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 Collection: National Advisory Committee for Aeronautics Collection
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

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

Date: September 23, 1958
Creator: Weston, K. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Date: September 23, 1958
Creator: Nettle, J. Cary
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. Temperature as high as 1200 F was measured in the base region because of the ignition of burnable rocket gases. combustibles that are dumped into the base by accessories seriously aggravate the base-burning temperature rise.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet from Mach 2.1 to 3.0

Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet from Mach 2.1 to 3.0

Date: September 23, 1958
Creator: Anderson, B. H. & Bowditch, D. N.
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 from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg. When the inlet was unstarted, an erroneous signal was obtained from the normal-shock control through most of the starting cycle that prevented the inlet from starting. Therefore, it was necessary to over-ride the normal-shock control signal and not allow the control to position the terminal shock until the spike was positioned.
Contributing Partner: UNT Libraries Government Documents Department
A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance

A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance

Date: September 20, 1958
Creator: Heinle, D. R. & Turner, H. L.
Description: Effects of manual attack-display noise filtering on pilot tracking performance.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Date: September 17, 1958
Creator: Gloria, H. R.; Sarabia, M. F. & Syvertson, C. A.
Description: Aerodynamic performance characteristics and static stability and control of hypersonic glider with arrow planform wings.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Date: September 17, 1958
Creator: Syvertson, Clarence A; Gloria, Hermilo R & Sarabia, Michael F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces

Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces

Date: September 17, 1958
Creator: Lazzeroni, Frank A.
Description: Wind tunnel tests of wingless low aspect ratio folding control missile configurations.
Contributing Partner: UNT Libraries Government Documents Department
Measurements of the buffeting loads on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane

Measurements of the buffeting loads on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane

Date: September 17, 1958
Creator: Rainey, A Gerald & Igoe, William B
Description: The buffeting loads acting on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane have been measured in the Langley 16-foot transonic tunnel in the Mach number range from 0.40 to 0.90. When the buffeting loads were reduced to a nondimensional aerodynamic coefficient of buffeting intensity, it was found that the maximum buffeting intensity of the horizontal tail was about twice as large as that of the wing. Comparison of power spectra of buffeting loads acting on the horizontal tail of the airplaneand of the model indicated that the model horizontal tail, which was of conventional force-test-model design, responded in an entirely different mode than did the airplane.This result implied that if quantitative extrapolation of model data to flight conditions were desired a dynamically scaled model of the rearward portion of the fuselage and empennage would be required. A study of the sources of horizontal-tail buffeting of the model indicated that the wing wake contributed a large part of the total buffeting load. At one condition it was found that removal of the wing wake would reduce the buffeting loads on the horizontal tail to about one-third of the original value.
Contributing Partner: UNT Libraries Government Documents Department
Stability investigation of a blunt cone and a blunt cylinder with a square base at Mach numbers from 0.64 to 2.14

Stability investigation of a blunt cone and a blunt cylinder with a square base at Mach numbers from 0.64 to 2.14

Date: September 17, 1958
Creator: Coltrane, Lucille C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design and Experimental Investigation of a Single-stage Turbine With a Rotor Entering Relative Mach Number of 2

Design and Experimental Investigation of a Single-stage Turbine With a Rotor Entering Relative Mach Number of 2

Date: September 15, 1958
Creator: Moffitt, T. P.
Description: Design of single-stage turbine for rotor entering at supersonic speed - performance characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Date: September 15, 1958
Creator: Anderson, B. H. & Bowditch, D. N.
Description: Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7.
Contributing Partner: UNT Libraries Government Documents Department
The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane

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

Date: September 15, 1958
Creator: Lopez, Armando E & Tinling, Bruce E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration

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

Date: September 15, 1958
Creator: Kelly, Mark W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight

Aerodynamic characteristics at Mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight

Date: September 10, 1958
Creator: Carmel, Melvin R; Kelly, Thomas C & Gregory, Donald T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10

Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10

Date: September 10, 1958
Creator: Swanson, A. G.
Description: Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 8O deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine of the sweep angle. The data also indicate that laminar heating rates over the windward surface of a highly swept flat glider wing at moderate angles of attack can be predicted with reasonable engineering accuracy by flat-plate theory using wedge local flow conditions and basing Reynolds numbers on lengths from the wing leading edge parallel to the surface center line.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at Mach numbers from 0.6 to 1.4 of several ejected pilot-seat models

Wind-tunnel investigation at Mach numbers from 0.6 to 1.4 of several ejected pilot-seat models

Date: September 10, 1958
Creator: Summers, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane

Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane

Date: September 10, 1958
Creator: Cocke, Bennie W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane

Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane

Date: September 9, 1958
Creator: Smith, C. C., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades

Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades

Date: September 4, 1958
Creator: Stepka, Francis S
Description: Average spanwise blade temperatures and cooling-air pressure losses through a small (1.4-in, span, 0.7-in, chord) air-cooled turbine blade were calculated and are compared with experimental nonrotating cascade data. Two methods of calculating the blade spanwise metal temperature distributions are presented. The method which considered the effect of the length-to-diameter ratio of the coolant passage on the blade-to-coolant heat-transfer coefficient and assumed constant coolant properties based on the coolant bulk temperature gave the best agreement with experimental data. The agreement obtained was within 3 percent at the midspan and tip regions of the blade. At the root region of the blade, the agreement was within 3 percent for coolant flows within the turbulent flow regime and within 10 percent for coolant flows in the laminar regime. The calculated and measured cooling-air pressure losses through the blade agreed within 5 percent. Calculated spanwise blade temperatures for assumed turboprop engine operating conditions of 2000 F turbine-inlet gas temperature and flight conditions of 300 knots at a 30,000-foot altitude agreed well with those obtained by the extrapolation of correlated experimental data of a static cascade investigation of these blades.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Injectors With a 200-pound-thrust Ammonia-oxygen Engine

Comparison of Injectors With a 200-pound-thrust Ammonia-oxygen Engine

Date: September 4, 1958
Creator: Clark, B. J. & Priem, R. J.
Description: Injection techniques for 200-pound thrust ammonia- oxygen rocket engine.
Contributing Partner: UNT Libraries Government Documents Department
Design and experimental performance of a 0.35 hub-tip radius ratio transonic axial-flow-compressor rotor designed for 40 pounds per second per unit frontal area

Design and experimental performance of a 0.35 hub-tip radius ratio transonic axial-flow-compressor rotor designed for 40 pounds per second per unit frontal area

Date: September 4, 1958
Creator: Montgomery, John C & Yasaki, Paul T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Thermal reaction of diborane with trimethylborane

Thermal reaction of diborane with trimethylborane

Date: September 4, 1958
Creator: Lamneck, John H , Jr & Kaye, Samuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Analysis of Ramjet Engines Using Supersonic Combustion

An Analysis of Ramjet Engines Using Supersonic Combustion

Date: September 1, 1958
Creator: Weber, Richard J & Mackay, John S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of the creep behavior of a square plate loaded in edge compression

Analysis of the creep behavior of a square plate loaded in edge compression

Date: September 1, 1958
Creator: Mccomb, Harvey G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department