more
Date: February 4, 1948
Creator: Nuber, Robert J. & Gottlieb, Stanley M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation at Low Speeds of Swept Wings in Yawing Flow

Description: Memorandum presenting a wind-tunnel investigation conducted to determine the rotary stability characteristics in yawing flow of a series of untapered wings with angles of sweep of -45, 0, 45, and 60 degrees. The results of the yawing-flow tests indicated that the values of the rotary derivatives agreed fairly well with simple sweep theory for a moderate range of lift coefficients.
Date: February 4, 1948
Creator: Goodman, Alex & Feigenbaum, David
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Initial Flight Tests of the NACA FR-2, a High-Velocity Rocket-Propelled Vehicle for Transonic Flutter Research

Description: Report presenting initial flight tests of two simplified flutter vehicles. Test results were in agreement with the results of the freely-falling-body test in that the wing failures in the transonic range occurred at velocities greater than the flutter velocity calculated from the two-dimensional theory.
Date: March 4, 1948
Creator: Barmby, J. G. & Teitelbaum, J. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Boundary-Layer Control by Suction and Several High-Lift Devices on the Longitudinal Aerodynamic Characteristics of a 47.5 Degree Sweptback Wing-Fuselage Combination

Description: "An investigation has been made in the Langley full-scale tunnel of a 47.5 degree sweptback wing-fuselage combination equipped for boundary-layer control by suction. The wing aspect ratio was 3.5, the taper ratio was 0.5, and the airfoil sections normal to the quarter-chord line were NACA 64(sub 1)-A112. The wing configurations tested included the wing with various combinations of extensible leading-edge and split flaps" (p. 1).
Date: November 4, 1948
Creator: Pasamanick, Jerome & Proterra, Anthony J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-speed wind-tunnel tests of a 1/16-scale model of the D-558 research airplane-dynamic pressure and comparison of point and effective downwash at the tail of the D-558-1

Description: Report discussing the point downwash angles and dynamic pressure at the horizontal-tail location of the D-558-1 airplane at a range of Mach numbers and lift coefficients. Results regarding the effective downwash with the tail-on and tail-off configuration, flow direction at the tail, rate of change, and dynamic pressure changes are provided.
Date: November 4, 1948
Creator: Robinson, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of the chordwise pressure distributions over the wing of the XS-1 research airplane in flight

Description: Report presenting measurements of the chordwise pressure distributions over the 8-percent-thick wing of the XS-1 research airplane at a section near the midspan of the left wing. Data are presented for a Mach number range and a normal-force coefficient of about 0.33. Results regarding the upper-surface pressure distribution, lower-surface pressure distributions, and total section loads are provided.
Date: August 4, 1948
Creator: Beeler, De E.; McLaughlin, Milton D. & Clift, Dorothy C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure-sensitive system for gas-temperature control

Description: From Summary: "A thermodynamic relation is derived and simplified for use as a temperature-limiting control equation involving measurement of gas temperature before combustion and gas pressures before and after combustion. For critical flow in the turbine nozzles of gas-turbine engines, the control equation is further simplified to require only measurements upstream of the burner. Hypothetical control systems are discussed to illustrate application of the control equations."
Date: March 4, 1948
Creator: Cesaro, Richard S. & Matz, Norman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine 6: Combustion-Chamber Performance

Description: "An analysis of the performance of the types A, B, and C combustion chambers of the 4000-pound-thrust axial-flow turbojet engine is presented. The data were obtained from investigations of the complete engine over a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.00 to 1.86. The combustion-chamber pressure losses, the effect of the losses on cycle efficiency, and the combustion efficiency are discussed" (p. 1).
Date: August 4, 1948
Creator: Pinkel, I. Irving & Shames, Harold
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements in Flight of the Longitudinal-Stability Characteristics of a Republic YF-84A Airplane (Army Serial No. 45-59488) at High Subsonic Mach Numbers

Description: A brief investigation was made of the longitudinal-stability characteristics of a YF-84A airplane (Army Serial No. 45-79488). The airplane developed a pitching-up tendency at approximately 0.80 Mach number which necessitated large push forces and down-elevator deflections for further increases in speed. In steady turns at 35,000 feet with the center of gravity at 28.3 percent mean aerodynamic chord for normal accelerations up to the maximum test value, the control-force gradients were excessive… more
Date: November 4, 1948
Creator: Turner, Howard L. & Cooper, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Turbine Axial Nozzle-Wheel Clearance on Performance of Mark 25 Torpedo Power Plant

Description: "Investigations were made of the turbine from a Mark 25 torpedo to determine the performance of the unit with three different turbine nozzles at various axial nozzle-wheel clearances. Turbine efficiency with a reamed nondivergent nozzle that uses the axial clearance space for gas expansion was little affected by increasing the axial running clearance from 0.030 to 0.150 inch. Turbine efficiency with cast nozzles that expanded the gas inside the nozzle passage was found to be sensitive to increa… more
Date: February 4, 1948
Creator: Hoyt, Jack W. & Kottas, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine 5 - Analysis of Turbine Performance

Description: "Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was determined in investigations of the complete engine in the NACA Cleveland altitude wind tunnel. Characteristics are presented as functions of the total-pressure ratio across the turbine and of turbine speed and gas flow corrected to sea-level conditions. Three turbine nozzles of different areas were used to determine the area that gave optimum performance" (p. 1).
Date: August 4, 1948
Creator: Krebs, Richard P. & Hensley, Reece V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of First-Stage Blade Design on Performance of Mark 25 Torpedo Power Plant

Description: "The effect of rotor-blade length, inlet angle, and shrouding was investigated with four different nozzles in a single-stage modification of the Mark 25 aerial-torpedo power plant. The results obtained with the five special rotor configurations are compared with those of the standard first-stage rotor with each nozzle. Each nozzle-rotor combination was operated at nominal pressure ratios of 8, 15 (design), and 20 over a range of speeds from 6000 rpm to the design speed of 18,000 rpm" (p. 1).
Date: August 4, 1948
Creator: Schum, Harold J. & Hoyt, Jack W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 317

Description: "An investigation of the spin and recovery characteristics of a scale model of the Grumman XF9F-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the flight loading were determined. The investigation also included spin-recovery-parachute, pilot-escape, and rudder-pedal- . force tests" (p. 1).
Date: February 4, 1948
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Aerodynamic Characteristics of a 3/4-Scale Model of the EX-3 Pine-Cone-Head Pellet in the Langley High-Speed 7-by 10-Foot Wind Tunnel

Description: "An investigation of the EX-3 pine-cone-head pellet was made in the Langley high-speed 7-by 10-foot wind tunnel to determine the static force and moment characteristics at high Mach numbers with the reference center of gravity located at 37.5 percent of the over-all length aft of the nose. For this center-of-gravity location there were no secondary trim positions, and the center-of-pressure position was not appreciably affected by Mach number" (p. 1).
Date: August 4, 1948
Creator: Campbell, George S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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