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Investigation of Sandwich Construction Under Lateral and Axial Loads

Description: Note presenting testing under combined axial load and lateral pressure on 12 bonded sandwich panels with simply supported loaded edges and free unloaded edges. The maximum load and mode of failure were observed for all the panels. Lateral deflections and axial strains were also measured.
Date: December 1953
Creator: Kroll, Wilhelmina D.; Mordfin, Leonard & Garland, William A.
open access

An investigation of some factors affecting the drag of relatively large nonlifting bodies of revolution in a slotted transonic wind tunnel

Description: Report presenting an investigation to study some factors affecting the drag of relatively large nonlifting bodies of revolution at transonic speeds in the 8-foot transonic tunnel. Drag and surface pressure measurements were made for two geometrically similar bodies of revolution of 8-inch and 4-inch maximum diameter at zero angle of attack through a range of Mach numbers.
Date: January 15, 1953
Creator: Pendley, Robert E. & Bryan, Carroll R.
open access

Investigation of Spoiler Ailerons with and Without a Gap Behind the Spoiler on a 45 Degree Sweptback Wing-Fuselage Combination at Mach Numbers from 0.60 to 1.03

Description: Report presenting an investigation conducted with several 73-percent semispan inboard spoiler ailerons, projecting 4 percent of the local wing chord from the wing surface, and located at the 70-percent chord line of a 45 degree sweptback wing-fuselage combination. Results regarding the effect of upper-surface spoilers on basic model characteristics, effect of gap on spoiler characteristics, comparison of upper- and lower-surface spoiler characteristics, comparison of upper-surface spoiler with … more
Date: September 14, 1953
Creator: West, F. E., Jr.; Solomon, William & Brummal, Edward M.
open access

Investigation of Spoilers at a Mach Number of 1.93 to Determine the Effects of Height and Chordwise Location on the Section Aerodynamic Characteristics of a Two-Dimensional Wing

Description: Report presenting an investigation of spoilers at a Mach number of 1.93 to determine the effects of height and chordwise location on the section pressure distributions and section aerodynamic characteristics of a two-dimensional, 6-percent-thick, symmetrical wing. Spoilers of 3-, 5-, and 7-percent-chord height were tested at three chordwise locations. Results regarding pressure distributions, aerodynamic characteristics, and shock boundary-layer interactions are provided.
Date: March 25, 1953
Creator: Mueller, James N.
open access

Investigation of the Attenuation of Plane Shock Waves Moving Over Very Rough Surfaces

Description: "Experimental measurements of the attenuation of plane shock waves moving over rough walls have been made in a shock tube. Measurements of the boundary-layer characteristics, including thickness and velocity distribution behind the shock, have also been made with the aid of new cal techniques which provide direct information on the local boundary-layer conditions at the rough walls. Measurements of shock speed and shock pressure ratio are presented for both smooth-wall and rough-wall flow over … more
Date: June 16, 1953
Creator: Huber, Paul W.; McFarland, Donald R. & Levine, Philip
open access

Investigation of the Behavior of NaOH-UO₃ Slurries in Small Flow Loops

Description: From introduction: "This report presents the results of an experimental program to evaluate engineering problems which might be encountered when circulating NaOH-UO3 slurry through a thermal cycle."
Date: September 15, 1953
Creator: Stang, J. H.; Lagedrost, J. F.; Simons, E. M. & Dayton, R. W.
open access

Investigation of the Effect of Chordwise Positioning and Shape of an Underwing Nacelle on the High-Speed Aerodynamic Characteristics of a 45 Degree Sweptback Tapered-in-Thickness-Ratio Wing of Aspect Ratio 6

Description: Report presenting an investigation of three different nacelles in an underwing position at the 0.46 semispan station of a 45 degree sweptback wing at three chordwise positions for a range of Mach numbers. The nacelle profiles were an ogive cylinder, an NACA 65A-series airfoil, and an NACA 0-series airfoil (reversed). Results regarding drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.
Date: January 22, 1953
Creator: Silvers, H. Norman & King, Thomas J., Jr.
open access

Investigation of the Effect of Spanwise Positioning of a Vertically Symmetric Ogive-Cylinder Nacelle on the High-Speed Aerodynamic Characteristics of a 45 Degree Sweptback Tapered-in-Thickness Wing of Aspect Ratio 6 With and Without a Fuselage

