Technical Report Archive & Image Library (TRAIL) - 156 Matching Results

Search Results

Results: 1 - 24 next
open access

Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Tests occurred at a range of angles of attack and control deflections. Results regarding basic pressure distributions, comparison of experimental and theoretical results, and experimental comparisons are provided.
Date: May 16, 1958
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 degree delta wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at two Mach numbers to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Thirteen controls were of the balanced tip type and seven of the controls were of the more conventional trailing-edge type. Results regarding the basic pressure distributions, comparison of experimental and theoretical results, and some experimental comparisons are provided.
Date: May 16, 1958
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of sliding velocity on friction properties and endurance life of bonded lead monoxide coatings at temperatures up to 1250 degrees F

Description: Report presenting studies to determine the effect of sliding velocity and ambient temperature on the friction properties and endurance lift of thin lead monoxide coatings bonded to type 440-C martensitic stainless steel. Results regarding the effect of run-in on endurance life are also provided.
Date: May 16, 1958
Creator: Sliney, Harold E.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary performance data obtained in a full-scale, free-jet investigation of a side-inlet supersonic diffuser

Description: Report presenting an investigation of a full-scale, four-shock, side-inlet diffuser in a free-jet facility at a Mach number of 3.16. The diffuser was a heavy-duty version of the diffuser to be used with the XRJ47-W-7 engine. Results regarding the supercritical capture-area ratio, critical diffuser total-pressure recovery, and diffuser-exit flow profiles are provided.
Date: January 16, 1958
Creator: Seashore, Ferris L. & Farley, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing

Description: Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Date: October 16, 1957
Creator: Hanson, Perry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing

Description: Report presenting an experimental investigation made in the supersonic flutter tunnel to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing over a range of Mach numbers. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Date: October 16, 1957
Creator: Hanson, Perry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight and Analog Study of the Effect of Elevating the Radar-Boresight Axis Upon Stability and Tracking Performance of an Automatically Controlled Interceptor

Description: Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. Results regarding effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, effect of elevating the radar-boresight axis upon the required bank-angle feedback, an… more
Date: October 16, 1957
Creator: Cheatham, Donald C. & Mathews, Charles W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight and Analog Study of the Effect of Elevating the Radar-Boresight Axis Upon Stability and Tracking Performance of an Automatically Controlled Interceptor

Description: Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. The interceptor was designed to perform the lead-pursuit type of attacks and test runs were made in flight and on the analog simulator with and without lead-angle computation. Results regarding the effects of interceptor rolling motion upon tracking errors, similarity of flight resu… more
Date: October 16, 1957
Creator: Cheatham, Donald C. & Mathews, Charles W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A preliminary investigation of methods for improving the pressure recovery characteristics of variable-geometry supersonic-subsonic diffuser systems

Description: Report presenting an investigation to study methods for improving the pressure-recovery characteristics of two-dimensional, variable-geometry, supersonic-subsonic diffuser systems. Results without injection, with injection, and effect of diffuser configuration on wind-tunnel performance are provided.
Date: October 16, 1957
Creator: Hasel, Lowell E. & Sinclair, Archibald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic wind-tunnel investigation of the low-lift aerodynamic characteristics, including the effects of leading edge droop and thickness, of a thin trapezoidal wing in combination with basic and indented bodies

Description: Report presenting an investigation in the transonic tunnels to determine the aerodynamic force characteristics at low lift coefficients for a 2-percent-thick trapezoidal wing tested in combination with basic and indented bodies. The effects of wing leading-edge droop and wing thickness were investigated. Testing occurred over a range of Mach numbers and angles of attack.
Date: October 16, 1957
Creator: Kelly, Thomas C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Design and Cascade Tests of Free-Streamline and Full-Contour 160 Degree Turning Supersonic-Turbine-Blade Sections

Description: Memorandum presenting the flow characteristics of two supersonic-impulse-turbine-blade sections designed for a turning angle of 160 degrees. Results regarding the full-contour blade, free streamline blades, and a comparison of the performance are provided.
Date: August 16, 1957
Creator: Westphal, Willard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The design and cascade tests of free-streamline and full-contour 160 degrees turning supersonic-turbine-blade sections

Description: Report presenting a study of the flow characteristics of two supersonic-impulse-turbine-blade sections designed for a turning angle of 160 degrees. The primary difference between the two sections was the cutting away of a large portion of the convex surface and the presence of a free streamline as the boundary of flow in the passage. Results regarding the full-contour blade, free-streamline blade, and a comparison of the two are provided.
Date: August 16, 1957
Creator: Westphal, Willard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration

Description: Report discussing a model of a delta-wing configuration with four engines mounted two to a nacelle below the wing that was tested a variety of Mach numbers and Reynolds numbers. The wing static-pressure coefficients, wing pressure coefficients, and lift coefficient of different configurations are described.
Date: August 16, 1957
Creator: Falanga, Ralph A. & Judd, Joseph H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight investigation at transonic speeds of the power-on characteristics including some effects of sonic propulsive jets of a four-engine delta-wing configuration

Description: Report presenting an investigation of a free-flight model of a delta-wing configuration with four engines mounted two to a nacelle below the wing with rocket turbojet simulators operating at a range of Mach numbers. Results regarding wing pressure coefficients, fuselage pressure coefficient, airplane aerodynamic characteristics, and airplane trim are provided.
Date: August 16, 1957
Creator: Judd, Joseph H. & Falanga, Ralph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Status of Spin Research for Recent Airplane Designs

Description: Report presenting the status of spin research for recent airplane designs as interpreted. Some of the major problem areas discussed include interpretation of results of spin-model research, analytical spin studies, techniques involved int he measurement of various parameters in the spin, effectiveness of controls during spins and recoveries, influence of long noses, strakes, and canards on spin and recovery characteristics, and correlation of airplane and model spin and recovery characteristics. more
Date: August 16, 1957
Creator: Neihouse, Anshal I.; Klinar, Walter J. & Scher, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation to Determine the Effectiveness of Mach Number 1.0, 1.2, and 1.41 Fuselage Indentations for Reducing the Pressure Drag of a 45 Degree Sweptback Wing Configuration at Transonic and Low Supersonic Speeds

Description: Report presenting a flight investigation to determine the effectiveness of three fuselage indentations for reducing the pressure drag of a 45 degree sweptback-wing-body configuration at a range of Mach numbers. The results indicate that the supersonic area rule can be used to determine indentations with low pressure drag over a Mach number range in which the blunt leading edge is subsonic. Information about total drag and pressure drag is provided.
Date: May 16, 1957
Creator: Blanchard, Willard S., Jr. & Hoffman, Sherwood
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of wing-body juncture interference effects at transonic speeds for several swept-wing and body combinations

Description: Report presenting the results of an investigation of wing-body juncture interference effects at high subsonic and transonic speeds. Three different model series were used: one with a swept wing of aspect ratio 6 and two with swept wings of aspect ratio 3. Results regarding drag, lift, pressure distributions, and tests with the body alone are provided.
Date: May 16, 1957
Creator: McDevitt, John B. & Taylor, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen