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469
Vibration Survey of Blades in 19XB Axial-Flow Compressor 2: Dynamic Investigation
"Strain-gage measurements were taken under operating conditions from blades of various stages of the 19XB axial-flow compressor in an effort to determine the reason for failures in the seventh and tenth stages. First bending-mode vibrations were detected in the first five stages of the compressor caused by each integral multiple of rotor speed from three through ten. Lead-wire failures in the last five stages resulted in incomplete data" (p. 1).
Date:
April 9, 1947
Creator:
Meyer, André J., Jr. & Calvert, Howard F.
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines: 4 - Analysis of Compressor Performance
"Investigations were conducted in the Cleveland altitude wind tunnel to determine the performance and operational characteristics of the 19B-2, 19B-8, and 19XS-1 turbojet engines. One objective was to determine the effect of altitude, flight Mach number, and tail-pipe-nozzle area on the performance characteristics of the six-stage and ten-stage axial-flow compressors of the 19B-8 and 19XB-1 engines, respectively, The data were obtained over a range of simulated altitudes and flight Mach numbers" (p. 1).
Date:
April 25, 1947
Creator:
Dietz, Robert O. & Kuenzig, John K.
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet Propulsion Engines, 4 - Performance and Windmilling Drag Characteristics
The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag characteristics of the 19B-6 engine were determined in the Cleveland altitude wind tunnel. The investigations were conducted on the 19B-8 engine at simulated altitudes from 5000 to 25,000 feet with various free-stream ram-pressure ratios and on the 19XB--1 engine at simulated altitudes from 5000 to 30,000 feet with approximately static free-stream conditions.
Date:
April 9, 1947
Creator:
Fleming, William A. & Dietz, Robert O., Jr.
System:
The UNT Digital Library
Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 5 - Effect on Over-All Performance Characteristics of a 20-Percent Reduction in Solidity of the Fourteenth Through Sixteenth Stage Rotors
The performance of a 16-stage axial-flow compressor, in which the mean-radius solidity was reduced from 1.28 to 1.02 in the fourteenth through sixteenth stage rotors was determined. The performance of this modification was compared with that of the compressor with original rotors. The reduced solidity resulted in slightly improved performance.
Date:
April 21, 1952
Creator:
Medeiros, Arthur A. & Hatch, James E.
System:
The UNT Digital Library
Take-Off Stability Characteristics of a 1/13-Scale Model of the Consolidated Vultee Skate 7 Seaplane (TED No. NACA DE 338)
The take-off stability characteristics of a Consolidated Vultee Aircraft Corporation Skate 7 seaplane were determined in the Langley tank no. 2. Trim limits of stability, trim tracks, and elevator limits of stability are presented.
Date:
April 27, 1949
Creator:
McKann, Robert; Coffee, Claude W. & Arabian, Donald D.
System:
The UNT Digital Library
An Evaluation of the Roll-Rate Stabilization System of the Sidewinder Missile at Mach Numbers from 0.9 to 2.3
"A linear stability analysis and flight-test investigation has been performed on a rolleron-type roll-rate stabilization system for a canard-type missile configuration through a Mach number range from 0.9 to 2.3. This type damper provides roll damping by the action of gyro-actuated uncoupled wing-tip ailerons. A dynamic roll instability predicted by the analysis was confirmed by flight testing and was subsequently eliminated by the introduction of control-surface damping about the rolleron hinge line" (p. 1).
Date:
April 22, 1955
Creator:
Nason, Martin L.; Brown, Clarence A., Jr. & Rock, Rupert S.
System:
The UNT Digital Library
Free-Flight Zero-Lift Drag Results from a 1/5-Scale Model and Several Small-Scale Equivalent Bodies of Revolution of the Convair F-102 Configuration at Mach Numbers up to 1.34
From Summary: "A 1/5-scale, rocket-propelled model of the Convair F-102 configuration was tested in free flight to determine zero-lift drag at Mach numbers up to 1.34 and at Reynolds numbers comparable to those of the full-scale airplane. This large-scale model corresponded to the prototype airplane and had air flow through the duct. Additional zero-lift drag tests involved a series of small equivalent bodies of revolution which were launched by means of a helium gun."
