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Development of a new flutter testing technique using a towed dynamic airplane model equipped with an automatic stabilizing system: Experimental and calculated dynamic stability characteristics for speeds up to 200 mph

Description: Report presenting testing of a towed airplane model in the 19-foot pressure tunnel in conjunction with the development of a flutter testing technique. The model was equipped with an autopilot to keep the model flying straight and level in the tunnel while restrained only in drag. Results regarding period and cycles to damp to half amplitude, time histories, and motions of the flexible wing model are provided.
Date: March 25, 1955
Creator: Schneider, William C.
Partner: UNT Libraries Government Documents Department
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Lift, drag, and static longitudinal stability characteristics of four airplane-like configurations at Mach numbers from 3.00 to 6.28

Description: Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for four airplane-like configurations determined from tests at a range of Mach numbers and angles of attack. The wings and nose shapes were modified for each of the configurations.
Date: April 25, 1955
Creator: Neice, Stanford E.; Wong, Thomas J. & Hermach, Charles A.
Partner: UNT Libraries Government Documents Department
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Effect of inlet-air-flow-distortions on steady-state performance of J65-B-3 turbojet engine

Description: The effects of inlet-air-flow distortions on the performance of the J65-B-3 turbojet engine were determined over a range of altitudes from 15,000 to 50,000 feet at a flight Mach number of 0.8. Radial inlet-air-flow distortions apparently do not affect the radial distribution of pressure after the first few compressor stages, while the circumferential inlet-air-flow distortion carried completely through the engine. For the distortions investigated, at rated exhaust-gas temperature and fixed-area… more
Date: January 25, 1956
Creator: Smith, Ivan D.; Braithwaite, W. M. & Calvert, Howard F.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of effect of cooling air on turbine performance of two turbojet engines modified for air-cooling

Description: Report presenting an investigation at sea-level static conditions to determine the effects of radial discharge of cooling air from turbine rotor blades on turbine performance in two turbojet engines, one with a centrifugal compressor and the other with an axial-flow compressor. Results regarding the performance characteristics, efficiency comparisons, and some interpretation are provided.
Date: January 25, 1956
Creator: Smith, Gordon T.; Freche, John C. & Cochran, Reeves P.
Partner: UNT Libraries Government Documents Department
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Investigation of the effects of body indentation and of wing-plan-form modification on the longitudinal characteristics of a 60 degree swept-wing-body combination at Mach numbers of 1.41, 1.61, and 2.10

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of body indentation on the minimum drag and maximum lift-drag ratio of a 60 degree swept-wing-body combination. A secondary goal of the tests was to determine the effect on the maximum lift-drag ratio of modifying the inboard plan form of the 60 degree swept wing. Lift, drag, and pitching-moment data are presented.
Date: July 25, 1955
Creator: Sevier, John R., Jr.
Partner: UNT Libraries Government Documents Department
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A flight investigation at transonic speeds and small angles of attack of the aerodynamic characteristics of a model having a 45 degree sweptback wing of aspect ratio 3 with an Naca 64A006 airfoil section

Description: Report presenting an investigation of the longitudinal aerodynamic characteristics of a model with a 45 degree sweptback wing of aspect ratio 3 and a 45 degree sweptback cruciform tail at transonic speeds and small angles of attack by a free-fall recoverable-model technique. Results regarding lift, drag, static longitudinal stability, dynamic longitudinal stability, and loading distribution over the fuselage are provided.
Date: January 25, 1954
Creator: Holdaway, George H.
Partner: UNT Libraries Government Documents Department
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Investigation of Two Short Annular Diffuser Configurations Utilizing Section and Injection as a Means of Boundary-Layer Control

Description: Memorandum presenting an investigation of the performances of two annular diffuser designs applicable to turbojet afterburner installations to determine the effectiveness of injection and suction boundary-layer controls. Results regarding inlet measurements, flow observations, static-pressure distributions, downstream velocity distributions, and mean performance coefficients are provided.
Date: January 25, 1955
Creator: Wilbur, Langley W. & Higginbotham, James T.
Partner: UNT Libraries Government Documents Department
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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.
Partner: UNT Libraries Government Documents Department
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Interference effects at Mach 1.9 on a horizontal tail due to trailing shock waves from an axisymmetric body with an exiting jet

Description: Report presenting measurements of the normal force and pitching moment of a rectangular tail surface at Mach 1.9 to determine the interference effects due to trailing shock waves from an axisymmetric body with a jet exiting from a sonic nozzle in the base. The data were obtained at various jet pressure ratios and locations of tail with respect to the body. Results regarding tail location, tail pitching moment, and tail-shock-wave effects on base pressure are provided.
Date: January 25, 1956
Creator: Salmi, Reino J. & Klann, John L.
Partner: UNT Libraries Government Documents Department
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Preliminary Free-Flight Investigation of the Effect of Airfoil Section on Aileron Rolling Effectiveness at Transonic and Supersonic Speeds

Description: "Results have been obtained by means of a free-flight technique utilizing rocket propulsion which indicate that aileron-rolling-effectiveness characteristics are affected adversely by variations in airfoil section which procedure large increases in the trailing-edge angle" (p. 1).
Date: June 25, 1948
Creator: Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness of a 42.7 Degree Sweptback Wing Having Partial-Span Ailerons

Description: An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ailerons on a 42.7 degree sweptback wing having symmetrical circular-arc airfoil sections of 10-percent thickness ratio normal to the wing quarter-chord line has been made by means of rocket-propelled test vehicles. The results are compared with results of a supersonic wind-tunnel test at Mach number 1.9.
Date: October 25, 1948
Creator: Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department
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NACA Transonic Wing-Tunnel Test Sections

Description: Memorandum presenting an approximate subsonic theory developed for the solid blockage interference in circular wind tunnels with walls slotted in the direction of flow. The theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.
Date: October 25, 1948
Creator: Wright, Ray H. & Ward, Vernon G.
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation at a Mach Number of 1.9 and a Reynolds Number of 2,200,000 of Three Ailerons Applicable to the Bell XS-2 Airplane Design

Description: Report presenting testing of a 42.7 degree sweptback tapered wing with three types of ailerons tested at a Mach number of 1.9 and a Reynolds number of 2,200,000; the wing geometry was similar to that of an XS-2 airplane. The purpose of the investigation was to determine the effectiveness of ailerons at these specified flight characteristics. Results regarding the aerodynamic characteristics of the wing are also provided.
Date: May 25, 1948
Creator: Sivells, James C. & Conner, D. William
Partner: UNT Libraries Government Documents Department
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Experimental investigation of the drag of 30 degree, 60 degree, and 90 degree cone cylinders at Mach numbers between 1.5 and 8.2

Description: Report presenting the total drag coefficients of 60 degree cone cylinders of fineness ratio 2.07 measured in free flight from Mach numbers of 1.5 to 8.2. Results regarding the smooth 60 degree cone cylinder, rifled models, and discontinuity lines in the shadowgraph pictures are provided.
Date: April 25, 1952
Creator: Seiff, Alvin & Sommer, Simon C.
Partner: UNT Libraries Government Documents Department
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Investigation of Stresses Due to Thermal Gradients in Typical Aircraft Structures

Description: Memorandum presenting an investigation of a series of five 75S-T6 aluminum-alloy elementary skin and spar-cap combinations with skin varying from 0.051 to 0.500 inch in thickness to determine the temperature and stress gradients resulting from the application of heat to the surface. The data are presented in the form of tables of the measured temperatures and stresses calculated from the measured strains.
Date: January 25, 1952
Creator: Barzelay, Martin E. & Boison, James C.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of the Longitudinal Stability and Control Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Up to 0.89

Description: Report presenting results and analysis of the longitudinal stability and control characteristics of the Douglas D-558-I airplane at a range of altitudes and Mach numbers. It was found that large and rapid changes in elevator deflection and force were required for balance at Mach numbers above 0.84 due to a sharp decrease in elevator-stabilizer effectiveness.
Date: June 25, 1951
Creator: Sadoff, Melvin; Roden, William S. & Eggleston, John M.
Partner: UNT Libraries Government Documents Department
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A study of the flow over a 45 degree sweptback wing-fuselage combination at transonic Mach numbers

Description: Report presenting pressure distributions, tuft patterns, and schileren surveys of a sweptback wing-fuselage combination in the 8-foot transonic tunnel at a range of Mach numbers and angles of attack. The wing had 45 degrees of sweepback, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Results regarding an angle of attack of 0 degrees, 4 degrees, 6 degrees, 8 degrees, 12 degrees, and 20 degrees are provided.
Date: June 25, 1952
Creator: Whitcomb, Richard T. & Kelly, Thomas C.
Partner: UNT Libraries Government Documents Department
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Total-Pressure Recovery of a Circular Underslung Inlet With Three Different Nose Shapes at a Mach Number of 1.42

Description: Report presenting tests of three types of nose shapes with a circular underslung inlet inlet located well forward of the body of revolution at a Mach number of 1.42. Total-pressure measurements and shadowgraphs of the different configurations were obtained.
Date: February 25, 1952
Creator: Merlet, Charles F. & Carter, Howard S.
Partner: UNT Libraries Government Documents Department
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The effect of bluntness on the drag of spherical-tipped truncated cones of fineness ratio 3 at Mach numbers 1.2 to 7.4

Description: Report presenting an investigation of the drag of spherically blunted conical models of fineness ratio 3 at a range of Mach and Reynolds numbers. Results of the tests showed that slightly blunted models had less drag than cones of the same fineness ratio through the Mach number range. Results regarding the total drag, wave drag, and viscous effects are provided.
Date: April 25, 1952
Creator: Sommer, Simon C. & Stark, James A.
Partner: UNT Libraries Government Documents Department
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Effects of Propeller-Shank Geometry and Propeller-Spinner-Juncture Configuration on Characteristics of an NACA 1-Series Cowling-Spinner Combination With an Eight-Blade Dual-Rotation Propeller

Description: Report presenting an investigation at low speed in the low-turbulence tunnel to determine the effects of variations in propeller-shank geometry and propeller-spinner-juncture configuration on the aerodynamic characteristics of an NACA 1-series cowling-spinner combination with an eight-blade dual-rotation propeller. Results regarding internal flow and external flow are provided.
Date: September 25, 1951
Creator: Keith, Arvid L., Jr.; Bingham, Gene J. & Rubin, Arnold J.
Partner: UNT Libraries Government Documents Department
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A flight study of requirements for satisfactory lateral oscillatory characteristics of fighter aircraft

Description: Report presenting a pilot-opinion survey conducted with a conventional fighter airplane fitted with special servo devices for varying in flight the dihedral effect, static directional stability, and directional damping. Results showing the boundaries that define satisfactory and tolerable lateral oscillatory characteristics are presented.
Date: July 25, 1951
Creator: Liddell, Charles J., Jr.; Creer, Brent Y. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department
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Flight calibration of angle-of-attack and sideslip detectors on the fuselage of a 35 degree swept-wing fighter airplane

Description: Report presenting measurements of the position errors of angle-of-attack and sideslip detectors located on the fuselage of a 35 degree swept-wing fighter airplane over a range of Mach numbers and at lift coefficients up to the buffet boundary. Results regarding the angle of attack and sideslip are provided.
Date: February 25, 1952
Creator: McFadden, Norman M.; Bray, Richard S. & Rathert, George A., Jr.
Partner: UNT Libraries Government Documents Department
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Free-flight investigation of longitudinal stability and control of a rocket-propelled missile model having cruciform, triangular, inline wings and tails

Description: Report presenting a rocket-propelled missile model with cruciform, triangular, inline wings and tails, which has been tested through a range of Mach numbers at small wing-deflection angles. Results regarding the stability and damping, control effectiveness, and hinge moments are provided.
Date: March 25, 1952
Creator: Hall, James R.
Partner: UNT Libraries Government Documents Department
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The Ames supersonic free-flight wind tunnel

Description: From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
Partner: UNT Libraries Government Documents Department
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