500 Matching Results

Search Results

Results: 1 - 24 next
open access

Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Degree Swept- Wing-Fuselage Configuration at a Mach Number of 1.61

Description: Forces and moments of store-pylon combination mounting on swept wing-fuselage configuration in supersonic pressure tunnel. The results of the investigation indicate that the most important source of store-pylon side forces is the pylon itself.
Date: January 30, 1958
Creator: Morris, Odell A.; Carlson, Harry W. & Geier, Douglas J.
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability Investigation of a Vertical-Take-Off-and-Landing Airplane Configuration With Simulated Jet Intake and Exhaust at Mach Numbers of 1.61 and 2.01

Description: Report presenting an investigation of a semispan model of a possible vertical-take-off-and-landing jet bomber configuration at a range of Mach numbers. The primary objective was to determine to the effects of jet interference, horizontal-tail location, and canard controls on the longitudinal stability characteristics of the model.
Date: January 30, 1958
Creator: Lord, Douglas R.
Partner: UNT Libraries Government Documents Department
open access

Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Description: Report presenting the performance of a two-dimensional side inlet with a technique of varying compression-surface angle while retaining a fixed-geometry diffuser at several Mach numbers and zero angle of attack. A 12 degree compression ramp was faired into the diffuser contour in this conventional manner. Results regarding the inlet flow field, application to reduced engine speeds, and a inlet performance with a sudden expansion in the diffuser are provided.
Date: January 30, 1958
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department
open access

Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 by 10 to the 6th Power

Description: Report discussing heat-transfer and pressure measurements obtained from flight testing of a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. The heat-transfer coefficients were compared to theoretical results and a discrepancy was found during the accelerating portions of flight. Drag coefficients were obtained for a range of Mach numbers.
Date: January 29, 1958
Creator: Graham, John B., Jr.
Partner: UNT Libraries Government Documents Department
open access

Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model on the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 X 10(Exp 6) : Coord. No. AF-AM-70

Description: Report presenting heat-transfer and pressure measurements obtained from flight tests of a model of the Titan intercontinental ballistic missile. Turbulent flow was observed over the model throughout the flight with the exception of one station on the nose. Results regarding pressure measurements, heat transfer, and drag measurements are required.
Date: January 29, 1958
Creator: Graham, John B., Jr.
Partner: UNT Libraries Government Documents Department
open access

Effects of Leading-Edge Slat and Trailing-Edge Split Flap on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a Nearly Triangular Wing of Aspect Ratio 2.9 at Mach Numbers From 0.60 to 0.92

Description: Report presenting an investigation to determine the effectiveness of a leading-edge slat and a trailing-edge split flap in improving the high subsonic speed aerodynamic characteristics of a model of a wing-fuselage combination with a nearly triangular wing. Results regarding the effects of Reynolds number, effects of slats, and effects of flaps are provided.
Date: January 24, 1958
Creator: Demele, Fred A.
Partner: UNT Libraries Government Documents Department
open access

Free-flight roll performance of a steady-flow jet-spoiler control on an 80 degree delta-wing missile between Mach numbers of 0.6 and 1.8

Description: Report presenting a free-flight investigation of the zero-lift control effectiveness of a steady-flow jet-spoiler roll control on a cruciform 80 degree delta-wing missile over a range of Mach numbers. Measurements were made of the rolling-moment, damping-in-roll derivative, drag, and pressures at the inlet and on the wing near the jet exit. Results indicated that the wing and jet combination magnified the thrust force of the isolated jet alone by factors of 11 at subsonic speeds to 3 at superso… more
Date: January 24, 1958
Creator: Schult, Eugene D.
Partner: UNT Libraries Government Documents Department
open access

Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane

Description: Memorandum presenting a transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane in the transonic blowdown tunnel. The models were dynamically and elastically scaled by criteria which provide a flutter safety margin. Results regarding some general comments, simulated airplane tests, effects of pitch stiffness with rearward pitch axis, and effect of pitch-axis location are provided.
Date: January 24, 1958
Creator: Sellers, Thomas B.
Partner: UNT Libraries Government Documents Department
open access

Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane

Description: Report presenting an investigation of the transonic flutter characteristics of models of an all-movable horizontal tail of a fighter airplane. Results regarding simulated airplane tests, the effects of pitch stiffness with rearward pitch axis, and the effect of pitch-axis location are provided.
Date: January 24, 1958
Creator: Sellers, Thomas B.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Use of Leading-Edge and Trailing-Edge Area-Suction Flaps on a 13-Percent-Thick Straight Wing and Fuselage Model

Description: Report presenting a wind-tunnel investigation to determine the effectiveness of area suction in increasing the lift of a moderately thick straight wing encountering trailing-edge air flow separation. Results regarding a model with undeflected leading-edge flap and tip tanks on and a model with the tip tanks removed are provided.
Date: January 24, 1958
Creator: Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Vortex Movements About a Wing in Steady Subsonic Flow Undergoing a Large Angle-of-Attack Change in a Blast-Induced Gust

Description: Report presenting some measurements of the vortex movements with time about an airfoil undergoing a blast of sufficient strength to exceed the stall angle by a large amount. Measurements were also obtained without flight simulation but with blast orientation and strength and compared to the first test. Results regarding Schileren photographs, presentation of results, and discussion of results are provided.
Date: January 22, 1958
Creator: McFarland, Donald R. & Huber, Paul W.
Partner: UNT Libraries Government Documents Department
open access

Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-Cylinder-Flare Configuration in Free Flight at Mach Numbers Up to 4.7

Description: Report presenting measurements of aerodynamic heat transfer at a number of stations along a cone-cylinder-flare model with 15 degree total-angle conical nose and a 10 degree half-angle flare skirt. Results regarding temperature measurements and heating rates, local flow parameters, heat transfer with theoretical recovery factors, experimental recovery factors, prediction of skin temperatures, and transition are provided.
Date: January 22, 1958
Creator: Rumsey, Charles B. & Lee, Dorothy B.
Partner: UNT Libraries Government Documents Department
open access

A Simulator Investigation of Factors Affecting the Design and Utilization of a Stick Pusher for the Prevention of Airplane Pitch-Up

Description: Memorandum presenting the results of a simulator stud of the factors affecting the design of a device, a stick pusher, for preventing a representative supersonic airplane from entering the pitch-up region. The effects of varying the stick-pusher-activation boundaries, sensing parameters, and magnitude of stick-pusher force on the controllability of the airplane pitch-up were investigated.
Date: January 22, 1958
Creator: Holleman, Euclid C. & Boslaugh, David L.
Partner: UNT Libraries Government Documents Department
open access

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22 : longitudinal characteristics of a triangular wing and canard

Description: Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers. Data are presented for a variety of angles of attack and canard angles.
Date: January 22, 1958
Creator: Boyd, John W. & Peterson, Victor L.
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Boundary-Layer-Control Investigation on a Thin Rectangular Semispan Wing With Leading-Edge and Trailing-Edge Flaps

Description: Report presenting a boundary-layer-control investigation to determine the longitudinal aerodynamic characteristics and chordwise load distribution on a thin, untapered, semispan wing with an aspect ratio of 3.33 and NACA 65A004 airfoil sections. The results are presented without discussion.
Date: January 20, 1958
Creator: Croom, Delwin R. & Turner, Thomas R.
Partner: UNT Libraries Government Documents Department
open access

Tracking Performance of a Swept-Wing Fighter With a Director-Type Radar Fire-Control System and Scope Presentation

Description: Memorandum presenting flight tests conducted with an F-86D airplane equipped with a director-type radar fire-control system with scope presentation of the attack display. The effects of two attack-computer parameters and one attack-display parameter on the tracking performance in the manual mode of operation were investigated. Results regarding fixed-sight tracking and tracking with scope presentation are provided.
Date: January 20, 1958
Creator: Turner, Horward L.; Rathert, George A., Jr. & Heinle, Donovan R.
Partner: UNT Libraries Government Documents Department
open access

