17 Matching Results

Search Results

Results: 1 - 17
open access

Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane

Description: Memorandum presenting a transonic flutter investigation of models of the wing of a current fighter airplane. The models were dynamically and elastically scaled in accordance with criteria which include a flutter safety margin. Results regarding the presentation of data, interpretation of results, wings without leading-edge chord-extensions, and wings with leading-edge chord-extensions are provided.
Date: April 15, 1958
Creator: Smith, Samuel L., III & Boswinkle, Robert W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Transonic Flutter Investigation of Models of T-Tall of Blackburn NA-39 Airplane

Description: Report discussing a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation was made at a variety of Mach numbers at simulated altitudes extending to below sea level. The Mach numbers at which asymmetric flutter and symmetric oscillations occur are presented.
Date: April 15, 1958
Creator: Jones, George W., Jr. & Boswinkle, Robert W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of an Isentropic, All-Internal-Contraction, Axisymmetric Inlet Designed for Mach 2.50

Description: Memorandum presenting an experimental investigation of an internal-contraction, axially symmetric inlet with isentropic compression surfaces on both the cowl and centerbody conducted over a range of Mach numbers from 2.0 to 2.7 at angles of attack from 0 to 6 degrees. The study was made to determine the optimum bleed system, together with a method of controlling the inlet.
Date: September 15, 1958
Creator: Bowditch, David N. & Anderson, Bernhard H.
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 Rotor Entering Relative Mach Number of 2

Description: Memorandum presenting a design and experimental investigation of a single-stage supersonic turbine. The turbine was designed for a rotor entering relative Mach number of 2. Results regarding the overall turbine performance, outer-wall static-pressure variation, momentum-loss considerations, effect of rotor modifications, and supersonic starting are provided.
Date: September 15, 1958
Creator: Moffitt, Thomas P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Transonic Flutter Investigation of Models of T-Tail of Blackburn NA-39 Airplane

Description: Memorandum presenting a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation is to be considered preliminary in that only estimated airplane properties were available for the scaling. Results regarding interpretation of results, presentation of data, and a discussions are provided.
Date: April 15, 1958
Creator: Jones, George W., Jr. & Boswinkle, Robert W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Performance and Internal Flow of a Variable-Area, Variable-Internal-Contraction Inlet at Mach Numbers of 2.00, 2.50, and 2.92

Description: Memorandum presenting the performance of a variable-internal-contraction inlet without boundary-layer removal measured at Mach numbers of 2.00, 2.50, and 2.92. The total-pressure recovery at the design Mach number, 2.50, was 0.78. Results regarding total-pressure recovery and contraction ratio, flow unsteadiness and distortion, and summary data correlations are provided.
Date: July 15, 1958
Creator: Scherrer, Richard & Anderson, Warren E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of nose and afterbody modifications on aerodynamic characteristics of a body with and without a vertical tail at a Mach number of 2.01

Description: Report presenting the effects at Mach number 2.01 of various changes in nose and afterbody shape on the static aerodynamic characteristics of a body of revolution with a fineness ratio of 11 with an ogive nose, a cylindrical center section, and a boattail or cylindrical afterbody. Some body conditions were tested in combination with a vertical tail. Results regarding the effects of nose and afterbody modifications and vertical tail-on configurations are provided.
Date: April 15, 1958
Creator: Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane

Description: Report presenting a transonic flutter investigation of models of the wing of a fighter airplane. Results regarding the wings with and without leading-edge chord-extensions, and scaling of the stiffness are presented. The flutter boundary was found to remain below sea level with or without the leading-edge extensions.
Date: April 15, 1958
Creator: Smith, Samuel L., III & Boswinkle, Robert W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of shock-boundary-layer interaction on the performance of a long and a short subsonic annular diffuser

Description: Report presenting an investigation to determine the effects on performance of positioning normal shocks in or upstream of both a long and a short subsonic annular diffuser. Results regarding the entrance flow conditions, performance for subsonic-entrance flows, and performance with choked- and supersonic-entrance flows are provided.
Date: April 15, 1958
Creator: Wood, Charles C. & Henry, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Jet effects on the base drag of a cylindrical afterbody with extended nozzles

Description: A wind-tunnel investigation to determine the effects of both single and twin jets on base drag of a cylindrical body has been conducted at Mach numbers from 0.6 to 1.4. The plane of the jet exit was varied with respect to that of the afterbody. Jet total-pressure ratio ranged up to 20. Significant improvements in base drag were obtained by extending the plane of the jet exits beyond the afterbody base and by venting the base cavity to the external stream.
Date: April 15, 1958
Creator: Nelson, William J. & Scott, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Exploratory Investigation at Mach Numbers of 2.50 and 2.87 of a Canard Bomber-Type Configuration Designed for Supersonic Cruise Flight

Description: Report presenting results for a canard bomber-type configuration designed for supersonic cruise flight at Mach numbers 2.50 and 2.87 and over a range of angles of attack and angles of sideslip. Results regarding longitudinal characteristics and lateral stability are provided. The original configuration was directionally unstable at low angles of attack, but satisfactory directional stability could be obtained using upper-surface vertical fins.
Date: April 15, 1958
Creator: Kelly, Thomas C.; Carmel, Melvin M. & Gregory, Donald T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental ablation cooling

Description: Report presenting the results of an experimental investigation on the ablation of a number of promising materials for heating conditions comparable to those which maybe encountered by unmanned reentry satellite vehicles or heating conditions associated with reentry ballistic missiles. Results regarding exploratory tests, further Teflon tests, and graphite testing are provided.
Date: July 15, 1958
Creator: Bond, Aleck C.; Rashis, Bernard & Levin, L. Ross
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration

Description: Report presenting a wind-tunnel investigation of the low-speed aerodynamic characteristics of an airplane configuration designed to obtain high lift-drag ratios at hypersonic speeds. The power-off landing of this aircraft would be difficult due to the high sinking speeds inherent in the design. Results regarding the longitudinal characteristics, lateral characteristics, and landing considerations are provided.
Date: September 15, 1958
Creator: Kelly, Mark W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane

Description: Report presenting measurements in a wind tunnel of the subsonic static and dynamic-rotary stability derivatives of a model of an airplane designed to fly at high supersonic speeds and high altitudes. The effects of flaps and landing gear, speed brakes, and several model components are included in the results as well as the stability characteristics of the model.
Date: September 15, 1958
Creator: Lopez, Armando E. & Tinling, Bruce E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of leading-edge-flap deflection on the wing loads, load distributions , and flap hinge moments of the Douglas X-3 research airplane at transonic speeds

Description: Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the wing of the Douglas X-3 research airplane with various leading-edge-flap deflections. The load and hinge-moment characteristics of the leading-edge flap are presented for a range of Mach numbers with and without flap deflection. Results regarding chordwise load distributions, wing-section and wing-panel characteristics, span load and pitching-moment dist… more
Date: July 15, 1958
Creator: Keener, Earl R.; McLeod, Norman J. & Taillon, Norman V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of screens in reducing distortion and diffusion length for a 'dump' diffuser at a Mach number of 3.85

Description: Report presenting an investigation of the effect of screens in a dump-type diffuser in the 2- by 2-foot supersonic wind tunnel at Mach number 3.85. Results of a slanted half screen of 0.41 solidity, positioned 0.263 inlet diameter from the cowl lip, are presented on a range basis, as this configuration allows for shortening of the subsonic diffuser.
Date: July 15, 1958
Creator: Wasserbauer, Joseph F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal and Lateral Stability and Control Characteristics and Vertical-Tail-Load Measurements for a 0.03-Scale Model of the Avro CF-105 Airplane at Mach Numbers of 1.60, 1.80, and 2.00

Description: "An investigation has been made in the Langley Unitary Plan wind tunnel at Mach numbers of 1.60, 1.80, and 2.00 to determine the aerodynamic characteristics of a 0.03-scale model of the Avro CF-105 airplane. The investigation included the determination of the static longitudinal and lateral stability, the control and the hinge-moment characteristics of the elevator, rudder, and aileron, as well as the vertical-tail-load characteristics. Although the data are presented without analysis, a limite… more
Date: July 15, 1958
Creator: Silvers, H. Norman; Fournier, Roger H. & Wills, Jane S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen