451 Matching Results

Search Results

Results: 1 - 24 next
open access

Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Description: Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.
Date: June 17, 1954
Creator: Burrows, Dale L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53

Description: Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale … more
Date: June 24, 1958
Creator: Oehman, Waldo I. & Turner, Kenneth L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic Characteristics of Missiles Launched Under Water

Description: Report presenting some of the hydrodynamic problems associated with launching an air missile from underwater. The results of an experiment with models are also provided, including deviation angle, effect of forward speed of the submarine, curved path of the missile, and potential environmental disruptions.
Date: June 27, 1958
Creator: Dawson, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Estimation of Incremental Pitching Moments Due to Trailing-Edge Flaps on Swept and Triangular Wings

Description: Report presenting a method by which incremental pitching moments can be estimated for swept and triangular wings with arbitrary types of trailing-edge high-lift flaps. Span-loading theory is combined with two-dimensional airfoil data adjusted for the effects of sweep. Application of the method is demonstrated for 58 cases covering various types of flaps on wings with a wide range of sweep, aspect ratio, and taper ratio.
Date: June 10, 1955
Creator: James, Harry A. & Hunton, Lynn W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Removal of secondary-flow accumulations in a two-dimensional turbine nozzle passage by boundary-layer bleed

Description: Report presenting an investigation of boundary-layer bleed through a slot placed at the juncture of the suction surface and end wall to determine whether bleed in this manner could be used to prevent the local accumulation of boundary-layer fluids due to secondary flows. Results regarding the effect of bleed pressure, effect of bleed-slot height, and effect of slot length and position are provided.
Date: June 30, 1955
Creator: Wong, Robert Y.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Flutter Results for Cantilever-Wing Models at Mach Numbers Up to 3.0

Description: Report presenting experimental flutter testing at Mach numbers up to 3.0 using cantilever-wing models with 0 to 60 degree sweepback and 60 degree delta-wing models. The main variables explored were the high Mach number and center-of-gravity location on flutter trends. The theoretical results for flutter analyses were noted to be lower than the experimental results.
Date: June 14, 1955
Creator: Tuovila, W. J. & McCarty, John Locke
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral Stability and Control Measurements of a Fighter-Type Airplane With a Low-Aspect-Ratio Unswept Wing and a Tee-Tail

Description: Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.
Date: June 12, 1956
Creator: Arabian, Donald D. & Schmeer, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Bibliography of NACA Reports on Control of Turbojet Engines

Description: Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.
Date: June 28, 1956
Creator: Sanders, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Drag Coefficients of Round Noses With Conical Windshields at Mach Number 2.72

Description: "An exploratory investigation at Mach number 2.72 has been made to show the decrease in the drag of a round-nose model achieved by mounting a small cone on a rod ahead of the nose. The geometric parameters which were varied were the cone-base diameter, cone angle, and rod length. All models showed large decreases in drag compared to that of the round nose alone" (p. 1).
Date: June 28, 1955
Creator: Jones, Jim J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static longitudinal and lateral stability and control characteristics of an 0.065-scale model of the Chance Vought Regulus II missile at Mach numbers of 1.41, 1.61, and 2.01: TED No. NACA AD 398

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal and lateral stability and control characteristics of an 0.065-scale model of the Chance Vought Regulus II missile. The tests were made at three Mach and Reynolds numbers.
Date: June 6, 1955
Creator: Robinson, Ross B.; Driver, Cornelius & Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Recent Experimental Data on Three-Dimensional Oscillating Air Forces

Description: Report presenting the status of oscillating air forces, including forces, moments, and their respective phase angles for a 45 degree swept wing of aspect ratio 2 and for two bodies of revolution. Derivatives based on available analyses were also demonstrated for those three configurations.
Date: June 27, 1955
Creator: Leadbetter, Sumner A. & Clevenson, Sherman A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Steady-state and surge characteristics of a compressor equipped with variable inlet guide vanes operating in a turbojet engine

