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open access

Preliminary Investigation of the Effects of Rectangular Vortex Generators on the Performance of a Short 1.9:1 Straight-Wall Annular Diffuser

Description: Report presenting a preliminary investigation in a duct system with fully developed pipe flow to determine the effectiveness of vortex generators in improving the performance of a 21-inch-diameter straight-outer-wall annual diffuser with an overall equivalent conical expansion angle of 15 degrees and a and 1.9:1 area ratio. The vortex generators used were rectangular noncambered airfoils that varied in chord, span, angle of attack, number, and location. Results regarding a diffuser with no vort… more
Date: October 10, 1951
Creator: Wood, Charles C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Damping in Roll of Straight and 45 Degree Swept Wings of Various Taper Ratios Determined at High Subsonic, Transonic, and Supersonic Speeds With Rocket-Powered Models

Description: Report presenting rocket-powered flight testing to determine the damping in roll of several wings of 0 degree and 45 degree quarter-chord-line sweep with various taper ratios for a range of Mach numbers. Damping in roll decreased with decreasing taper ratio at roughly the same rate for swept and unswept wings and also decreased by sweeping the quarter-chord line. The experimental results were also consistently lower than what was predicted by theory.
Date: October 10, 1951
Creator: Sanders, E. Claude, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Graphic Analysis of American and British Axial-Flow Turbojet Engine Performance Trends (Current and Future)

Description: From Summary: "This report presents a compilation of static sea-level data on existing or designed American and British axial-flow turbojet engines in terms of basic engine parameters such as thrust and air flow. In the data presented, changes in the over-U engine performance with time are examined as well as the relation of the various engine parameters to each other."
Date: December 10, 1951
Creator: Cesaro, Richard S. & Lazar, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of the Longitudinal Stability and Control of a Rocket-Propelled Missile Model Having Cruciform, Triangular, Interdigitated Wings and Tails

Description: Report presenting flight testing of a missile model with cruciform, triangular, interdigitated wings and tails to determine the longitudinal stability and control characteristics over a range of Mach numbers. Results regarding static stability and damping, control effectiveness, and control hinge moments are provided.
Date: July 10, 1951
Creator: Sandahl, Carl A. & Hall, James R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Over-all performance of J35-A-23 two-stage turbine

Description: Over-all performance of a two-stage turbine from a J35-A-23 turbojet engine is presented. Limiting blade loading restricted work output to approximately 95 percent of the design value. The brake internal efficiency at design operating conditions was approximately 0.75. maximum brake internal efficiency at off-design conditions was between 0.81 and 0.82.
Date: December 10, 1951
Creator: Rebeske, John J., Jr.; Berkey, William E. & Forrette, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Investigation of an Automatic Control System With Primary Sensitivity to Normal Accelerations as Used to Control a Supersonic Canard Missile Configuration

Description: Report presenting a theoretical investigation of an automatic control system with primary sensitivity to normal accelerations as used to control a specific supersonic canard missile. The control system is made up of an integrating servomotor that receives a signal from an accelerometer that is sensitive to normal accelerations of the airframe that it is controlling. The acceleration control system appears to work well for obtaining longitudinal control, but works best when combined with a homin… more
Date: July 10, 1951
Creator: Seaberg, Ernest C. & Smith, Earl F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Investigation of the Effects of Single Slotted and Double Slotted Flaps on a 47.7 Degree Sweptback-Wing: Fuselage Combination at a Reynolds Number of 6.0 X 10(Exp 6)

Description: Report presenting an investigation to determine the effects of partial-span single slotted and double slotted flaps at various deflections on the longitudinal aerodynamic characteristics of a sweptback-wing-fuselage combination. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and effect of flap-bracket alignment are provided.
Date: September 10, 1951
Creator: Mollenberg, Ernst F. & Spooner, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Compilation and review of effects of design parameters on ditching characteristics

Description: From Summary: "This paper supplements a previously published one on the effect of design parameters on ditching characteristics. The supplementary information is based on additional data available from both model tests and full-scale experience. In addition, summary tables compiled from the NACA model ditching investigations are presented."
Date: July 10, 1951
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of altitude starting and acceleration characteristics of J47 turbojet engine

