National Advisory Committee for Aeronautics (NACA) - 208 Matching Results

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Exploratory Investigation of Performance of Experimental Fuel-Rich Hydrogen Combustion System

Description: Memorandum presenting an exploratory investigation conducted to determine the performance characteristics of a fuel-rich hydrogen combustor; in addition, the performance of an afterburner operating with the fuel-rich exhaust mixture was evaluated. Results regarding performance of the fuel-rich combustor, afterburner performance, and resonating combustion are provided.
Date: June 25, 1958
Creator: Smith, Arthur L. & Grobman, Jack S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Data on the Longitudinal and Lateral-Directional Rotary Derivatives of a Straight-Wing, Research Airplane Configuration at Mach Numbers From 2.5 to 3.5

Description: Memorandum presenting the results of wind-tunnel oscillation tests to measure the rotary derivatives of a research airplane configuration at supersonic speeds. Measurements were made of the damping in yaw, pitch, and roll, the static longitudinal and directional stability derivatives, the effective-dihedral derivative, the rolling moment due to yawing, and the yawing moment due to rolling. The configuration was found to be statistically stable throughout the Mach number range, although its stab… more
Date: March 25, 1958
Creator: Beam, Benjamin H. & Endicott, Kenneth C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of fuel-orifice diameter on performance of heptane-oxygen rocket-engines

Description: A study of the effect of fuel-orifice diameter on the performance of heptane-oxygen rocket engines with single-element injectors. Five engines with a range of thrust were tested with parallel-sheet, triplet, and parallel-jet injectors. Decreasing the fuel-orifice diameter was found to increase the performance for a fixed chamber length. Results regarding injector performance and a comparison of experimental and analytical results are provided.
Date: February 25, 1958
Creator: Priem, Richard J. & Hersch, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Elevated-Temperature Combined Stress-Rupture Plus Fatigue Strength of Waspaloy Having Different Aging Treatments and/or Molybdenum Contents

Description: Report presenting an investigation to determine if the combined stress-rupture plus fatigue strengths of three groups of Waspaloy with different aging treatments and/or molybdenum contents could be correlated with their stress-rupture ductilities and notch-rupture strengths. Waspaloy is of interest as a gas turbine-bucket alloy because it has low strategic material content and relatively good stress-rupture properties. Results regarding metallurgical evaluation of the failed specimens are also … more
Date: February 25, 1958
Creator: Hoffman, C. A. & Hornak, M. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Preliminary Study of the Effect of Boric Oxide Deposits on the Performance of Two Selected Turbine Stator-Blade Shapes

Description: Report discussing testing on the performance of two stator-blade shapes with and without boric oxide deposits. The deposits were found to cause total pressure losses and decreases in the blade-exit flow angle. Information about the cascade throat area, boundary-layer momentum thickness, total pressure ratio, and exit flow angle and tangential component of velocity is provided.
Date: February 25, 1958
Creator: Setze, Paul C. & Nusbaum, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A preliminary study of the effect of boric oxide deposits on the performance of two selected turbine stator-blade shapes

Description: Report presenting the performance of two stator-blade shapes with and without boric oxide deposits, which was determined in a two-dimensional cascade. The differences between the blades were the amount of curvature and suction-surface diffusion downstream of the throat. Results regarding the cascade throat area, boundary-layer momentum thickness, total-pressure ratio, and exit flow angle and tangential component of velocity.
Date: February 25, 1958
Creator: Setze, Paul C. & Nusbaum, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-Oxygen Mixtures Assuming Equilibrium Composition

Description: "Theoretical rocket performance for equilibrium composition during expansion was calculated for JP-4 fuel with several fluorine-oxygen mixtures for a range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperature, nozzle-exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, thermal conductivity… more
Date: February 25, 1958
Creator: Gordon, Sanford
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Mutual Interference Loads on a Supersonic Bomber Configuration and Store During Separation at Mach Numbers of 1.57, 1.77, and 2.01

Description: Report discussing an investigation into the mutual interference loads on a supersonic bomber configuration and store during separation of the store. Tests were performed at several airplane angles of attack, store angles of attack, and airplane sidestep angles. The aerodynamic characteristics of the various components and coefficients of forces are provided in tables.
Date: October 25, 1957
Creator: Morris, Owen G. & Turner, Kenneth L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a Series of Practice Bombs

