Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane (open access)

Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane

Memorandum presenting rudder pulse maneuvers obtained with the Convair XF-92A delta-wing research airplane at an altitude of about 30,000 feet over a Mach number range of 0.52 to 0.92. Tests were made with and without a wing fence. By analyzing the maneuvers, the characteristics of the airplane transient, airplane stability derivatives, and frequency-response characteristics were measured.
Date: August 5, 1955
Creator: Holleman, Euclid C.
System: The UNT Digital Library
Investigation of the Effect of Balancing Tabs on the Hinge-Moment Characteristics of a Trailing-Edge Flap-Type Control on a Trapezoidal Wing at a Mach Number of 1.61 (open access)

Investigation of the Effect of Balancing Tabs on the Hinge-Moment Characteristics of a Trailing-Edge Flap-Type Control on a Trapezoidal Wing at a Mach Number of 1.61

Report presenting an investigation at Mach number 1.61 to determine the effect of 10-percent control are attached tabs on the hinge-moment characteristics of a trailing-edge flap-type control on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. Results regarding hinge-moment coefficients, tab parameters, and control effectiveness are provided.
Date: August 5, 1954
Creator: Lord, Douglas R. & Driver, Cornelius
System: The UNT Digital Library
Comparison Between Theoretical and Experimental Rates of Roll of Two Models with Flexible Rectangular Wings at Supersonic Speeds (open access)

Comparison Between Theoretical and Experimental Rates of Roll of Two Models with Flexible Rectangular Wings at Supersonic Speeds

"A comparison is presented between the experimentally measured and theoretically calculated (by the method of NACA TN 3067) rates of roll of two rocket-propelled models with flexible rectangular wings. The comparisons show that although there are large aeroelastic losses in rolling rate, the theory predicts the actual rate of roll accurately" (p. 1).
Date: August 5, 1954
Creator: Hedgepeth, John M. & Kell, Robert J.
System: The UNT Digital Library
Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3:  Ramjet engine performance (open access)

Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance

Report presenting ramjet engine performance data over a range of engine design variables to permit selection and evaluation of a ramjet engine configuration for a long-range supersonic missile. Results include engine thrust, drag, fuel consumption, area ratios, and weight, and are suitable for use in design studies of missiles incorporating either internally or externally mounted ramjet engines.
Date: August 5, 1954
Creator: Weber, Richard J. & Luidens, Roger W.
System: The UNT Digital Library
Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Plain Flap by the NACA Wing-Flow Method (open access)

Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Plain Flap by the NACA Wing-Flow Method

Report presenting measurements using the NACA wing-flow method of the lift, pitching-moment, and hinge-moment characteristics of a 35 degree sweptback NACA 65-009 airfoil of aspect ratio 3.04 with a full-span 1/4-chord unsealed plain flap. The tests were carried out at a range of Mach numbers, Reynolds numbers, angles of attack, and flap deflections. Variations of lift and pitching moment with angle of attack or flap deflection were approximately rectilinear at all Mach numbers for moderate angles of attack and flap deflections.
Date: August 5, 1947
Creator: Johnson, Harold I.
System: The UNT Digital Library
Calculative method for estimating the interference pressure field at zero lift on a symmetrical swept-back wing mounted on a circular cylindrical body (open access)

Calculative method for estimating the interference pressure field at zero lift on a symmetrical swept-back wing mounted on a circular cylindrical body

Report presenting an approximate method for calculating the interference pressure distribution at zero lift of a symmetrical sweptback wing mounted on a circular cylindrical body with the chord plane of the wing passing through the axis of the body. An example is provided using a circular cylindrical body and an untapered wing with 60 degrees of sweepback.
Date: August 5, 1949
Creator: Nielsen, Jack N. & Matteson, Frederick H.
System: The UNT Digital Library
Effects of simulated skin wrinkles on the wing surface on the aerodynamic characteristics of two wing-body combinations employing wings of low aspect ratio at subsonic and supersonic speeds (open access)

Effects of simulated skin wrinkles on the wing surface on the aerodynamic characteristics of two wing-body combinations employing wings of low aspect ratio at subsonic and supersonic speeds

Report presenting the results of an investigation to determine the effects of simulated skin wrinkling of the wing surface on the aerodynamic characteristics of two wing-body combinations. The lift, drag, and pitching moment of a low-wing wing-body combination with a plane triangular wing of aspect ratio 3 are presented for a range of Mach and Reynolds numbers.
Date: August 5, 1952
Creator: Heitmeyer, John C. & Smith, Willard G.
System: The UNT Digital Library
Aerodynamic characteristics of several tip controls on a 60 degree wing at a Mach number of 1.61 (open access)

Aerodynamic characteristics of several tip controls on a 60 degree wing at a Mach number of 1.61

Report presenting an investigation at a Mach number of 1.61 to determine the control effectiveness characteristics of seven tip controls on a 60 degree delta wing. Pressure distribution measurements were made for a range of angles of attack and control deflections. Results regarding the effect of control deflection, effect of wing angle of attack, effect of hinge-line location, effect of fences, and effect of control size and location are provided.
Date: August 5, 1954
Creator: Lord, Douglas R. & Czarnecki, K. R.
System: The UNT Digital Library
A Compilation of Summaries From NACA Reports on Fuels Research, 1945-1952 (open access)

