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A study of service-imposed maneuvers of four jet fighter airplanes in relation to their handling qualities and calculated dynamic characteristics
Report presenting results from a flight program conducted to obtain information on the airplane response and actual rates and amounts of control motion used by service pilots to perform squadron operational training missions, which are correlated with the airplane handling qualities and calculated maximum dynamic response. Results regarding longitudinal characteristics, rolling characteristics, and sideslip characteristics are provided.
Date:
August 15, 1955
Creator:
Mayer, John P. & Hamer, Harold A.
System:
The UNT Digital Library
Altitude performance of compressor, combustor, and turbine components of XT38-A-2 turboprop engine
From Introduction: "The overall performance and operational characteristics are reported in reference 1. The performance of the components (compressor, combustor, turbine) is reported herein."
Date:
August 27, 1954
Creator:
Schulze, Frederick W. & Prince, William R.
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
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
Investigation of a 10-stage subsonic axial-flow research compressor 4: performance evaluation and flow distributions in the first, fifth, and tenth stages
Report presenting a determination of the performance and flow distributions in the first, fifth, and tenth stages of a 10-stage axial-flow research compressor at design and part speed in order to study the validity of the compressor design assumptions and to show the effects of part-speed compressor operation on stage performance.
Date:
August 6, 1954
Creator:
Budinger, Ray E.
System:
The UNT Digital Library
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
Performance of a 16-inch ram-jet engine with a can-type combustor at Mach numbers of 1.50 to 2.16
Report presenting an investigation in the supersonic wind tunnel to evaluate the performance of a 16-inch ramjet engine using a can-type-combustor configuration. Data were obtained over a range of fuel-air ratios, free-stream Mach numbers, and angles of attack. Combustion efficiencies were generally unaffected by free-stream Mach number and varied between 60 and 90 percent with JP-4 fuel.
Date:
August 27, 1954
Creator:
Hearth, Donald P. & Perchonok, Eugene
System:
The UNT Digital Library
Static Longitudinal Stability Characteristics of a Composite-Plan-Form-Wing-Model Including Some Comparisons with a 45 Degree Sweptback Wing at Transonic Speeds
Memorandum presenting an investigation made to determine the low-subsonic-speed static longitudinal stability characteristics of a composite-plan-form wing tested as a wing-fuselage combination and as a complete model. Also included is a comparison of the transonic-speed characteristics of the composite-plan-form wing alone and the 45 degree sweptback wing from which the composite wing was derived.
Date:
August 18, 1954
Creator:
Wolhart, Walter D.
System:
The UNT Digital Library
Effects of Canopy, Revised Vertical Tail, and a Yaw-Damper Vane on the Aerodynamic Characteristics of a 1/16-Scale Model of the Douglas D-558-II Research Airplane at a Mach Number of 2.01
Report discussing the aerodynamic characteristics in pitch and sideslip of a model of a Douglas D-558-II airplane with and without a yaw-damper vane at Mach number 2.01. A revised model was tested using a canopy and modified vertical tail. The revised configuration was found to have higher directional stability, trim lift coefficients, drag, and more positive effective dihedral than the original configuration.
Date:
August 30, 1954
Creator:
Robinson, Ross B.
System:
The UNT Digital Library
Performance characteristics of an underslung vertical-wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
Performance characteristics of underslung vertical wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0.
Date:
August 3, 1956
Creator:
Allen, John L. & Piercy, Thomas G.
System:
The UNT Digital Library
Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds
Report discussing available wind-tunnel data on low-speed horizontal-tail contribution to the static longitudinal stability of high-speed airplane configurations with unswept and sweptback wings. The effects of variations of tail position, wing plan form, airfoil section, trailing-edge flaps, stall-control devices, and ground interference on air-flow characteristics an tail contribution are also described.
Date:
August 23, 1955
Creator:
Neely, Robert H. & Griner, Roland F.
System:
The UNT Digital Library
Low-Speed Wind-Tunnel Tests of a 1/8-Scale Model of the Bell D-188A VTOL Airplane
Report discussing the results of an investigation to determine the low-speed power-off stability and control characteristics of a model of the Bell D-188A VTOL airplane. The static stability and control characteristics were generally satisfactory except above certain angles of attack and aileron effectiveness dropped off as the angle of attack was increased. Modifications for increasing the directional stability by altering the vertical tails are also described.
Date:
August 1, 1958
Creator:
McKinney, Marion O. & Smith, Charles C., Jr.
System:
The UNT Digital Library
Low-Speed Investigation of the Effect of Small Canard Surfaces on the Directional Stability of a Sweptback-Wing Fighter-Airplane Model
Memorandum presenting a low-speed investigation in the free-flight tunnel to determine the effect of small canard surfaces on the directional stability of a fighter-airplane model with an aspect ratio of 3.4 and a 42 degree sweptback wing. The canard surfaces were found to be generally ineffective at angles of attack below 20 degrees.
Date:
August 23, 1956
Creator:
Paulson, John W. & Boisseau, Peter C.
System:
The UNT Digital Library
An Investigation of the Dynamic and Static Stability Characteristics of a Group of Specialized Store Configurations at Transonic Speeds
Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.
Date:
August 21, 1953
Creator:
Henry, Beverly Z., Jr. & Braden, John A.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane
Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.
Date:
August 25, 1954
Creator:
Wolhart, Walter D. & Fletcher, H. S.
System:
The UNT Digital Library
Development of a Supersonic Area Rule and an Application to the Design of a Wing-Body Combination Having High Lift-to-Drag Ratios
Report presenting a concept for interrelating the wave drag of wing-body combinations at moderate supersonic speeds with axial distributions of cross-sectional area has been developed. Details of preliminary experiments meant to test the concept are also provided.
Date:
August 18, 1953
Creator:
Whitcomb, Richard T. & Fischetti, Thomas L.
System:
The UNT Digital Library
Natural Icing of an Axial-Flow Turbojet Engine in Flight for a Single Icing Condition
Memorandum presenting an investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. A description of the change over time in tail-pipe temperature, engine jet thrust, fuel flow, ice collection, and acceleration qualities are provided.
Date:
August 12, 1948
Creator:
Acker, Loren W.
System:
The UNT Digital Library
Preliminary Results of Natural Icing of an Axial-Flow Turbojet Engine
Memorandum presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Tail-pipe temperature increased from 761 to 1065 degrees Fahrenheit and the jet thrust decreased from 1234 to 910 pounds during a period of 45 minutes in icing. No general conclusions can be reached from the data because the icing condition was relatively light.
Date:
August 6, 1948
Creator:
Acker, Loren W.
System:
The UNT Digital Library
Transonic Wind-Tunnel Investigation of Static-Pressure Fluctuations in Duct of a Scale Inlet Model of a Supersonic Fighter-Bomber Airplane
Report presenting a transonic investigation of the static-pressure fluctuations in the left duct of a scale inlet model of a supersonic fighter-bomber airplane in the transonic tunnel. Results regarding amplitude characteristics of pressure fluctuations, power-spectral analyses, and flow distortions at compressor face are provided.
Date:
August 6, 1957
Creator:
Brooks, Joseph D.
System:
The UNT Digital Library
Preliminary Analysis of Performance of Turbojet Engines Used as Pumps for Boundary-Layer Control
Memorandum presenting a determination of the effects on engine performance of using turbojet engines for boundary-layer control by suction at the engine inlet or by bleeding air from the compressor outlet for three current production engines. Results regarding bleed, suction, and variable-area turbine are provided.
Date:
August 16, 1955
Creator:
Conrad, E. William
System:
The UNT Digital Library
Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls
Report presenting an investigation to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and all-movable control surfaces. Testing indicated that all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. Some of the configurations tested include body alone, body with 5 degree fins and trailing-edge flaps, and body with 10 degree flare and all-movable controls.
Date:
August 4, 1958
Creator:
Robinson, Ross B. & Bernot, Peter T.
System:
The UNT Digital Library
Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Lateral, Directional, and Additional Longitudinal Static Stability and Control
Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 at Mach numbers from 0.60 to 1.13. The primary focus of this report are the static lateral and directional stability and control characteristics of the model. Results regarding force and moment results, longitudinal characteristics, lateral and directional characteristics.
Date:
August 23, 1957
Creator:
Luoma, Arvo A.
System:
The UNT Digital Library
Preliminary Results of Heat Transfer from a Stationary and Rotating Ellipsoidal Spinner
"Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 4 degrees. The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures" (p. 1).
Date:
August 6, 1953
Creator:
von Glahn, U.
System:
The UNT Digital Library
Stability of Ballistic Reentry Bodies
Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date:
August 11, 1958
Creator:
Bird, John D. & Reese, David E., Jr.
System:
The UNT Digital Library
Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands
Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
Date:
August 11, 1958
Creator:
Cheatham, Donald C. & Brissenden, Roy F.
System:
The UNT Digital Library