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Analysis of Wind-Tunnel Stability and Control Tests in Terms of Flying Qualities in Full-Scale Airplanes
From Summary: "The analysis of results of wind-tunnel stability and control tests of powered airplane models in terms of the flying qualities of full-scale airplanes is advocated. In order to indicate the topics upon which comments are considered desirable in the report of a wind-tunnel stability and control investigation and to demonstrate the nature of the suggested analysis, the present NACA flying-qualities requirements are discussed in relation to wind-tunnel tests. General procedures for the estimation of flying qualities from wind-tunnel tests are outlined."
Date:
October 1943
Creator:
Kayten, Gerald G.
System:
The UNT Digital Library
The Comper "Mouse" Commercial Airplane (British): A Three-Seat Cabin Low-Wing Monoplane
Circular describing the Comper "Mouse" commercial airplane, which is a three-seat cabin low-wing monoplane. Details regarding the landing gear, wings, cabin, seating, fuselage, tail, power plant, controls, characteristics, performance, drawings, and photographs are provided.
Date:
October 1933
Creator:
unknown
System:
The UNT Digital Library
Correlation of exhaust-valve temperatures with engine operating conditions and valve design
Report presenting a theory regarding engine-cooling variables from a previous report, which was used as a basis for the development of a semi-empirical equation to correlate exhaust-valve temperature with engine conditions. Results regarding the determination of constants, influences of operating variables on mean effective gas temperatures, thermal-resistance factor, and accuracy of correlating equation are provided.
Date:
October 1945
Creator:
Zipkin, M. A. & Sanders, J. C.
System:
The UNT Digital Library
Fluid de-icing tests on a Chandler-Evans 1900 CPB-3 carburetor mounted on a Pratt & Whitney R-1830-C4 intermediate rear engine section
Report presenting an investigation of the icing and de-icing characteristics of a Pratt & Whitney R-1830 engine induction system. The current report covers a program to determine the most effective rate and method of injection of de-icing fluid to remove a heavy ice formation from the induction system. Results regarding the flow rates, recovery times, de-icing portions of the runs, and ice formation characteristics are provided.
Date:
October 1944
Creator:
Galvin, Herman B. & Essex, Henry A.
System:
The UNT Digital Library
Flight tests of thermal ice-prevention equipment in the XB-24F airplane
Report presenting performance tests of thermal ice-prevention equipment designed and installed in the XB-24F airplane in icing and non-icing conditions. The recorded temperature and air-flow data, and the calculated quantities of heat flow throughout the system are presented in tabular form.
Date:
October 7, 1943
Creator:
Neel, Carr B. & Jones, Alun R.
System:
The UNT Digital Library
Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings
Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.
Date:
October 7, 1953
Creator:
Radin, Edward J. & Carpenter, Paul J.
System:
The UNT Digital Library
Westland "Wessex" Commercial Airplane (British): A High-Wing Semicantilever Monoplane
Circular presenting a description of the Westland Wessex, which differs from other airplanes of its class because of the mounting of the outboard engines on outriggers from the fuselage and the placing of the engines in such a way that the slipstream does not interfere with the movement of the wing. A description of the design, flight characteristics, blueprints, and photographs are provided.
Date:
October 1930
Creator:
unknown
System:
The UNT Digital Library
Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26
Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.
Date:
October 30, 1953
Creator:
Martz, C. William & Goslee, John W.
System:
The UNT Digital Library
A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees
Report presenting a pressure-distribution investigation of a parabolic body of revolution with a fineness ratio of 12.2, which was performed in the 4- by 4-foot supersonic tunnel at Mach number 1.59 and Reynolds number 3.6 x 10(sub 6), based on body length, for a range of angles of attack. Results regarding basic pressures, aerodynamic coefficients, asymmetrical pressures, comparison of experimental and theoretical pressures, artificial roughness, section coefficients, and body coefficients are provided.
Date:
October 30, 1952
Creator:
Cooper, Morton; Gapcynski, John P. & Hasel, Lowell E.
System:
The UNT Digital Library
The Flow of a Compressible Fluid Past a Circular Arc Profile
Report presenting the use of the Ackeret iteration process to obtain higher approximations than that of Prandtl and Glauert for the flow of a compressible fluid past a circular arc profile. The procedure is to expand the velocity potential in a power series of the camber coefficient.
Date:
October 1944
Creator:
Kaplan, Carl
System:
The UNT Digital Library
The Caproni Monoplanes "Ca 97" (Italian)
The Ca 97 is constructed with wings half overhung, a large fuselage, all metal construction, and can be configured with 1 to 3 engines.
Date:
October 1928
Creator:
unknown
System:
The UNT Digital Library
The Fairchild "All-Purpose" Cabin Monoplane
The Fairchild "all-purpose" is a 4 seater with a large luggage compartment, good visibility, and can be configured for surveying work. It is rated at 200 HP. at 1800 R.P.M., but can deliver over 220 HP.
