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 Decade: 1940-1949
 Year: 1943
 Collection: National Advisory Committee for Aeronautics Collection
Experimental Investigation of a Model of a Two-Stage Turboblower

Experimental Investigation of a Model of a Two-Stage Turboblower

Date: April 1, 1943
Creator: Dovjik, s. & Polikovsky, W.
Description: In the present paper an investigation is made of two stages of a multistage turboblower having a vaneless diffuser behind the impeller and guide vanes at the inlet to the nest stage. The method employed was that of investigating the performance of the successive elements of the blower (the impeller, vaneless diffuser, ets.) whereby the kinematics of the flow through the blower could be followed and the pressure at the different points computed. The character of the flow and the physical significance of the loss coefficients could thereby be determined so as to secure the best agreement of the computed with the actual performance of the blower. Since the tests were carried out for various delivery volumes, the dependence of the coefficients on a number of factors (angle of attack, velocities, etc.) could be obtained. The distribution of the losses that occur during the transformation of dynamic pressure at the impeller exit into static pressure could be found and likewise the range within which the friction coefficient varies in the vaneless diffuser. With the aid of factors having a certain physical significance, the centrifugal blower could be computed on the basis of a more or less schematical consideration of the ...
Contributing Partner: UNT Libraries Government Documents Department
Determination of the Mass Moments and Radii of Inertia of the Sections of a Tapered Wing and the Center-of-Gravity Line along the Wing Span

Determination of the Mass Moments and Radii of Inertia of the Sections of a Tapered Wing and the Center-of-Gravity Line along the Wing Span

Date: December 1, 1943
Creator: Savelyev, V. V.
Description: For computing the critical flutter velocity of a wing among the data required are the position of the line of centers of gravity of the wing sections along the span and the mass moments and radii of inertia of any section of the wing about the axis passing through the center of gravity of the section. A sufficiently detailed computation of these magnitudes even if the weights of all the wing elements are known, requires a great deal of time expenditure. Thus a rapid competent worker would require from 70 to 100 hours for the preceding computations for one wing only, while hundreds of hours would be required if all the weights were included. With the aid of the formulas derived in the present paper, the preceding work can be performed with a degree of accuracy sufficient for practical purposes in from one to two hours, the only required data being the geometric dimensions of the outer wing (tapered part), the position of its longerons, the total weight of the outer wing, and the approximate weight of the longerons, The entire material presented in this paper is applicable mainly to wings of longeron construction of the CAHI type and investigations ...
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Determination of Axial Fan Performance

Theoretical Determination of Axial Fan Performance

Date: April 1, 1943
Creator: Struve, E.
Description: The report presents a method for the computation of axial fan characteristics. The method is based on the assumption that the law of constancy of the circulation along the blade holds, approximately, for all fan conditions for which the blade elements operate at normal angles of attack (up to the stalling angles). Pressure head coefficient K(sub a) and power coefficient K(sub u) for the force components in the axial and tangential directions, respectively, and analogous to the lift and drag coefficients C(sub y) and C(sub x) are conveniently introduced.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of flow in an axially symmetrical heated jet of air

Investigation of flow in an axially symmetrical heated jet of air

Date: December 1, 1943
Creator: Corrsin, Stanley
Description: The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air. (author).
Contributing Partner: UNT Libraries Government Documents Department
Construction of wire strain gages for engine application

Construction of wire strain gages for engine application

Date: December 1, 1943
Creator: Tucker, Maurice
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of carburetor-mixture-control and supercharger characteristics on fuel knock under simulated sea-level flight conditions

Effect of carburetor-mixture-control and supercharger characteristics on fuel knock under simulated sea-level flight conditions

Date: March 1, 1943
Creator: Wear, Jerrold D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of exhaust back pressure on engine power

Effect of exhaust back pressure on engine power

Date: June 1, 1943
Creator: Pinkel, Benjamin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of xylidines on the corrosiveness of aircraft-engine oil

The effect of xylidines on the corrosiveness of aircraft-engine oil

Date: July 1, 1943
Creator: Olson, Walter T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of xylidines on the load-carrying capacity of an aircraft-engine oil I

The effect of xylidines on the load-carrying capacity of an aircraft-engine oil I

Date: August 1, 1943
Creator: Olson, Walter T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of xylidines on the stability of an aircraft-engine lubricating oil

The effect of xylidines on the stability of an aircraft-engine lubricating oil

Date: August 1, 1943
Creator: Meyrowitz, Emanuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of xylidines on the load-carrying capacity of an aircraft engine oil II

The effect of xylidines on the load-carrying capacity of an aircraft engine oil II

Date: September 1, 1943
Creator: Spurr, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of single-cylinder cooling tests of a Pratt and Whitney R-2800-21 engine cylinder with wind-tunnel tests of a Pratt and Whitney R-2800-27 engine

Correlation of single-cylinder cooling tests of a Pratt and Whitney R-2800-21 engine cylinder with wind-tunnel tests of a Pratt and Whitney R-2800-27 engine

Date: December 1, 1943
Creator: Rollin, Vern G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of a plain aileron with thickened and beveled trailing edges on a tapered low-drag wing

Wind-tunnel investigation of a plain aileron with thickened and beveled trailing edges on a tapered low-drag wing

Date: January 1, 1943
Creator: Mckee, John W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of a full-span retractable flap in combination with full-span plain and internally balanced ailerons on a tapered wing

Wind-tunnel investigation of a full-span retractable flap in combination with full-span plain and internally balanced ailerons on a tapered wing

Date: August 1, 1943
Creator: Fischel, Jack
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Date: September 1, 1943
Creator: Bogdonoff, Seymour M.
Description: Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.
Contributing Partner: UNT Libraries Government Documents Department
Tables of stiffness and carry-over factor for flat rectangular plates under compression

Tables of stiffness and carry-over factor for flat rectangular plates under compression

Date: November 1, 1943
Creator: Kroll, W D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces

Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces

Date: December 1, 1943
Creator: Sears, Richard I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons

Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons

Date: January 1, 1943
Creator: Underwood, William J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel investigation of rear underslung fuselage ducts

Wind tunnel investigation of rear underslung fuselage ducts

Date: September 1, 1943
Creator: Nelson, W J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theory and preliminary flight tests of an all-movable vertical tail surface

Theory and preliminary flight tests of an all-movable vertical tail surface

Date: January 1, 1943
Creator: Kleckner, Harold F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of the Characteristics of Blunt-Nose Ailerons on a Tapered Wing

Wind-Tunnel Investigation of the Characteristics of Blunt-Nose Ailerons on a Tapered Wing

Date: February 1, 1943
Creator: Toll, Thomas A.
Description: Characteristics are determined for various modifications of 0.155-chord blunt-nose aileron on semispan model of tapered fighter plane wing. Ailerons with 40 percent nose balance reduced high-speed stick forces. Increased balance chord increases effectiveness and reduces high-speed stick forces. Increased balance chord increases effectiveness and reduces adverse effects of gap at aileron hose. Increase of nose radii increased negative slope of curve hinge-movement coefficient plotted against deflection. Extended deflection range decreased aileron effectiveness for small deflections but increased it at large deflections. Peak pressures at noses of ailerons are relatively high at moderate deflections.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel vibration tests of a four-blade single rotating pusher propeller

Wind-tunnel vibration tests of a four-blade single rotating pusher propeller

Date: June 1, 1943
Creator: Miller, Mason F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel vibration tests of dual-rotating propellers

Wind-tunnel vibration tests of dual-rotating propellers

Date: September 1, 1943
Creator: Miller, Mason, F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Date: October 1, 1943
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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