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Flight investigation of the heat requirements for ice prevention on aircraft windshields

Description: Report presenting a flight investigation conducted to establish the heat requirements for ice prevention on aircraft windshields mounted on the forebody of an airplane at several angles. Electrically heated windshields were used in order to provide accurate measuring of heat input to the windshield. Results regarding the quantity of heat provided, amount of water collection, ideal windshield angle, ranges in airplane velocity, and icing conditions are provided.
Date: September 5, 1947
Creator: Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Low-Speed Stalling and Lift Characteristics

Description: Report presenting the low-speed stalling and lift characteristics of the Douglas D-558-II airplane measured in a series of 1 g stalls in four different airplane configurations. Various combinations of landing gear, flaps, inlet-duct flaps, and slats were tested at a range of altitudes.
Date: September 5, 1950
Creator: Stillwell, W. H.; Wilmerding, J. V. & Champine, R. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests at Supersonic Speeds to Determine the Effect of Taper on the Zero-Lift Drag of Sweptback Low-Aspect-Ratio Wings

Description: Report presenting testing using rocket-powered models to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings with thin, symmetrical, double-wedge airfoil sections. The theory compared favorably with experimental results over most of the test range. Taper was generally found to increase wing drag at low supersonic speeds but reduced drag at higher speeds.
Date: September 5, 1950
Creator: Pittel, Murray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Performance of a J47D (RX1-1) turbojet engine equipped with afterburner, variable-area exhaust nozzle, and integrated electronic control was determined over a range of flight conditions. These data were obtained with the electronic control both operative and inoperative. For operation with scheduled exhaust nozzle area, the minimum specific fuel consumption of 1.15 pounds of fuel per hour per pound of net thrust occurred at about 7200 rpm at altitudes from 5000 to 25,000 feet at a flight Mach n… more
Date: September 5, 1951
Creator: Conrad, E. William & McAulay, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of a Wedge With Various Holder Configurations for Static-Pressure Measurements in Subsonic Gas Streams

Description: The characteristics of a wedge static-pressure sensing element with various holder configurations were determined and compared with the characteristics of the conventional tube. The probes were tested over a range of Mach number from 0.3 to 0.95 and at various pitch and yaw angles. The investigation showed that the spike-mounted wedge sensing element has a pressure coefficient comparable with the conventional subsonic static-pressure probe and the pressure coefficient of the wedge varied less t… more
Date: September 5, 1951
Creator: Gettelman, Clarence C. & Krause, Lloyd N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of dynamic characteristics of a turbine-propeller engine

Description: Time constants that characterize engine speed response of a turbine-propeller engine over the cruising speed range for various values of constant fuel flow and constant blade angle were obtained both from steady-state characteristics and from transient operation. Magnitude of speed response to changes in fuel flow and blade angle was investigated and is presented in the form of gain factors. Results indicate that at any given value of speed in the engine cruising speed range, time constants obt… more
Date: September 5, 1951
Creator: Oppenheimer, Frank L. & Jacques, James R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects of oscillation amplitude and frequency on the experimental damping in pitch of a triangular wing having an aspect ratio of 4

Description: Memorandum presenting the results of a wind-tunnel investigation of the damping in pitch of a model triangular wing with an aspect ratio of 4 combined with a slender pointed body. The investigation was conducted at Mach numbers from 0.10 to 0.95 for Reynolds numbers of 550,000 and 1,250,000 with additional data obtained at Reynolds numbers of 3,000,000 and 6,000,000 at Mach number 0.23. Results regarding the effects of oscillation amplitude, Mach number, Reynolds number, angle of attack, freque… more
Date: September 5, 1952
Creator: Beam, Benjamin H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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