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A Method for the Design of Sweptback Wings Warped to Produce Specified Flight Characteristics at Supersonic Speeds

Description: One of the problems connected with the sweptback wing is the difficulty of controlling the location of the center of pressure and hence the pitching moment. A method is presented for designing a wing to be self-trimming at a given set of flight conditions. Concurrently, the spanwise distribution of load on the wing is made to be approximately elliptical, in an effort to maintain low wing drag.
Date: May 11, 1951
Creator: Tucker, Warren A.
Partner: UNT Libraries Government Documents Department
open access

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 dr… more
Date: July 11, 1951
Creator: Perkins, Porter J. & Kline, Dwight B.
Partner: UNT Libraries Government Documents Department
open access

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
open access

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
open access

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
open access

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
open access

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
open access

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 effe… more
Date: October 11, 1951
Creator: Draper, John W.
Partner: UNT Libraries Government Documents Department
open access

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
open access

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 … more
Date: September 11, 1951
Creator: Jenkins, Joe E.; Buchele, Donald R. & Long, Roger A.
Partner: UNT Libraries Government Documents Department
open access

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
open access

Ceramic-Based Materials for High Temperature Service

Description: The following report provides data that was discovered from a preliminary literature survey that was made to define the utility of the newer refractory ceramics or ceramic-based materials.
Date: June 11, 1951
Creator: Bates, W. A.
Partner: UNT Libraries Government Documents Department
open access

Ion Exchange Experiments with Polonium

Description: The state of polonium in aqueous solutions was investigated by means of ion exchange equilibrium studies. The distribution of the polonium between the solid and liquid phases was determined for solutions of various compositions using both a cation and an anion exchanges. These studies show that in the absence of a complexing agent polonium is hydrolyzed to such a degree that it forms monovalent cations and anions whose charge was not investigated in this study.
Date: May 11, 1951
Creator: Tompkins, Edward R.
Partner: UNT Libraries Government Documents Department
open access

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" (p. 1).
Date: April 11, 1951
Creator: Syvertson, Clarence A. & Savin, Raymond C.
Partner: UNT Libraries Government Documents Department
open access

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 pro… more
Date: July 11, 1951
Creator: Zarovsky, Jacob
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of a Flight Investigation of 1/6-Scale Rocket-Powered Models of the Bell MX-776 to Determine Aileron Rolling Effectiveness and Total Drag

Description: "An experimental investigation of the variation of aileron rolling effectiveness and total drag with Mach number has been made using 1/6-scale rocket-propelled models of the Bell MX-776. Three models having constant-chordwise-thickness full-span aileron at approximate deflections of 2 deg, 5 deg, and 15 deg have been flown. Positive control effectiveness over the Mach number range between approximately 0.5 and 1.2 was obtained from the models and no indication of reversal of effectiveness was e… more
Date: May 11, 1951
Creator: Stevens, Joseph E.
Partner: UNT Libraries Government Documents Department
open access

An analysis of base pressure at supersonic velocities and comparison with experiment

Description: From Introduction: "The primary purpose of the investigation described in the present described in the present report is to formulate a method which is of value for qualitative calculations of base pressure both on airfoils and bodies."
Date: May 11, 1951
Creator: Chapman, Dean R.
Partner: UNT Libraries Government Documents Department
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