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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
A comparison of the longitudinal aerodynamic characteristics at mach numbers up to 0.94 of swept back wings having NACA 4-digit or NACA 64A thickness distributions

A comparison of the longitudinal aerodynamic characteristics at mach numbers up to 0.94 of swept back wings having NACA 4-digit or NACA 64A thickness distributions

Date: August 23, 1954
Creator: Sutton, Fred B & Dickson, Jerald K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the effects of lip geometry on drag and pressure recovery of a normal-shock nose inlet on a body of revolution at Mach numbers of 1.41 and 1.81

Wind-tunnel investigation of the effects of lip geometry on drag and pressure recovery of a normal-shock nose inlet on a body of revolution at Mach numbers of 1.41 and 1.81

Date: February 3, 1958
Creator: Robins, A Warner
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Nozzles and Three Rotor-Blade Designs

Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Nozzles and Three Rotor-Blade Designs

Date: January 1, 1949
Creator: Schum, Harold J. & Whitney, Warren J.
Description: A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzles and three rotor-blade designs. The performance was evaluated in terms of brake, rotor, and blade efficiencies at pressure ratios of 8, 15 (design), and 20. The blade efficiencies with the two nozzles are compared with those obtained with four other nozzles previously investigated with the same three rotor-blade designs. Blade efficiency with the cast nozzle of rectangular cross section (J) was higher than that with the circular reamed nozzle (K) at all speeds and pressure ratios with a rotor having a 0.45-inch 17 degree-inlet-angle blades. The efficiencies for both these nozzles were generally low compared with those of the four other nozzles previously investigated in combination with this rotor. At pressure ratios of 15 and 20, the blade efficiencies with nozzle K and the two rotors with 0.40-inch blades having different inlet angles were higher than with the four other nozzles, but the efficiency with nozzle J was generally low. Increasing the blade inlet angle from 17 degrees to 20 degrees had little effect on turbine performance, whereas changing the blade length from 0.40 to 0.45 inch had ...
Contributing Partner: UNT Libraries Government Documents Department
Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes Within Thunderstorms August 14, 1946 to August 15, 1946 at Orlando, Florida

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes Within Thunderstorms August 14, 1946 to August 15, 1946 at Orlando, Florida

Date: March 19, 1947
Creator: Tolefson, H. B.
Description: Tables I and II of the present paper summarize the gust and draft velocity data for thunderstorm-flights 21 and 22 of August 14, 1946 and August 15, 1946, respectively. These data were evaluated from records of NACA airspeed-altitude and acceleration recorders installed in P-61C airplanes and are of the type presented for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient-air temperature during thunderstorm surveys. These data were read from photo-observer records and include all cases in which variations of the instrument indications were noted for the present flights.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary empirical design requirements for the prevention of tumbling of airplanes having no horizontal tails

Preliminary empirical design requirements for the prevention of tumbling of airplanes having no horizontal tails

Date: October 11, 1950
Creator: Bryant, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Cierva "Autogiro" Mark III (British) : Armstrong-Siddeley "Genet Major" Engine

The Cierva "Autogiro" Mark III (British) : Armstrong-Siddeley "Genet Major" Engine

Date: June 1, 1930
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a Hermes A-2 Missile Body at Mach Number 4.04

Tests of a Hermes A-2 Missile Body at Mach Number 4.04

Date: January 1, 1950
Creator: Ulmann, Edward F. & Lord, Douglas R.
Description: Force tests on a proposed body shape of the Hermes A-2 missile with and without longitudinal spoilers were made at Mach number 4.04. Values of normal force coefficient, pitching-moment coefficient, and center-of-pressure position were obtained.
Contributing Partner: UNT Libraries Government Documents Department
Damping in roll of rectangular wings of several aspect ratios and NACA 65A-series airfoil sections of several thickness ratios at transonic and supersonic speeds as determined with rocket-powered models

Damping in roll of rectangular wings of several aspect ratios and NACA 65A-series airfoil sections of several thickness ratios at transonic and supersonic speeds as determined with rocket-powered models

Date: August 24, 1950
Creator: Edmondson, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigations on the Stability, Oscillation, and Stress Conditions of Airplanes with Tab Control: First Partial Report. Derivation of the Equations of Motion and their General Solutions

Investigations on the Stability, Oscillation, and Stress Conditions of Airplanes with Tab Control: First Partial Report. Derivation of the Equations of Motion and their General Solutions

Date: September 1, 1949
Creator: Filzek, B.
Description: For the design and the construction of airplanes the control is of special significance, not only with regard to the flight mechhnical properties but also for the proportional arrangement of wing unit, fuselage, and tail unit. whereas these problems may be regarded as solved for direct control of airplane motions, that is, for immediate operation of the control surfaces, they are not clarified as to oscimtions, stability, and stress phenomena occurring in flight motions with Indirect control, ss realized for instance in tab control. Its modus operandi is based on the activation of a tab hinged to the trailing edge & the main control surface. Due to lift and drag variations, mcments originate about the axis of rotation of the main contnol surface which cause an up-or--down floating of the main control surface and thus a change in the direction of the airplane. Since this tab control means flying with free control surface , the treatment of this problem should provide the basis on which to judge stability, oscilhtton, and stress data.The present report is to represent a contribution toward the clarification of the problems arising and, to treat the longitudinal motion of an airplane.
Contributing Partner: UNT Libraries Government Documents Department
Longitudinal Stability Characteristics of a 1/40-Scale Model of a Proposed Configuration of the XF-91 Airplane Measured by the Wing-Flow Method

Longitudinal Stability Characteristics of a 1/40-Scale Model of a Proposed Configuration of the XF-91 Airplane Measured by the Wing-Flow Method

Date: January 1, 1948
Creator: Crane, Harold L. & Beckhardt, Arnold R.
Description: This report presents the results of an investigation in the transonic speed range of the longitudinal stability characteristics of a proposed configuration for the Republic XF-91 airplane. The tests covered a Mach number range of 0.55 to 1.05 and a Reynolds number range from 400,000 to 1,375,000. Lift, pitching-moment, and rolling-moment characteristics of the half model and the hinge moments on the all-moving tail were measured. The downwash factor delta x epsilon / delta x alpha at the tail was determined from the pitching-moment data. A calculation of the elevator deflection and stick force required for trim was also made. It was found that the variation of force and moment coefficients was linear through the test angle-of-attack range of -1 deg to 8 deg at any Mach number; that the stability increased markedly at Mach numbers above 0.85; that the effectiveness of the tail in producing pitching moments decreased about one-third with increasing Mach numbers and that the value of the downwash factor, delta x epsilon / delta x alpha, at the tail decreased from about 0.35 at a Mach number of 0.85 to about zero at a Mach number near 0.95 and became slightly negative at higher Mach numbers. ...
Contributing Partner: UNT Libraries Government Documents Department