Description: Report presenting an investigation of a turbojet engine with variable inlet guide vanes in an altitude test facility to determine the steady-state compressor performance and surge characteristics. Compressor surge pressure ratios were found to be unaffected by changes in flight condition for either position of the inlet guide vanes. Decreasing the inlet Reynolds number was found to reduce the corrected fuel flow required for compressor surge.
Date: June 20, 1955
Creator: Wallner, Lewis E. & Lubick, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of wing flexibility on the damping roll of a notched delta-wing body combination between Mach numbers 0.6 and approximately 2.2 as determined with rocket-propelled models

Description: Report presenting an investigation with sting-mounted rocket-propelled models in free flight at approximately zero lift to determine the effect of wing flexibility on the damping-in-roll characteristics of a wing-body combination over a range of Mach numbers.
Date: June 18, 1954
Creator: Bland, William M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Amplitude Damping-in-Pitch Characteristics of Tailless Delta-Wing-Body Combinations at Mach Numbers From 0.80 to 1.35 as Obtained With Rocket-Powered Models

Description: Report of an investigation using three rocket-propelled delta-wing-body combinations for a range of Mach numbers to determine the damping-in-pitch characteristics. All models were statically stable but dynamically unstable at transonic speeds. Information about trim, lift, and drag is also provided.
Date: June 24, 1954
Creator: D'Aiutolo, Charles T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Forces and moments on inclined bodies at Mach numbers from 3.0 to 6.3

Description: Report presenting the results of force and moment tests at Mach numbers from 3.0 to 6.3 on bodies of revolution of fineness ratios from 5 to 10 and on flat-bottom bodies of fineness ratio 10 along with theoretical predictions for these bodies. Testing included eight cone and cone-cylinder models, six nose-cylinder models, and three flat-bottom bodies.
Date: June 25, 1954
Creator: Dennis, David H. & Cunningham, Bernard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Effects of Jet Exhaust and Reynolds Number Upon the Flow Over the Vertical Stabilizer and Rudder of the Douglas D-558-II Research Airplane at Mach Numbers of 1.62, 1.93, and 2.41

Description: Memorandum presenting an investigation to determine the effects of jet exhaust and Reynolds number on the flow over the vertical stabilizer and rudder of the Douglas D-558-II research airplane with special attention to an understanding of the rudder reversals experienced in flight on the full-scale airplane. Tests were made at Mach numbers of 1.62, 1.93, and 2.41 over a range of ratios of jet static pressure to stream static pressure from the jet-off ratio to about 40 and for a maximum range of… more
Date: June 17, 1954
Creator: Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Full-Scale Evaluation of Some Flameholder Design Concepts for High-Inlet-Velocity Afterburners

Description: Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.
Date: June 28, 1956
Creator: Prince, William R.; Velie, Wallace W. & Braithwaite, Willis M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical Investigation of Fuel-Cooled Turbine Blades With Return-Flow Type of Finned Coolant Passages

Description: Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen… more
Date: June 26, 1957
Creator: Nachtigall, Alfred J. & Slone, Henry O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine

Description: Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.
Date: June 12, 1957
Creator: Stepka, Francis S.; Richards, Hadley T. & Hickel, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds

Description: "The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).
Date: June 27, 1955
Creator: Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51

Description: Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
Date: June 23, 1958
Creator: Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0

Description: Memorandum presenting an investigation to determine the internal flow performance of a fixed 14 degree ramp inlet from zero to 20 degrees angle of attack conducted at three free-stream Mach numbers. The inlet was mounted in three circumferential fuselage locations and utilized inlet throat and fuselage boundary-layer removal.
Date: June 26, 1957
Creator: Mitchell, Glenn A. & Chiccine, Bruce G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Roll Effectiveness of a Differentially Deflected Horizontal-Tail Surface on a 42 Degree Swept-Wing Model

Description: Memorandum presenting an investigation to determine the roll effectiveness of a differentially deflected horizontal tail of a 42 degree swept-wing model. The model was tested through an angle-of-attack range of 0 degrees through the stall in the clean and landing configurations with the horizontal tail in a low position. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: June 19, 1956
Creator: Boisseau, Peter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen