You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
Preliminary results of natural icing of an axial-flow turbojet engine

Preliminary results of natural icing of an axial-flow turbojet engine

Date: August 6, 1948
Creator: Acker, L. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in fighter-airplane crashes

Accelerations in fighter-airplane crashes

Date: November 4, 1957
Creator: Acker, Loren W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Date: April 7, 1949
Creator: Acker, Loren W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions

Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions

Date: May 25, 1950
Creator: Acker, Loren W
Description: A flight investigation in natural icing conditions was conducted to determine the effect of inlet ice formations on the performance of axial-flow turbojet engines. The results are presented for icing conditions ranging from a liquid-water content of 0.1 to 0.9 gram per cubic meter and water-droplet size from 10 to 27 microns at ambient-air temperature from 13 to 26 degrees F. The data show time histories of jet thrust, air flow, tail-pipe temperature, compressor efficiency, and icing parameters for each icing encounter. The effect of inlet-guide-vane icing was isolated and shown to account for approximately one-half the total reduction in performance caused by inlet icing.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary results of natural icing of an axial-flow turbojet engine

Preliminary results of natural icing of an axial-flow turbojet engine

Date: August 6, 1948
Creator: Acker, Loren W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation

Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation

Date: February 14, 1947
Creator: Acker, Loren W.
Description: Flight and ground investigations have been made to compare an exhaust-ejector installation with a standard exhaust-collector-ring installation on air-cooled aircraft engines in a twin-engine airplane. The ground investigation allowed that, whereas the standard engine would have overheated above 600 horsepower, the engine with exhaust ejectors cooled at take-off operating conditions at zero ram. The exhaust ejectors provided as much cooling with cowl flaps closed as the conventional cowl flaps induced when full open at low airspeeds. The propulsive thrust of the exhaust-ejector installation was calculated to be slightly less than the thrust of the collector-ring-installation.
Contributing Partner: UNT Libraries Government Documents Department
Air forces on airfoils moving faster than sound

Air forces on airfoils moving faster than sound

Date: June 1, 1925
Creator: Ackeret, J
Description: We are undertaking the task of computing the air forces on a slightly cambered airfoil in the absence of friction and with an infinite aspect ratio. We also assume in advance that the leading edge is very sharp and that its tangent lies in the direction of motion.
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements of two thin wing sections at different index values

Drag measurements of two thin wing sections at different index values

Date: June 1, 1927
Creator: Ackeret, J
Description: It is stated that the index value 6000, as found in normal tests of wing sections with a 20 cm chord, falls in the same region where the transition of laminar to turbulent flow takes place on thin flat plates. It is to be expected that slightly cambered, thin wing sections will behave similarly. The following test of two such wing sections were made for the purpose of verifying this supposition.
Contributing Partner: UNT Libraries Government Documents Department
Experiments on airfoils with trailing edge cut away

Experiments on airfoils with trailing edge cut away

Date: September 1, 1927
Creator: Ackeret, J
Description: Airfoils with their trailing edge cut away are often found on aircraft, as the fins on the hulls of flying boats and the central section of the wings for affording better visibility. It was therefore of some interest to discover the effect of such cutaways on the lift and drag and on the position of the center of pressure. For this purpose, systematic experiments were performed on two different airfoils, a symmetrical airfoil and an airfoil of medium thickness, with successive shortenings of their chords.
Contributing Partner: UNT Libraries Government Documents Department
Experiments with an airfoil from which the boundary layer is removed by suction

Experiments with an airfoil from which the boundary layer is removed by suction

Date: August 1, 1926
Creator: Ackeret, J
Description: Our attempts to improve the properties of airfoils by removing the boundary layer by suction, go back to 1922. The object of the suction is chiefly to prevent the detachment of the boundary layer from the surface of the airfoil. At large angles of attack, such detachment prevents the attainment of the great lift promised by the theory, besides greatly increasing the drag, especially of thick airfoils. This report gives results of those experiments.
Contributing Partner: UNT Libraries Government Documents Department