Description: An investigation was conducted on an axial-flow-compressor type turbojet engine in the NACA Lewis altitude wind tunnel to determine the operational characteristics of several ignition systems, cross-fire tube configurations and fuel systems over a range of simulated flight conditions. The opposite-polarity-type spark plug provided the most satisfactory ignition. Increasing the cross-fire-tube diameter improved intercombustor flame propagation. At high windmilling speeds, accelerations to approx… more
Date: January 10, 1951
Creator: Golladay, Richard L. & Bloomer, Harry E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of spanwise thickness variation on the aerodynamic characteristics of 35 degree and 45 degree sweptback wings of aspect ratio 6: transonic-bump method

Description: Report presenting an aerodynamic investigation in the high-speed 7- by 10-foot tunnel to determine the effects of taper-in-thickness on the aerodynamic characteristics of wings with 35 and 45 degrees of sweepback, aspect ratio 6, and taper ratio 0.60. The wings were tested over a range of Mach numbers.
Date: July 10, 1951
Creator: Morrison, William D., Jr. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The transonic characteristics of 17 rectangular, symmetrical wing models of varying aspect ratio and thickness

Description: Report presenting an investigation to determine the aerodynamic characteristics of a series of thin, rectangular wings in the 16-foot high-speed wind tunnel using the transonic bump technique over a range of Mach and Reynolds numbers. Lift, drag, and pitching moment characteristics are presented for wings of 4 different aspect ratios and NACA 63A0XX sections and with 5 different thickness-to-chord ratios.
Date: May 10, 1951
Creator: Nelson, Warren H. & McDevitt, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical performance of lithium and fluorine as a rocket propellant

Description: Theoretical performance for liquid lithium and liquid fluorine as a rocket propellant was calculated with assumptions both of equilibrium and frozen composition during expansion. Parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, composition, mean molecular weight, characteristic velocity, coefficient of thrust, and ratio of nozzle-exit area to throat area. For chamber pressure of 300 pounds per square inch absolute and expansion to 1 atmosphere,… more
Date: May 10, 1951
Creator: Gordon, Sanford & Huff, Vearl N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Investigation of Several Types of Split Flap on a 47.7 Degree Sweptback-Wing - Fuselage Combination of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X 10(Exp 6)

Description: Report presenting a low-speed wind-tunnel investigation to determine the longitudinal aerodynamic characteristics of a 47.7 degree sweptback wing-fuselage combination with split flaps and several modifications. The lift characteristics, pitching-moment characteristics, drag characteristics, and a comparison with flaps of the slotted type are included.
Date: July 10, 1951
Creator: Spooner, Stanley H. & Mollenberg, Ernst F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral Control Characteristics and Dihedral Effect of a Wing-Body Combination With a Variable Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52

Description: "Aileron effectiveness and dihedral effect were investigated for a wing-body combination having a variable-incidence triangular wing with modified half-delta controls at the wing tips. The tests were conducted at a Mach number of 1.52 at a Reynolds number of 0.82 million. At the Mach number of the tests, the Mach cone from the wing apex was almost coincident with the wing leading edge" (p. 1).
Date: January 10, 1951
Creator: Scherrer, Richard & Dennis, David H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Study of the Effect of Sweepback on Transonic Aileron Flutter

Description: Report presenting the effects of sweepback on the occurrence and principal characteristics of single-degree-of-freedom aileron flutter for a wing-aileron combination. Testing occurred over a range of Mach and Reynolds number and angles of attack. Results regarding the measurements of aileron motion, effect of sweep, variation of lift coefficient, and use of shadowgraph technique for visualizing flow are provided.
Date: September 10, 1951
Creator: Levy, Lionel L., Jr. & Knechtel, Earl D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral-Control Characteristics and Dihedral Effect of a Wing-Body Combination With a Variable-Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52

Description: Memorandum presenting an investigation of aileron effectiveness and dihedral effect for a wing-body combination with a variable-incidence triangular wing with modified half-delta controls at the wing tips. The tests were conducted at a Mach number of 1.52 at a Reynolds number of 0.82 million. The experimental value of aileron effectiveness at 0 degrees angle of attack was approximately 78 percent of the value predicted by linear theory, and the effectiveness decreased with increasing wing angle… more
Date: January 10, 1951
Creator: Scherrer, Richard & Dennis, David H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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