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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
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
System:
The UNT Digital Library
Effect of hot-gas bleedback ice prevention on performance of a turbojet engine with fixed-area tail-pipe nozzle
Report presenting the results of an analytical investigation, which demonstrated that the inlet of a turbojet engine can be protected from ice accretions by bleeding hot gases from other locations within the engine to the inlet without undue loss in thrust. Results regarding the bleedback requirements, engine performance, effect of nozzle area, mixing efficiency, and seriousness of thrust losses are provided.
Date:
May 16, 1949
Creator:
Dietz, Robert O., Jr. & Krebs, Richard P.
System:
The UNT Digital Library
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
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.
System:
The UNT Digital Library
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
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.
System:
The UNT Digital Library
An investigation of wing-body juncture interference effects at transonic speeds for several swept-wing and body combinations
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.
System:
The UNT Digital Library
A Wind-Tunnel Investigation of the Low-Amplitude Damping in Yaw and Directional Stability of a Fuselage-Tail Configuration at Mach Numbers Up to 1.10
Report presenting a low-amplitude free-oscillation investigation at zero angle of attack of the damping in yaw and directional stability of a fuselage-tail configuration through a range of reduced frequency. The damping in yaw was found to decrease with Mach numbers above 0.8 and became the lowest at about 1.0. An increase in reduced frequency was observed to cause a decrease in damping in yaw and directional stability for the test frequency range.
Date:
May 16, 1957
Creator:
Palmer, William E.
System:
The UNT Digital Library
Relation of Currently Estimated ANP Performance to Required ANP Performance
Memorandum presenting an investigation of performance estimates of aircraft nuclear propulsion (ANP) systems. This paper includes a relation of current estimated ANP performance to the future requirements that nuclear propulsion systems will be required to meet.
Date:
May 16, 1957
Creator:
Rothrock, Addison M. & Cesaro, Richard S.
System:
The UNT Digital Library
Relation of currently estimated ANP performance to required ANP performance
Report presenting a comparison of performance estimates of aircraft nuclear propulsion (ANP) systems and an attempt to determine the manner in which the estimated nuclear propulsion system performance in conjunction with the estimated airframe performance will lead to a useful military airplane.
Date:
May 16, 1957
Creator:
Rothrock, Addison M. & Cesaro, Richard S.
System:
The UNT Digital Library
Effect of sliding velocity on friction properties and endurance life of bonded lead monoxide coatings at temperatures up to 1250 degrees F
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.
System:
The UNT Digital Library
Criterions for prediction and control of ram-jet flow pulsations
Report presenting the results of a theoretical and experimental study of ramjet diffuser flow pulsing, commonly referred to as a buzz condition, with and without combustion. The acoustical resonance properties of ram jets are an important factor in establishing the frequency of diffuser flow pulsations.
Date:
May 16, 1951
Creator:
Sterbentz, William H. & Evvard, John C.
System:
The UNT Digital Library
Effect of Engine Skew on Directional and Lateral Control Characteristics of Single-Engine Airplanes
Report discussing an investigation on the effect of engine skew on the directional and lateral control characteristics of a single-engine airplane with a single-rotating propeller. The estimated and test results showed an advantage to skewing the propeller, as it assists with overcoming inadequate rudder control in power-on flight and aileron control, especially with flaps deflected.
Date:
May 16, 1947
Creator:
Wallace, Arthur R. & Comenzo, Raymond J.
System:
The UNT Digital Library