Description: Report presenting an investigation of an ogive-cylinder nacelle in various spanwise locations in a vertically symmetric position on a small-size 45 degree sweptback wing of aspect ratio 6 with and without a fuselage. Results regarding the drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.
Date: October 7, 1953
Creator: Silvers, H. Norman & King, Thomas J., Jr.
open access

An investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61

Description: Report presents the results of an investigation conducted to determine the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA rm-10 without fins) at Mach number of 1.61 and over a Reynolds number range from 2.5 x 10(6) to 35 x 10(6). The maximum cooling of the model used in these tests corresponded to a temperature ratio (ratio of model-surface temperature to free-stream temperature) of 1.12, a value somewhat higher than the theoretical value required … more
Date: February 16, 1953
Creator: Czarnecki, K. R. & Sinclair, Archibald R.
open access

Investigation of the Effects of Leading-Edge Flaps on the Aerodynamic Characteristics in Pitch at Mach Numbers From 0.40 to 0.93 of a Wing-Fuselage Configuration With a 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Report presenting an investigation to determine the effects of a number of leading-edge flaps on the aerodynamic characteristics in pitch of a wing-fuselage configuration with a 45 degree sweptback wing. All of the flaps were found to reduce the drag in the medium lift range , but there were no significantly large effects on the lift characteristics for any of the arrangements studied.
Date: August 20, 1953
Creator: Spreemann, Kenneth P. & Alford, William J., Jr.
open access

Investigation of the Effects of Propeller Operation on the Low-Speed Stability and Control Characteristics of a 1/6-Scale Model of a Revised Configuration of the Republic XF-84H Airplane

Description: "An investigation was made to determine the static longitudinal and lateral stability and control characteristics of a 1/6-scale model of the revised Republic XF-84H airplane with and without the propeller operating. The model had a 40 degree swept wing of aspect ratio 3.45 and was equipped with a thin, three-blade supersonic-type propeller. Modifications incorporated in the revised model included a raised horizontal tail, increased rudder size, wing fences at 65 percent semispan, and a modifie… more
Date: September 22, 1953
Creator: Sleeman, William C., Jr.
open access

Investigation of the Effects of Wing and Tail Modifications on the Low-Speed Stability Characteristics of a Model Having a Thin 40 Degree Swept Wing of Aspect Ratio 3.5

Description: Report presenting an investigation of the effects of wing and tail modifications on the low-speed stability characteristics of a model with thin 40 degree swept wings of aspect ratio 3.5. The main purpose was to improve some of the undesirable longitudinal stability characteristics observed in flight of several airplanes with similar wing geometry. The use of flaps, the position of the horizontal tail, and the use of chord extensions are all explored as possible solutions.
Date: April 28, 1953
Creator: Weil, Joseph; Sleeman, William C., Jr. & Byrnes, Andrew L., Jr.
open access

An Investigation of the Experimental Aerodynamic Loading on a Model Helicopter Rotor Blade

Description: Note presenting pressure distributions measured on a model helicopter rotor blade under hovering and simulated forward-flight conditions. Pressure were recorded at advance ratios of 0.10, 0.22, 0.30, 0.40, and 0.50 for a zero-offset flapping-hinge rotor and at 0.10, 0.22, 0.30, 0.45, 0.60, 0.80, and 1.0 for a lifting rotor with a flapping-hinge offset of 13 percent.
Date: May 1953
Creator: Meyer, John R., Jr. & Falabella, Gaetano, Jr.
open access

Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the Convair YF-102 Airplane in the Langley Free-Flight Tunnel

Description: From Summary: "An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the Convair YF-102 airplane has been made in the Langley free-flight tunnel. The model was flown over a lift-coefficient range from 0.5 to the stall in its basic configuration and with several modifications involving leading-edge slats and increases in vertical-tail size. Only relatively low-altitude conditions were simulated and no attempt was made to determine the effect … more
Date: November 18, 1953
Creator: Johnson, Joseph L., Jr. & Boisseau, Peter C.
open access

Investigation of the NACA 1.167-(0)(03)-058 and NACA 1.167-(0)(05)-058 Three-Blade Propellers at Forward Mach Numbers to 0.92 Including Effects of Thrust-Axis Inclination

Description: Report presenting an investigation to determine the aerodynamic characteristics of two three-blade propellers over a range of blade angles and Mach numbers. The thick-blade propeller was more adversely affected by compressibility than the thin-blade propeller, and the maximum efficiency of the thin-blade propeller was higher than the thick-blade propeller.
Date: August 31, 1953
Creator: Demele, Fred A. & Otey, William R.
open access

Investigation of the Spinning and Tumbling Characteristics of a 1/25-Scale Model of the Lockheed XFV-1 Airplane in the Langley 20-Foot Free-Spinning Tunnel

Description: "An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/23-scale model of the Lockheed XFV-1 airplane to determine the effects of control setting and movement upon the erect-spin and recovery characteristics for a range of airplane loading conditions. A windmilling propeller was simulated on the model for some of the tests. The investigation included determination of the size of tail parachute required for emergency recovery from demonstration spins" (p. 1).
Date: August 21, 1953
Creator: Lee, Henry A.
open access

Investigation of the Statistical Nature of the Fatigue of Metals

Description: Note presenting an investigation which utilized the statistical methods developed in previous research to study the scatter found in aluminum alloys and the effect of the morphology of the carbide phase on the scatter in a eutectoid steel. The scatter in fatigue life for 24S and 75S aluminum was found to be comparable with that reported previously for steel.
Date: September 1953
Creator: Dieter, G. E. & Mehl, R. F.
open access

Investigation of the Use of a Stick Force Proportional to Pitching Acceleration for Normal-Acceleration Warning

Description: Report presenting an investigation of the feasibility of modifying the transient portion of the stick force in abrupt maneuvers in order to eliminate inadvertent normal-acceleration overshoots. The modification consists of additional stick force proportional to a quantity which leads the normal acceleration. The characteristics introduced by the inclusion of the force were considered to be very desirable by pilots.
Date: August 14, 1953
Creator: Abramovitz, Marvin; Schmidt, Stanley F. & Van Dyke, Rudolph D., Jr.
open access

An investigation of three NACA 1-series nose inlets at subsonic and transonic speeds

Description: Report presenting an investigation of three NACA 1-series nose inlets at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements and schileren photographs were obtained at zero angle of attack through a range of Mach numbers and mass-flow-ratios. Results regarding tunnel boundary interference, surface pressure distribution, external drag, and pressure recovery are provided.
Date: January 7, 1953
Creator: Pendley, Robert E.; Milillo, Joseph R. & Fleming, Frank F.
open access

Investigation of translating-spike supersonic inlet as means of mass-flow control at Mach numbers of 1.5, 1.8, and 2.0

Description: Report presenting an investigation in the supersonic wind tunnel on a 50 degree conical-spike inlet at three Mach numbers over a range of angles of attack. The additive-drag penalty associated with inlet mass-flow spillage was significantly reduced by using a translating-spike inlet rather than a fixed-geometry inlet.
Date: October 29, 1953
Creator: Gorton, Gerald C.
open access

Investigation of Turbines for Driving Supersonic Compressors 3: First Configuration With Four Nozzle Settings and One Nozzle Modification

Description: A turbine designed to power a supersonic compressor was investigated with four nozzle settings and one nozzle modification to determine the effect on turbine performance. With the correct ratio of nozzle throat area to rotor effective throat area, the design specific work was obtained near the peak efficiency. From the results of the investigation it was concluded that the convex in sweep of the rotor inner wall and high degree of blade taper caused the turbine configuration to have two aerodyn… more
Date: March 10, 1953
Creator: Stewart, Warner L.; Whitney, Warren J. & Monroe, Daniel E.
open access

Investigation of Turbines for Driving Supersonic Compressors 4: Design and Performance of Second Configuration Including Study of Three-Dimensional Flow Effects

Description: Report presenting the design and experimental performance of a turbine configuration designed to drive a high-speed, high specific-weight-flow supersonic compressor. Results regarding two configurations and their work output, design weight flow, and blade loading are provided.
Date: May 18, 1953
Creator: Whitney, Warren J.; Stewart, Warner L. & Schum, Harold J.
open access

Investigation of Turbines for Driving Supersonic Compressors 5: Design and Performance of Third Configuration With Nontwisted Rotor Blades

Description: Report presenting the design and performance of a turbine with nontwisted rotor blades designed to drive a high-speed, high-specific-mass-flow supersonic compressor. Results regarding turbine performance, entrance Mach number, radial temperature surveys, and loading are provided.
Date: September 4, 1953
Creator: Whitney, Warren J.; Stewart, Warner L. & Monroe, Daniel E.
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