Tracking performance of a swept-wing fighter with a director-type radar fire-control system and scope presentation

Description: Report presenting flight testis using an F-86D airplane equipped with a director-type radar fire-control system with scope presentation of the attack display. The effects of two attack-computer parameters and one attack-display parameter on the tracing performance in manual mode were investigated.
Date: January 20, 1958
Creator: Turner, Howard L.; Rathert, George A., Jr. & Heinle, Donovan R.
Partner: UNT Libraries Government Documents Department
open access

Component performance investigation of L71 experimental turbine 10: effect of first-stator adjustment; internal flow conditions of J71-97 turbine with 132-percent-design stator area

Description: Report presenting an investigation of the changes in the internal flow conditions resulting from adjusting the first-stator throat area of the J71 experimental three-stage turbine. The results of interstage flow measurements obtained from a radial survey investigation conducted on the turbine when equipped with a first-stage stator with the throat area increased to 132 percent of the design area and operated at a single predetermined turbine match point are also provided.
Date: January 16, 1958
Creator: Petrash, Donald A.; Schum, Harold J. & Davison, Elmer H.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a 7-Inch-Tip-Diameter Transonic Turbine

Description: Memorandum presenting the overall performance results obtained for a 7-inch transonic turbine and a comparison with the results of a 14-inch turbine of geometrically similar design that had been previously investigated. The peak efficiency obtained with the turbine was 0.85, which was 2 points lower than that obtained previously with the 14-inch turbine.
Date: January 16, 1958
Creator: Whitney, Warren J. & Wintucky, William T.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a 7-Inch-Tip-Diameter Transonic Turbine

Description: Report presenting performance results for a 7-inch transonic turbine and a comparison of said turbine with a 14-inch turbine of geometrically similar design. The size effect on performance was found to generally be due to the inability to fabricate the smaller blades to the same percentage of dimensional deviation as that of larger blades. Results regarding overall performance and performance under specific inlet conditions are provided.
Date: January 16, 1958
Creator: Whitney, Warren J. & Wintucky, William T.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a High Subsonic Mach Number Turbine Having a 40-Blade Rotor With Zero Suction-Surface Diffusion

Description: Memorandum presenting an experimental turbine designed for a high weight flow per unit frontal area, a high specific work output, a relative critical velocity ratio of 0.82 at the rotor hub inlet, and zero rotor blade suction-surface diffusion. Results regarding a comparison of overall performance of subject turbine with that of configurations I and II and comparison of rotor blade momentum thickness of subject turbine with that of configurations I and II are provided.
Date: January 16, 1958
Creator: Nusbaum, William J.; Wasserbauer, Charles A. & Hauser, Cavour H.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of a high subsonic Mach number turbine having a 40-blade rotor with zero suction-surface diffusion

Description: Report presenting an experimental turbine designed for high weight flow per unit frontal area, a high specific work output, a relative critical velocity ratio of 0.82 at the rotor hub inlet, and zero rotor blade suction-surface diffusion. At the equivalent design blade speed and work out put, the brake internal efficiency based on the actual overall total-pressure ratio was 0.889. Results regarding the comparison of overall performance of subject turbine with that of configurations I and II and… more
Date: January 16, 1958
Creator: Nusbaum, William J.; Wasserbauer, Charles A. & Hauser, Cavour H.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Description: Report presenting an investigation to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct prototype aircraft. Results regarding inlet instability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, theoretical thraot Mach number control analysis, effect of angle of attack, and… more
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Description: Report presenting an investigation in the supersonic wind tunnel to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct, side-inlet, fuselage forebody model of a prototype aircraft. These types of control systems have been found to be particularly helpful in supersonic flight. Results regarding inlet stability, control requirements, indi… more
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen