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A specially constructed metallograph for use at elevated temperatures

Description: "A metallographic microscope was developed with provision for heating a specimen to 1800 F in protective atmospheres, that is, vacuum or gas. A special objective was constructed of reflecting elements with an unusually long working distance (7/16 in.) and a high numerical aperture (0.5). Changes in specimen microstructure were observed and recorded on 35-millimeter motion-picture film. The resulting pictures were projected as motion pictures and individual frames were cut and enlargements made for close observation" (p. 1).
Date: September 11, 1951
Creator: Jenkins, Joe E.; Buchele, Donald R. & Long, Roger A.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of a supersonic scoop inlet derived from a conical-spike nose inlet

Description: Report presenting an investigation on a supersonic scoop inlet derived from a conical spike nose inlet at Mach numbers of 1.3, 1.6, and 1.9. The pressure recoveries of both inlets were similar. Results regarding the pressure drag, amounts of boundary-layer suction, and comparison of the inlets under several conditions are provided.
Date: September 11, 1951
Creator: Wittliff, Charles E. & Byrne, Robert W.
Partner: UNT Libraries Government Documents Department

The effects at transonic speeds of thickening the trailing edge of a wing with a 4-percent-thick circular-arc airfoil

Description: Report presenting an investigation of the effects of a systematic variation of trailing-edge thickness of a symmetrical, circular-arc airfoil on the aerodynamic force, moment, base-pressure, and wake fluctuations using the transonic-bump testing technique. Results regarding the effects of a systematic variation of the trailing-edge thickness, investigation of a boattailed trailing edge, and wake fluctuation characteristics are provided.
Date: December 11, 1951
Creator: Cleary, Joseph W. & Stevens, George L.
Partner: UNT Libraries Government Documents Department

System Analyses and Autopilot Design for Automatic Roll Stabilization of a Supersonic Pilotless Aircraft

Description: Memorandum presenting system analyses and autopilot design procedure for a supersonic pilotless aircraft with twin jet engines. The autopilots investigated were a gyro-actuated control, a gyro-actuated control with a rate-sensing device, and an electronic-hydraulic autopilot. Results regarding the airframe and gyro-actuated control system; airframe, gyro-actuated control, and rate servo; airframe and electronic-hydraulic autopilot; and contribution of method of analysis to system design are provided.
Date: July 11, 1951
Creator: Zarovsky, Jacob
Partner: UNT Libraries Government Documents Department

An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane: TED No. NACA DE 344

Description: "At the request of the Bureau of Aeronautics, Navy Department, an investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the McDonnell XF3H-1 airplane has been made in the Langley free-flight tunnel. Flight tests of the model in the clean and in the slats-and-flaps-extended conditions were made over a lift-coefficient range from about 0.5 through the stall. Only low-altitude conditions were simulated and no attempt was made to determine the effect on the stability characteristics of freeing the controls" (p. 1).
Date: October 11, 1951
Creator: Draper, John W.
Partner: UNT Libraries Government Documents Department

The Design of Variable Mach Number Asymmetric Super-Sonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines

Description: Two theoretical procedures are developed for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One procedure is applicable at Mach numbers less than approximately 3. This approach yields, without iteration, a nozzle for which the calculated exit flow is uniform at two Mach numbers and, with proper design, is nearly uniform at Mach numbers between, slightly above, and slightly below these two. The use of an inclined and curved sonic line is an essential feature of this approach, The second procedure requires iteration and is used far designs at Mach numbers exceeding 3. Although it is not a necessary feature, an inclined and curved sonic line is also used in this procedure. In both approaches the flow field dawn stream of the sonic line is determined using the method of characteristics.
Date: April 11, 1951
Creator: Syvertson, Clarence A. & Savin, Raymond C.
Partner: UNT Libraries Government Documents Department

Contributions of wing, tail, and fuselage to the aerodynamic characteristics of a semispan model of a supersonic airplane configuration at transonic speeds from tests by the NACA wing-flow method

Description: Report presenting an investigation using the NACA wing-flow method at transonic speeds to determine the contributions of wing, tail, and fuselage to the aerodynamic characteristics of a semispan airplane model with a long slender fuselage and straight wing and tail of low aspect ratio with faired symmetrical double-wedge airfoil sections 4.6 percent of the chord in thickness. Results regarding the drag, pitching moment, downwash, and lift are provided.
Date: July 11, 1951
Creator: Silsby, Norman S. & McKay, James M.
Partner: UNT Libraries Government Documents Department

Flight investigation of the effect of sideslip on the pressure at the static orifices of the Boeing B-29 airplane

Description: Report discussing testing to determine the sensitivity to sideslip of the static-pressure orifices of the Boeing B-29. The purpose was to determine the errors in indicated altitude and vertical velocity that occur when an airplane experiences oscillations in sideslip on a bombing run. The sensitivity of the orifices to sideslip was determined by measurements of pressure and sideslip angle during constant-amplitude oscillations in sideslip.
Date: April 11, 1951
Creator: Chilton, Robert G. & Brown, B. Porter
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at Mach numbers of 1.5 and 2.0 of a canard missile configuration

Description: Report presenting wind-tunnel testing at Mach numbers of 1.5 and 2.0 to investigate the force, moment, and control characteristics of a canard missile configuration and its components in pitch and sideslip. The missile had small all-movable horizontal control surfaces at the nose and a cruciform wing at the rear, all of trapezoidal plan form. Trailing-edge flaps on the vertical fins were provided to supply directional control.
Date: May 11, 1951
Creator: Spahr, J. Richard & Robinson, Robert A.
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of the Control of a Gas-Turbine Engine for a Helicopter

Description: An analog investigation of the power plant for a gas-turbine powered helicopter indicates that currently proposed turbine-propeller engine controls are satisfactory for helicopter application. Power increases from one-half to full rated at altitudes from sea level to 15,000 feet could be made in less than 4 seconds with either the rotor or propellers absorbing the engine power.
Date: September 11, 1951
Creator: Krebs, Richard P.
Partner: UNT Libraries Government Documents Department

Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content

Description: Flight icing-rate data obtained in a dense and. abnormally deep supercooled stratiform cloud system indicated the existence of liquid-water contents generally exceeding values in amount and extent previously reported over the midwestern sections of the United States. Additional information obtained during descent through a part of the cloud system indicated liquid-water contents that significantly exceeded theoretical values, especially near the middle of the cloud layer.. The growth of cloud droplets to sizes that resulted in sedimentation from the upper portions of the cloud is considered to be a possible cause of the high water contents near the center of the cloud layer. Flight measurements of the vertical temperature distribution in the cloud layer indicated a rate of change of temperature with altitude exceeding that of the moist adiabatic lapse rate. This excessive rate of change is considered to have contributed to the severity of the condition.
Date: July 11, 1951
Creator: Perkins, Porter J. & Kline, Dwight B.
Partner: UNT Libraries Government Documents Department

An investigation of the low-speed stability and control characteristics of a 1/10-scale model of the McDonnell XF3H-1 airplane

Description: Report presenting an investigation of the low-speed, power-off stability and control characteristics of a model of the McDonnell XF3H-1 airplane. Flight testing occurred in the clean and slat- and flaps-extended conditions over a range of lift coefficients.
Date: October 11, 1951
Creator: Draper, John W.
Partner: UNT Libraries Government Documents Department