National Advisory Committee for Aeronautics (NACA) - 218 Matching Results

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Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet

Description: Report presenting an investigation of the effect of inlet component blunting on performance using an axisymmetric external-compression inlet in the supersonic wind tunnel. The investigation was carried out to determine the performance penalties associated with spike-tip and cowl-lip blunting. Results regarding the effect of rounding the spike tip on inlet performance, overall drag coefficients, flow distortion, and Schileren photographs are provided.
Date: September 23, 1958
Creator: Cubbison, R. W. & Samanich, N. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet

Description: Report presenting the effect of inlet component blunting on performance using an axisymmetric external-compression inlet in order to determine the performance penalties associated with spike-tip and cowl-lip blunting. The data can be used as a design guide for blunt inlet components applicable to cooling techniques. Results regarding the effect of tip rounding, drag coefficients, flow distortion, lip blunting, and Schileren photographs are provided.
Date: September 23, 1958
Creator: Cubbison, R. W. & Samanich, N. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Effect of Spike- Tip and Cowl-Lip Blunting on the Internal Performance of a Two-Cone Cylindrical-Cowl Inlet at Mach Number 4.95

Description: Memorandum presenting the effect of blunting on the internal performance of a two-cone inlet with an internally cylindrical cowl investigated experimentally at Mach number 4.95. Total-pressure-recovery and mass-flow data were obtained for a range of spike and cowl bluntness.
Date: September 23, 1958
Creator: Weston, Kenneth C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Description: "A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor" (p. 1).
Date: September 23, 1958
Creator: Nettles, J. Cary
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.0

Description: "Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery f… more
Date: September 23, 1958
Creator: Anderson, Bernhard H. & Bowditch, David N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane with External Fuel Tanks, TED No. NACA AD 3112

Description: From Summary: "A supplementary investigation to determine the effect of external fuel tanks on the spin and recovery characteristics of a l/28-scale model of the North American FJ-4 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The model had been extensively tested previously (NACA Research Memorandum SL38A29) and therefore only brief tests were made to evaluate the effect of tank installation."
Date: July 23, 1958
Creator: Healy, Frederick M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Data From Flow-Field Surveys Behind a Large-Scale Thin Straight Wing of Aspect Ratio 3

Description: Memorandum presenting limited flow-field surveys made behind a large-scale thin straight wing of aspect ratio 3, both alone and in combination with a body and vertical tail. The surveys indicated a region of high downwash angles, low dynamic pressures, and rough flow, that extended higher above the wing chord plane, and farther aft, with increasing angle of attack beyond the tail.
Date: June 23, 1958
Creator: Evans, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of aerodynamic heating on the flutter of a rectangular wing at a Mach number of 2

Description: Report presenting the flutter of a solid wing as affected by aerodynamic heating, which can cause a large momentary loss in torsional stiffness. Both experimental and analytical studies were conducted and good correlation was demonstrated. The loss of stiffness due to aerodynamic heating was calculated and the operational line intersected with the flutter curve.
Date: June 23, 1958
Creator: Runyan, Harry L. & Jones, Nan H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
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Some Factors Affecting the Stability and Performance Characteristics of Canard Aircraft Configurations

Description: "A survey has been made of some of the factors to be considered in the design of canard aircraft configurations. The factors include Mach number and angle-of-attack effects as well as the effects of various geometric changes. Among the geometric variables included are the effects of wing plan form, wing height, wing twist, canard plan form, canard area, canard moment arm, forebody length, afterbody length, forebody deflection, vertical-tail plan form, vertical-tail size, vertical-tail location,… more
Date: June 23, 1958
Creator: Spearman, M. Leroy & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: An Aluminum-Alloy Model of 40-Inch Chord With 0.125-Inch-Thick Skin

Description: Report presenting testing of a 5-percent-thick 2024-T3 aluminum-alloy multiweb wing (MW-1-(2)) at a Mach number of 2 under simulated supersonic flight conditions. The wing experienced dynamic failure as a result of catastrophic flag-waving flutter due to the combined action of aerodynamic heating and loading. Results regarding model temperatures, experimental pressures, strain results, accelerometer, and model failure are provided.
Date: June 23, 1958
Creator: Griffith, George E. & Miltonberger, Georgene H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane

Description: Memorandum presenting an investigation of the steady-state wing loads conducted on a Boeing B-52 airplane over a range of Mach numbers and altitudes. Results regarding flight tests and air-load calculations are provided.
Date: April 23, 1958
Creator: Kuhl, Albert E.; Rogers, John T. & Little, Mary V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of flight-determined and predicted effects of flexibility on the steady-state wing loads of the B-52 airplane

Description: From Introduction: "This paper presents the results obtained during the phase of the B-52 flight investigation concerned with the steady-state wing loads. Where possible, the effects of Mach number and flexibility on the measured load are analyzed and presented."
Date: April 23, 1958
Creator: Kuhl, Albert E.; Rogers, John T. & Little, Mary V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of control trailing-edge thickness or aspect ratio on the oscillating hinge-moment and flutter characteristics of a flap-type control at transonic speeds

Description: Report presenting free-oscillation tests in the high-speed tunnel to determine the effect of control trailing-edge thickness and control aspect ratio on the dynamic hinge-moment characteristics of a trailing-edge, flap-type control. Tests were made at a range of Mach numbers and a range of oscillation reduced frequency at an angle of attack of 0 degrees. Results regarding damping moments and flutter characteristics and spring moments are provided.
Date: April 23, 1958
Creator: Moseley, William C., Jr. & Thompson, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Control Trailing-Edge Thickness or Aspect Ratio on the Oscillating Hinge-Moment and Flutter Characteristics of a Flaptype Control at Transonic Speeds

Description: Control trailing-edge thickness and aspect ratio effect on oscillating hinge-moment and flutter characteristics of flap-type controls. Results regarding damping moments and flutter characteristics and spring moments are provided.
Date: April 23, 1958
Creator: Moseley, William C., Jr. & Thompson, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ground Simulator Studies of a Small Side-Located Controller in a Power Control System

Description: Memorandum presenting an investigation to determine the operating characteristics of a small side-located control stick with the use of a ground simulator incorporating a power control system. The simulator or pitch chair was designed to produce the pitching motion associated with the short-period mode of an airplane. The general opinion of all of the pilots operating the pitch chair was that they were favorably impressed with their ability to precisely track with the small side-located control… more
Date: April 23, 1958
Creator: Assadourian, Arthur
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-subsonic investigation to determine the chordwise pressure distribution and effectiveness of spoilers on a thin, low-aspect-ratio, unswept, untapered, semispan wing and on the wing with leading and trailing-edge flaps

Description: Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the effect of spoilers on the static longitudinal and lateral aerodynamic characteristics and the chordwise pressure distribution on a thin, untapered, unswept, semispan wing with an aspect ratio of 3.33 and NACA 65A004 airfoil sections. Results are presented in the form of static longitudinal and lateral aerodynamic characteristics and tabulated pressure coefficients, section normal-force coefficients, and sect… more
Date: April 23, 1958
Creator: Croom, Delwin R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Description: From Introduction: "The configuration described in this paper represents one approach to such an airplane and the results of the wind-tunnel and tank evaluations are presented. In the present investigation, the aerodynamic longitudinal characteristics over a Mach number range from 0.6 to 1.97 were obtained."
Date: October 23, 1957
Creator: Petynia, William W.; Hasson, Dennis F. & Spooner, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Boundary Solidity of Planing Lift Obtained in a High-Speed Water Jet With a Single Longitudinal Slot in Each Rigid Boundary

Description: Report discussing the hydrodynamic planing-lift forces of a model of a rectangular jet with several boundaries with slots in them in order to obtain varying boundary solidities. The lift coefficients at the different boundary solidities were compared to computed values from an equation. Information about the effects of boundary solidity, the level of optimum solidity, and the effects of speed is provided.
Date: October 23, 1957
Creator: Weinflash, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of fuel variables on carbon formation in turbojet-engine combustors

Description: Report presents the results of an investigation of the effects of fuel properties and of a number of fuel additives on combustion-chamber carbon deposition and exhaust-gas smoke formation in a single tubular turbojet-engine combustor. Limited tests were conducted with a number of the fuels in several full-scale turbojet engines to verify single-combustor data.
Date: October 23, 1957
Creator: Jonash, Edmund R.; Wear, Jerrold D. & Cook, William P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Indications of the Cooling Achieved by Ejecting Water Upstream From the Stagnation Point of Hemispherical, 80 Degree Conical, and Flat-Faced Nose Shapes at a Stagnation Temperature of 4,000 F

Description: Memorandum presenting an investigation of the effectiveness of water-vaporization cooling that would be obtained by ejecting water upstream from the stagnation point conducted in a liquid-fuel rocket jet as a stagnation temperature of 4000 degrees Fahrenheit.
Date: October 23, 1957
Creator: Rashis, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Two-dimensional cascade tests of NACA 65-(C(sub zeta)(sub o))A(sub 10))10 blade sections at typical compressor hub conditions for speeds up to choking

Description: Report presenting two-dimensional porous-wall cascade tests of specified NACA blade sections at typical compressor hub conditions at speeds up to choking. For typical compressor blade hub sections, the angle of attack for best operation at high Mach numbers is about 6 degrees higher than the design angle of attack for low speeds. Results regarding the 65-series blade tests and circular-arc blade-section tests are provided.
Date: October 23, 1957
Creator: Emery, James C. & Dunavant, James C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of several afterburner configurations on a J79 turbojet engine

Description: Report presenting an investigation in the altitude test chamber to evaluate several afterburner configurations on the XJ79 engine. Data were obtained from nine configurations which show the effect on burner performance of increased burner diameter and modifications to the flameholder, fuel system, and flow swirl.
Date: September 23, 1957
Creator: Bloomer, Harry E. & Campbell, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Airplane Measurements of Atmospheric Turbulence for Altitudes Between 20,000 and 55,000 Feet Over the Western Part of the United States

Description: Report presenting a sample of data on atmospheric turbulence on Lockheed U-2 airplanes during research flights. The intensity, amount, and extent of atmospheric turbulence observed in the United States is in good agreement with data from England and Western Europe. Results regarding overall gust distribution, intensity of turbulence, percent of rough air, and size of turbulent areas are provided.
Date: August 23, 1957
Creator: Coleman, Thomas L. & Coe, Emilie C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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