A Compilation of Summaries From NACA Reports on Fuels Research, 1945-1952

Memorandum compiling summaries from NACA reports on fuel that were published between July 1945 and 1952. The summaries are intended to be detailed enough to eliminate the need to obtain the complete report.
Date: August 5, 1953
Creator: DiPiazza, J. T.
System: The UNT Digital Library
Experimental investigation of the effects of support interference on the pressure distribution of a body of revolution at a Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 14 x 10(exp 6) (open access)

Experimental investigation of the effects of support interference on the pressure distribution of a body of revolution at a Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 14 x 10(exp 6)

Report presenting an experimental investigation performed to determine the effect on base and forebody pressures of using a sting modified with varying length splitter plates and fins instead of a conventional sting to support a cone-cylinder body of revolution.
Date: August 5, 1953
Creator: Baughman, L. Eugene & Jack, John R.
System: The UNT Digital Library
Magnesium-slurry combustion performance in 6.5-inch-diameter ram-jet engine mounted in connected-pipe facility (open access)

Magnesium-slurry combustion performance in 6.5-inch-diameter ram-jet engine mounted in connected-pipe facility

Report presenting an investigation of the performance of slurry fuels consisting of 50 percent magnesium powder in a hydrocarbon carrier in a flight-type, 6.5-inch-diameter ramjet engine mounted in a connected-pipe facility. Results regarding the slurry performance and a comparison of slurry and ethylene performance are provided.
Date: August 5, 1953
Creator: Branstetter, J. Robert; Gibbs, James B. & Kaufman, Warner B.
System: The UNT Digital Library
Effect of Inlet Temperature on Rotating Stall and Blade Vibrations in a Multistage Axial-Flow Compressor (open access)

Effect of Inlet Temperature on Rotating Stall and Blade Vibrations in a Multistage Axial-Flow Compressor

Report presenting rotating-stall and blade-vibration data for the first three rotor blade rows of a 13-stage axial-flow compressor at several inlet temperatures. Stall patterns of 1 through 5 stall zones were detected at all inlet temperatures in the equivalent compressor speed ranges between 4600 and 6200 rpm.
Date: August 5, 1955
Creator: Medeiros, Arthur A.; Calvert, Howard F. & Fenn, David B.
System: The UNT Digital Library
Stall and flame-out resulting from firing of armament (open access)

Stall and flame-out resulting from firing of armament

Report presenting an analysis of the causes of compressor stall and flame-out when armament is fired during flight at high altitudes. Experimental data are also presented. The increase in compressor-inlet temperature during armament firing was found to be the most important single factor affecting engine performance.
Date: August 5, 1955
Creator: Childs, J. Howard; Kochendorfer, Fred D.; Lubick, Robert J. & Friedman, Robert
System: The UNT Digital Library
Langley Full-Scale-Tunnel Investigation of Maximum Lift and Stability Characteristics of an Airplane Having Approximately Triangular Plan Form (DM-1 Glider) (open access)

Langley Full-Scale-Tunnel Investigation of Maximum Lift and Stability Characteristics of an Airplane Having Approximately Triangular Plan Form (DM-1 Glider)

"An investigation of the DM-1 Glider, which had approximately triangular plan form, an aspect ratio of 1.8 and a 60 degree sweptback leading edge, has been conducted in the Langley full-scale tunnel. The investigation consisted of the determination of the separate effects of the following modifications made to the glider on its maximum lift and stability characteristics: (a) installation of sharp leading edges over the inboard semispan of the wing, (b) removal of the vertical fin, (c) sealing of the elevon control-balance slots, (d) installation of redesigned thin vertical surfaces, (e) installation of faired sharp leading edges, and (f) installation of canopy" (p. 1).
Date: August 5, 1947
Creator: Lovell, J. Calvin & Wilson, Herbert A., Jr.
System: The UNT Digital Library
Investigation of Sea-Level Performance of I-16 Turbojet Engine at Zero Ram with XFR-1 Intake Duct Shroud, and Tail Pipe (open access)

Investigation of Sea-Level Performance of I-16 Turbojet Engine at Zero Ram with XFR-1 Intake Duct Shroud, and Tail Pipe

The sea-level performance of I-16 turbojet engine at zero ram was investigated to determine the effects of an intake duct, shroud, and tail pipe intended for installation in an XFR-1 airplane. Engine speeds ranged from 8000 to 16,500 rpm for several variations of the intake duct and tail pipes.
Date: August 5, 1947
Creator: Dowman, Harry W. & Anderson, William G.
System: The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 4 - Analysis of Compressor Performance (open access)

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 4 - Analysis of Compressor Performance

Operating characteristics of the 11-stage 4000-pound-thrust axial-flow turbojet engine were determined. A standard compressor and a compressor with the blade angles of the rotor and stator blades increased 5 degrees to obtain greater air flow, were investigated.
Date: August 5, 1948
Creator: Dietz, Robert O., Jr. & Suozzi, Frank L.
System: The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 3, Performance Characteristics with the High-Flow Compressor (open access)

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 3, Performance Characteristics with the High-Flow Compressor

A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-flow turbojet engine with a high flow compressor. Pressure altitudes included 5000 to 40000 feet with ram pressure ratios from 1.00 to 1.82. Altitudes included 20000 to 40000 feet and ram pressure ratios from 1.09 to 1.75. A comparison is made between engine performance with high flow and low flow compressors.
Date: August 5, 1948
Creator: Fleming, William A. & Golladay, Richard L.
System: The UNT Digital Library