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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Description and investigation of a dynamic model of the XH-17 two-blade jet driven helicopter

Description and investigation of a dynamic model of the XH-17 two-blade jet driven helicopter

Date: March 14, 1951
Creator: Brooks, George W & Sylvester, Maurice A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A description and test results of a spark-ignition and a compression-ignition 2-stroke-cycle engine

A description and test results of a spark-ignition and a compression-ignition 2-stroke-cycle engine

Date: January 1, 1935
Creator: Spanogle, J A & Whitney, E G
Description: This report presents performance results of air cooled and water-cooled engines. The results obtained were sufficiently promising to warrant further investigation with fuel injection and spark ignition, with the same arrangement of inlet ports and exhaust valves at the bottom of the cylinder and the exhaust gases discharged through two poppet valves in the cylinder head. The displacement of the engine was 118 cubic inches. Optimum performance was obtained with the inlet air directed into the cylinder at an angle of 20 degrees to the radial.
Contributing Partner: UNT Libraries Government Documents Department
Design and investigation of a transonic axial-flow compressor rotor with an inlet hub-tip radius ratio of essentially zero

Design and investigation of a transonic axial-flow compressor rotor with an inlet hub-tip radius ratio of essentially zero

Date: March 11, 1957
Creator: Westphal, Willard R & Maynard, John W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design charts for flat compression panels having longitudinal extruded Y-section stiffeners and comparison with panels having formed Z-section stiffeners

Design charts for flat compression panels having longitudinal extruded Y-section stiffeners and comparison with panels having formed Z-section stiffeners

Date: August 1, 1947
Creator: Dow, Norris F & Hickman, William A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of indicial lift and moment of a two-dimensional pitching airfoil at subsonic mach numbers from oscillatory coefficients with numerical calculations for a Mach number of 0.7

Determination of indicial lift and moment of a two-dimensional pitching airfoil at subsonic mach numbers from oscillatory coefficients with numerical calculations for a Mach number of 0.7

Date: February 1, 1952
Creator: Mazelsky, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of induced velocity in front of an inclined propeller by a magnetic-analogy method

Determination of induced velocity in front of an inclined propeller by a magnetic-analogy method

Date: February 1, 1946
Creator: Lahatte, James A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of jet-boundary corrections to cowling-flap-outlet pressures by an electrical analogy method

Determination of jet-boundary corrections to cowling-flap-outlet pressures by an electrical analogy method

Date: February 1, 1944
Creator: Finn, Robert S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of longitudinal stability and control characteristics from free-flight model tests with results at transonic speeds for three airplane configurations

Determination of longitudinal stability and control characteristics from free-flight model tests with results at transonic speeds for three airplane configurations

Date: January 1, 1957
Creator: Gillis, Clarence L & Mitchell, Jesse L
Description: A test technique and data analysis method has been developed for determining the longitudinal aerodynamic characteristics from free-flight tests of rocket-propelled models. The technique makes use of accelerometers and an angle-of-attack indicator to permit instantaneous measurements of lift, drag, and pitching moments. The data, obtained during transient oscillations resulting from control-surface disturbances, are analyzed by essentially nonlinear direct methods (such as cross plots of the variation of lift coefficient with angle of attack) and by linear indirect methods by using the equations of motion for a transient oscillation. The analysis procedure has been set forth in some detail and the feasibility of the method has been demonstrated by data measured through the transonic speed range on several airplane configurations. It was shown that the flight conditions and dynamic similitude factors for the tests described were reasonably close to typical full-scale airplane conditions.
Contributing Partner: UNT Libraries Government Documents Department
Determination of lateral-stability derivatives and transfer-function coefficients from frequency-response data for lateral motions

Determination of lateral-stability derivatives and transfer-function coefficients from frequency-response data for lateral motions

Date: January 1, 1955
Creator: Donegan, James J; Robinson, Samuel W , Jr & Gates, Ordway, B , jr
Description: A method is presented for determining the lateral-stability derivatives, transfer-function coefficients, and the modes for lateral motion from frequency-response data for a rigid aircraft. The method is based on the application of the vector technique to the equations of lateral motion, so that the three equations of lateral motion can be separated into six equations. The method of least squares is then applied to the data for each of these equations to yield the coefficients of the equations of lateral motion from which the lateral-stability derivatives and lateral transfer-function coefficients are computed. Two numerical examples are given to demonstrate the use of the method.
Contributing Partner: UNT Libraries Government Documents Department
Determination of longitudinal stability in supersonic accelerated maneuvers for the Douglas D-558-II research airplane

Determination of longitudinal stability in supersonic accelerated maneuvers for the Douglas D-558-II research airplane

Date: February 17, 1954
Creator: Ankenbruck, Herman O
Description: None
Contributing Partner: UNT Libraries Government Documents Department