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UNT Libraries Government Documents Department
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NACA Aircraft Circulars
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Technical Report Archive and Image Library
Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade
Date: January 1, 1945
Creator: Zimmey, Charles M.
Description: As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axfax-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0 deg to 80 deg starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimentally designed blower blades in a stationary cascade at low Mach numbers. The turning effectiveness and the pressure distributions of these blade sections at various angles of attack were evaluated over a range of solidities near 1. Entrance-vane design charts are presented that give a blade section and angle of attack for any desired turning angle. The blades thus obtained operate with peak-free pressure distributions. Approximate critical Mach numbers were calculated from the pressure distributions.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc63062/
The De Havilland D.H. 75 "Hawk Moth" (British): Cabin Monoplane
Date: March 1, 1929
Creator: unknown
Description: The Hawk Moth is designed as a passenger aircraft with comfort in mind. It seats 4. The tail is of metal construction, while the wings are of wood. It has a total loaded weight of 3500 lbs.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc65098/
Determination of Flight Paths of an SBD-1 Airplane in Simulated Diving Attacks, Special Report
Date: March 1, 1943
Creator: Johnson, Harold I.
Description: An investigation has been made to determine the motions of and the flight paths describe by a Navy dive-bombing airplane in simulated diving attacks. The data necessary to evaluate these items, with the exception of the atmospheric wind data, were obtained from automatic recording instruments installed entirely within the airplane. The atmospheric wind data were obtained from the ground by the balloon-theodolite method. The results of typical dives at various dive angles are presented in the form of time histories of the motion of the airplane as well as flight paths calculated with respect to still air and with respect to the ground.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc65195/
The determination of span load distribution at high speeds by use of high-speed wind-tunnel section data
Date: February 1, 1944
Creator: Boshar, John
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61274/
Determination of the effect of horizontal-tail flexibility on longitudinal control characteristics
Date: February 1, 1945
Creator: Harmon, S M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61496/
Determination of the stability and control characteristics of a straight-wing, tailless fighter-airplane model in the Langley free-flight tunnel
Date: February 1, 1946
Creator: Ankenbruck, Herman O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61003/
Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel
Date: February 1, 1945
Creator: Seacord, Charles L.
Description: Force and flight tests were performance on an all-wing model with windmilling propellers. Tests were conducted with deflected and retracted flaps, with and without auxiliary vertical tail surfaces, and with different centers of gravity and trim coefficients. Results indicate serious reduction of stick-fixed longitudinal stability because of wing-tip stalling at high lift coefficient. Directional stability without vertical tail is undesirably low. Low effective dihedral should be maintained. Elevator and rudder control system is satisfactory.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc60992/
Development of Wing Inlets
Date: March 1, 1946
Creator: Racisz, Stanley F.
Description: Lift, drag, internal flow, and pressure distribution measurements were made on a low-drag airfoil incorporating various air inlet designs. Two leading-edge air inlets are developed which feature higher lift coefficients and critical Mach than the basic airfoil. Higher lift coefficients and critical speeds are obtained for leading half of these inlet sections but because of high suction pressures near exist, slightly lower critical speeds are obtained for the entire inlet section than the basic airfoil.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61340/
The Dornier Do K commercial airplane (German) : a high-wing cantilever monoplane
Date: January 1, 1932
Creator: Heinze, Edwin P A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64435/
The "Dornier Mercury" commercial airplane with B.M.W. VI 600 HP. engine
Date: February 1, 1927
Creator: unknown
Description: The Dornier Mercury (Merkur) is an outgrowth of the Dornier Komet. It is designed as a passenger aircraft with the Alpine routes in mind. Its fuselage is made of steel for high stressed parts and duraluminum for all others. It can also be outfitted as a seaplane.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62568/