Date:
April 14, 1954
Creator:
Wallskog, Harvey A.
System:
The UNT Digital Library
Performance of a 13-Stage Development Compressor for the J40-WE-24 Engine at Equivalent Speeds from 30 to 112 Percent of Design
The performance of a 13-stage development compressor for the J40-WE-24 engine has been determined at equivalent speeds from 30 to 112 percent of design. The design total-pressure ratio of 6.0 and the design weight flow of 164 pounds per second were not attained, An analysis was conducted to determine the reasons for the poor performance at the design and over-design speed. The analysis indicated that most of the difficulty could be attributed to the fact that the first stage was overcompromised to favor part-speed performance,.
Date:
April 9, 1953
Creator:
Hatch, James E.; Lucas, James G. & Finger, Harold B.
System:
The UNT Digital Library
Experimental Investigation of Vibratory Stresses in a Concentric-Ring Direct-Air-Cycle Nuclear Fuel Element
"Preliminary tests made by the General Electric Company indicated that aerodynamic loads might cause large enough distortions in the thin sheet-metal rings of a nuclear fuel element to result in structural failure. The magnitude of the distortions in a test fuel element was determined from strains measured with airflow conditions simulating those expected during engine operation. The measured vibratory strains were low enough to indicate the improbability of failure by fatigue. A conservative estimate of the radial deflection that accompanied peak strains in the outer ring was +0.0006 inch" (p. 1).
Date:
April 17, 1957
Creator:
Chiarito, Patrick T.
System:
The UNT Digital Library
Flight Investigation of the Effect of a Propulsive Jet Positioned According to the Transonic Area Rule on the Drag Coefficients of a Single-Engine Delta-Wing Configuration at Mach Numbers From 0.83 to 1.36
Report discussing testing of a 60 degree delta-wing configuration with an engine located in a pod contiguous to the underside of the fuselage to determine the effects of the flow field and drag, lift, and longitudinal stability. Jet-on drag coefficients were found to be lower than jet-off drag coefficients at transonic speeds. The transonic-area-rule concept was also found to be viable for predicting jet effects on drag for this type of configuration.
Date:
April 13, 1956
Creator:
Judd, Joseph H. & Falanga, Ralph A.
System:
The UNT Digital Library
Wind-tunnel investigation of the damping in roll of the Bell X-1E research airplane and its components at supersonic speeds
Experimental values of damping in roll at zero angle of attack of the Bell X-1E research airplane and various combinations of components were obtained at 5 different Mach numbers. The damping in roll of the model was of the order predicted by theory. Results regarding the contributions of the airplane components and comparisons of experimental values with theoretical values are provided.
Date:
April 26, 1956
Creator:
McDearmon, Russell W. & Clark, Frank L.
System:
The UNT Digital Library
Lateral-Stability Flight Test of a 0.125-Scale Rocket-Propelled Model of the Mcdonnell F-101A Airplane at Mach Numbers from 1.0 to 1.9
"A rocket-propelled model of the McDonnell F-101A airplane was tested in free flight for its lateral stability characteristics. The 0.125-scale model was equipped with six pulse rockets to produce the lateral disturbances. The center of gravity was located at 17.3 percent of the mean aerodynamic chord. The method of analysis was based on lateral-force and moment vector diagrams which trigonometrically solved for the resultants" (p. 1).
Date:
April 17, 1956
Creator:
Hollinger, James A. & Coltrane, Lucille C.
System:
The UNT Digital Library
Component performance investigation of J71 experimental turbine 1: Over-all performance with 97-percent-design stator areas
From Summary: "The over-all component performance characteristics of a J71 experimental three-stage turbine with 97 percent design stator areas were determined over a range of speed and pressure ratio at inlet-air conditions of approximately 35 inches of mercury absolute and 700 degrees R. The turbine break internal efficiency at design operating conditions was 0.877; the maximum efficiency of 0.886 occurred at a pressure ratio of 4.0 at 120 percent of design equivalent rotor speed. In general, the turbine yielded a wide range of efficient operation, permitting flexibility in the choice of different modes of engine operation."
Date:
April 11, 1956
Creator:
Schum, Harold J. & Davison, Elmer H.
System:
The UNT Digital Library