Date:
October 1927
Creator:
unknown
System:
The UNT Digital Library
Application of Spring Tabs to Elevator Controls
Report presenting equations for calculating the stick-force characteristics obtained with a spring-tab type of elevator control. The main problems encountered in the design of the satisfactory elevator spring tab are to provide stick forces in the desired range, to maintain the force per g sufficiently constant throughout the speed range, to avoid undesirable "feel" of the control in ground handling, and to prevent flutter.
Date:
October 1944
Creator:
Phillips, William H.
System:
The UNT Digital Library
The De Havilland "Tiger Moth": A Low Wing Monoplane
With a speed of 186.5 M.P.H. and an operational altitude of 20,000 feet the De Havilland Tiger Moth has caused comment as it was introduced just before the King's Cup race of 1927. It is a single seater with unusual control configuration due to the cramped cockpit area.
Date:
October 1927
Creator:
unknown
System:
The UNT Digital Library
Methods of Analyzing Wind-Tunnel Data for Dynamic Flight Conditions
"The effects of power on the stability and the control characteristics of an airplane are discussed and methods of analysis are given for evaluating certain dynamic characteristics of the airplane that are not directly discernible from wind-tunnel tests alone. Data are presented to show how the characteristics of a model tested in a wind tunnel are affected by power. The response of an airplane to a rolling and a yawing disturbance is discussed, particularly in regard to changes in wing dihedral and fin area" (p. 1).
Date:
October 1941
Creator:
Donlan, C. J. & Recant, I. G.
System:
The UNT Digital Library
Göttingen Six-Component Scale Measurements on a Junkers A 35 Airplane Model
The suggestion for the measurements collected in this report was prompted by the results of spinning experiments. For the theoretical spinning investigations there was a lack of data on lateral force, yawing, and rolling moment of airplanes.
Date:
October 1930
Creator:
Blenk, Hermann
System:
The UNT Digital Library
Combustion of Liquid Fuels in Diesel Engine
Hitherto, definite specifications have always been made for fuel oils and they have been classified as more or less good or non-utilizable. The present aim, however, is to build Diesel engines capable of using even the poorest liquid fuels and especially the waste products of the oil industry, without special chemical or physical preparation.
Date:
October 1924
Creator:
Alt, Otto
System:
The UNT Digital Library
Spindled and Hollow Spars
"The most usual method of arriving at the maximum amount of spindling or hollowing out permissible in the case of any particular spar section is by trial and error, a process which is apt to become laborious in the absence of good guessing - or luck. The following tables have been got out with the object of making it possible to arrive with certainty at a suitable section at the first attempt" (p. 1).
Date:
October 1926
Creator:
Blyth, J. D.
System:
The UNT Digital Library
Aerodynamic heating and the deflection of drops by an obstacle in an air stream in relation to aircraft icing
From Summary: "Two topics of interest to persons attempting to apply the heat method of preventing ice formation on aircraft are considered. Surfaces moving through air at high speed are shown, both theoretically and experimentally, to be subject to important aerodynamic heating effects that will materially reduce the heat required to prevent ice. Numerical calculations of the path of water drops in an air stream around a circular cylinder are given. From these calculations, information is obtained on the percentage of the swept area cleared of drops."
Date:
October 1940
Creator:
Kantrowitz, Arthur
System:
The UNT Digital Library
The Vickers "Vellore" (British): A Freight Carrier Which Carries a Load Greater Than Its Own Weight
The Vellore is a single engine biplane of all metal construction. It has a wing span of 76 feet and a loaded weight of 9,500 lbs. Details of the wingspan, construction, characteristics, performance, drawings, and photographs are provided.
Date:
October 1928
Creator:
unknown
System:
The UNT Digital Library
The De Havilland "Moth"
Officially designated D.H. 60, De Havilland's Moth is a small, simply made, 770 lb. aircraft. It has had it's fittings reduced in number to assist in this, seats 2 (including pilot) and uses a Cirrus 60 HP. engine.
Date:
October 1926
Creator:
unknown
System:
The UNT Digital Library
A laboratory investigation of the icing characteristics of the Bendix-Stromberg carburetor model PD-12F5 with the Pratt and Whitney R-1830-C4 intermediate rear engine section
Report presenting icing tests on a Bendix-Stromberg PD-12F5 carburetor mounted on a Pratt & Whitney R-1830-C4 intermediate rear engine section. Limiting icing conditions were established for simulated cruising power and simulated rated power over a range of carburetor-air temperatures, and relative humidities are provided.
Date:
October 1944
Creator:
Galvin, Herman B. & Essex, Henry A.
System:
The UNT Digital Library
The De Havilland "Comet" Long-Range Airplane (British): A Low-Wing Cantilever Monoplane
Circular describing the De Havilland Comet, which is a long-range airplane that has been designed for the England-Australia race and was constructed using a stressed-skin construction. Details of the fuselage, landing gear, design, drawings, and photographs are provided.
Date:
October 1934
Creator:
unknown
System:
The UNT Digital Library
Heat-Exchanger-Core Weights for Use With Hydrogen-Expansion Turbine
Memorandum presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. This is because rotary regenerators offer possibilities for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.
Date:
October 3, 1957
Creator:
Reynolds, Thaine W.
System:
The UNT Digital Library