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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Free-spinning-tunnel investigation of a 1/28-scale model of the North American FJ-4 airplane : TED No. NACA AD-3112

Free-spinning-tunnel investigation of a 1/28-scale model of the North American FJ-4 airplane : TED No. NACA AD-3112

Date: February 11, 1958
Creator: Healy, Frederick M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical Treatment of Normal Condensation Shock

Analytical Treatment of Normal Condensation Shock

Date: July 1, 1947
Creator: Heybey
Description: The condensation of water vapor in an air consequences: acquisition of heat (liberated heat vaporization; loss of mass on the part of the flowing gas (water vapor is converted to liquid); change in the specific gas constants and of the ratio k of the specific heats (caused by change of gas composition). A discontinuous change of state is therefore connected with the condensation; schlieren photographs of supersonic flows in two-dimensional Laval nozzles show two intersecting oblique shock fronts that in the case of high humidities may merge near the point of intersection into one normal shock front.
Contributing Partner: UNT Libraries Government Documents Department
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