Description: Report discussing zero-lift drag data for several bomb configurations at various Mach numbers. Seven configurations were tested with different combinations of interchangeable noses and tail cones with fins, some with different surface conditions. Surface conditions were not found to affect the drag, but the thickness of the tail fins and shape of the noses did change the shape of the drag curve.
Date: October 25, 1957
Creator: Ward, Donald H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of low-lift drag at Mach numbers from 0.74 to 1.37 of rocket-boosted models having externally braced wings and cantilever wings

Description: Report presenting an investigation to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing wing thickness while external braces were used to provide the necessary bending strength. The investigation was conducted with two rocket models of aspect ratio 3.04, and unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data was compa… more
Date: September 25, 1957
Creator: Dickens, Waldo L. & Hastings, Earl C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compressibility Effects on a Hovering Helicopter Rotor Having an NACA 0018 Root Airfoil Tapering to an NACA 0012 Tip Airfoil

Description: Report presenting an investigation to determine the effects of compressibility on the hovering performance and the blade pitching moments of a helicopter rotor with a tip airfoil, a root airfoil, and twist. Results regarding hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.
Date: September 25, 1957
Creator: Powell, Robert D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation of the Drag of a Model of a 60 Degree Delta-Wing Bomber With Strut-Mounted Siamese Nacelles and Indented Fuselage at Mach Numbers From 0.80 to 1.35

Description: Memorandum presenting a model of a 60 degree delta-wing bomber with strut-mounted Siamese nacelles, which was designed, with the use of a symmetrical fuselage indentation, to have a smooth average area distribution at a Mach number of 1.20. The results show that the configuration drag rise was significantly higher than that from the equivalent-body tests and area-rule theory throughout the Mach number range. Results regarding total drag and pressure drag are provided.
Date: September 25, 1957
Creator: Hoffman, Sherwood
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Measurements at Transonic and Low Supersonic Speeds on a Thin Conical Cambered Low-Aspect-Ratio Delta Wing in Combination With Basic and Indented Bodies

Description: Report discussing pressure distributions on a thin conical cambered low-aspect-ratio delta wing over a range of Mach numbers. Combinations tested included the wing in combination with a basic Sears-Haack body and a body indented symmetrically for Mach number 1.2. Results regarding wing pressure distributions, effects of body indentation on the wing pressure, body pressure distributions, and effects of body indentation on body pressures are presented.
Date: September 25, 1957
Creator: Mugler, John P., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Investigation of Effects of Spanwise and Chordwise External Store Location and Body Contouring on Aerodynamic Characteristics of 45 Degree Sweptback Wing-Body Configuration

Description: Report presenting an investigation to determine the effects of spanwise and chordwise external store location on the aerodynamic characteristics of a cambered 45 degree sweptback wing-body configuration at a range of Mach numbers. Information about the drag characteristics of the various configurations, lift characteristics, and longitudinal stability characteristics is presented.
Date: September 25, 1957
Creator: Pearson, Albin O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of Missile Configurations With Wings of Low Aspect Ratio for Various Combinations of Forebodies, Afterbodies, and Nose Shapes for Combined Angles of Attack and Sideslip at a Mach Number of 2.01

Description: "An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a series of missile configurations having low-aspect-ratio wings at a Mach number of 2.01. The effects of wing plan form and size, length-diameter ratio, forebody and afterbody length, boattailed and flared afterbodies, and component force and moment data are presented for combined angles of attack and sideslip to about 28 degrees. No analysis of the data was mad… more
Date: June 25, 1957
Creator: Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Low-Speed Stability and Control Characteristics of a 1/7-Scale Model of the North American X-15 Airplane

Description: Report presenting an investigation of the low-speed power-on stability and control characteristics of a free-flying model of the North American X-15 airplane. Results regarding the longitudinal stability and control, lateral stability, and lateral control are provided. Longitudinal stability was low, but it was considered to be satisfactory up to an angle of attack of about 30 degrees.
Date: June 25, 1957
Creator: Boisseau, Peter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design and experimental investigation of a single-stage turbine with a downstream stator

Description: The high-work-output turbine had an experimental efficiency of 0.830 at the design point and a maximum efficiency of 0.857. The downstream stator was effective in providing axial flow out of the turbine for almost the whole range of turbine operation.
Date: January 25, 1957
Creator: Plohr, Henry W.; Holeski, Donald E. & Forrette, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Investigation of the Attack Phase of an Automatic Interceptor System at Supersonic Speeds With Particular Attention to Aerodynamic and Dynamic Representation of the Interceptor

Description: Report presenting a theoretical investigation of the attack phase of an automatically controlled interceptor. Three types of control systems were simulated on an analog computer: a modern high-speed interceptor, a dynamically perfect radar-controlled director-type guidance system for a lead-collision course, and a velocity-type automatic pilot. The primary flight maneuver tested was a 5g climbing turn with roll and acceleration commands applied simultaneously.
Date: January 25, 1957
Creator: Sherman, Windsor L. & Schy, Albert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical performance of liquid hydrogen and liquid fluorine as a rocket propellant for a chamber pressure of 600 pounds per square inch absolute

Description: Report presenting theoretical rocket performance for frozen and equilibrium composition during expansion for the propellant combination of liquid hydrogen and liquid fluorine at a chamber pressure of 600 pounds per square inch absolute and several pressure ratios and oxidant-fuel ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area… more
Date: January 25, 1957
Creator: Fortini, Anthony & Huff, Vearl N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tolerable Limits of Oscillatory Accelerations Due to Rolling Motions Experienced by One Pilot During Automatic-Interceptor Flight Tests

Description: Report presenting limited flight-test data obtained from an automatically controlled interceptor during runs in which oscillatory rolling motions occurred that were then compared to the pilot's comments about his ability to tolerate the imposed lateral oscillations. The alleviation of the undesirable effects of oscillatory lateral accelerations and their effects on piloting task were also considered. The marginally tolerable limit of acceleration forces on the pilot's head was found to be about… more
Date: January 25, 1957
Creator: Brissenden, Roy F.; Cheatham, Donald C. & Champine, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of External Stiffening Ribs on the Rolling Power of Ailerons on a Swept Wing

Description: Report presenting an investigation to determine the effects of external ribs, or load carrying fences, on the rolling effectiveness and drag on swept wings of two different stiffnesses. The primary effect of adding fences was a decrease in torsional flexibility and an increase in zero-lift rolling effectiveness. The aerodynamic effects on zero-lift rolling effectiveness due to adding fences are negligible.
Date: October 25, 1956
Creator: Stephens, Emily W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Aerodynamic Loading on a Helicopter Rotor Blade in Forward Flight

Description: Memorandum presenting an experimental investigation of the aerodynamic loading on one blade and of a two-blade teetering rotor conducted in forward flight for a tip-speed-ratio range of 0.08 to 0.29 at a disk loading of about 2.4 pounds per square foot and a tip speed of about 480 feet per second. Chordwise loading distributions at five spanwise stations and the variation of section loading and total blade lift with azimuth position are presented. Results regarding the performance data, section… more
Date: October 25, 1956
Creator: Rabbott, Robert P., Jr. & Churchill, Gary B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental study of the zero-angle-of attack transonic drag associated with the vertical position of a horizontal tail at zero incidence

Description: Report presenting a study of the transonic drag associated with varying the vertical location of the horizontal tail of a representative tail-body combination. Factors which significantly influenced the results were flow separation in the horizontal tail-body juncture, afterbody-tail-interference pressure drag, and a downwash over the horizontal tail which resulted from the boundary conditions of the converging afterbody.
Date: October 25, 1956
Creator: Howell, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight measurements of the low-speed characteristics of a 35 degree swept-wing airplane with blowing-type boundary-layer control in the trailing-edge flaps

Description: Report presenting tests to determine the flight characteristics of an F-86 airplane equipped with a blowing-type boundary-layer-control installation on the trailing-edge flaps. The effectiveness of the flap was determined in conjunction with slatted leading edges and an inflatable rubber boot on the leading edge. Measurements were made of lift, drag, flow requirements, and computations for take-off, climb, and landing.
Date: October 25, 1956
Creator: Anderson, Seth B.; Quigley, Hervey C. & Innis, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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