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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15391 - 15414 of 19,607
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Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Date: August 1953
Creator: Eiband, A Martin; Simpkinson, Scott H & Black, Dugald O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for rapid analysis of 45 degree strain-rosette data

Charts for rapid analysis of 45 degree strain-rosette data

Date: May 1, 1944
Creator: Manson, S S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for the rapid calculation of the work required to compress dry air

Charts for the rapid calculation of the work required to compress dry air

Date: April 1, 1946
Creator: Benser, William A; Wilcox, Ward W & Voit, Charles H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for the determination of supersonic air flow against inclined planes and axially symmetric cones

Charts for the determination of supersonic air flow against inclined planes and axially symmetric cones

Date: July 1, 1947
Creator: Moeckel, W E & Connors, J F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The crystal structure at room temperature of eight forged heat-resisting alloys

The crystal structure at room temperature of eight forged heat-resisting alloys

Date: July 1, 1946
Creator: Kittel, Howard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of misalignment of strain-gage components of strain rosettes

Effect of misalignment of strain-gage components of strain rosettes

Date: September 1, 1946
Creator: Manson, S S & Morgan, W C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Development of a protected air scoop for the reduction of induction-system icing

Development of a protected air scoop for the reduction of induction-system icing

Date: September 1, 1946
Creator: Von Glahn, Uwe & Renner, Clark E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of elastic stresses in gas-turbine disks

Determination of elastic stresses in gas-turbine disks

Date: January 1, 1947
Creator: Manson, S S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Distribution of bearing reactions on a rotating shaft supported on multiple journal bearings

Distribution of bearing reactions on a rotating shaft supported on multiple journal bearings

Date: May 1, 1947
Creator: Manson, S S & Morgan, W C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Distribution of wave drag and lift in the vicinity of wing tips at supersonic speeds

Distribution of wave drag and lift in the vicinity of wing tips at supersonic speeds

Date: July 1, 1947
Creator: Evvard, John C
Description: The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at supersonic speeds was extended to include the effect of the region between the wing boundary and the foremost Mach wave from the wing leading edge. The effect of this region on the surface velocity potential has been determined by an equivalent function, which is evaluated over a portion of the wing surface. In this manner, the effect of angles of attack and yaw as well as the asymmetry of top and bottom wing surfaces may be calculated. As examples of the method, the pressure distribution on a thin plate wing of rectangular plan form as well as the lift and the drag coefficients as a function of Mach number, angle of attack, and aspect ratio are calculated. The equations for the surface velocity potential of several other plan forms are also included. (author).
Contributing Partner: UNT Libraries Government Documents Department
The effect of engine variables on the prediction-limited performance of three fuels

The effect of engine variables on the prediction-limited performance of three fuels

Date: September 1, 1946
Creator: Male, Donald W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of exhaust pressure on the performance of a 12-cylinder liquid-cooled engine

Effect of exhaust pressure on the performance of a 12-cylinder liquid-cooled engine

Date: July 1, 1947
Creator: Desmon, Leland G & Doyle, Ronald B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of centrifugal force on the elastic curve of a vibrating cantilever beam

Effect of centrifugal force on the elastic curve of a vibrating cantilever beam

Date: February 1, 1947
Creator: Simpkinson, Scott H; Millenson, Morton B & Eatherton, Laurel J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects on performance of changing the division of work between increase of angular velocity and increase of radius of rotation in an impeller

Effects on performance of changing the division of work between increase of angular velocity and increase of radius of rotation in an impeller

Date: February 1, 1947
Creator: Ginsburg, Ambrose; Ritter, William K & Palasics, John
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of axial-plane curvature and passage-area variation on flow capacity of radial-discharge impeller with conventional inlet buckets

Effects of axial-plane curvature and passage-area variation on flow capacity of radial-discharge impeller with conventional inlet buckets

Date: May 1, 1946
Creator: Ritter, William K; Ginsburg, Ambrose & Redlitz, Alfred G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the effect of canopies on directional stability characteristics of a single engine airplane model

Wind-tunnel investigation of the effect of canopies on directional stability characteristics of a single engine airplane model

Date: May 1, 1946
Creator: Maclachlan, Robert & Levitt, Joseph
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some considerations on an airfoil in an oscillating stream

Some considerations on an airfoil in an oscillating stream

Date: August 1, 1947
Creator: Greenberg, J Mayo
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of aeroelasticity and sweepback on the rolling effectiveness and drag of a 1/11-scale model of the Bell X-5 airplane wing at Mach numbers from 0.6 to 1.5

Some effects of aeroelasticity and sweepback on the rolling effectiveness and drag of a 1/11-scale model of the Bell X-5 airplane wing at Mach numbers from 0.6 to 1.5

Date: November 18, 1953
Creator: English, Roland D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tail-design requirements for satisfactory spin recovery

Tail-design requirements for satisfactory spin recovery

Date: April 1, 1946
Creator: Neihouse, Jacob H; Lichtenstein, Jacob H & Pepoon, Philip W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tables of stiffness and carry-over factor for structural members under axial load

Tables of stiffness and carry-over factor for structural members under axial load

Date: June 1, 1938
Creator: Lundquist, Eugene E & Kroll, W D
Description: Tables of stiffness and carry-over factor are presented for members in which the cross section and axial load do not vary along the length of the member. These tables are of use in solving problems in the stability of structural members under axial load as well as in application of the Cross method of moment distribution when the effects of axial load in the members are considered. The interval between successive values of the argument is small enough to make interpolation unnecessary in engineering calculations.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of effect of span, spanwise location, and chordwise location of spoilers on lateral control characteristics of a tapered wing

Investigation of effect of span, spanwise location, and chordwise location of spoilers on lateral control characteristics of a tapered wing

Date: May 1, 1947
Creator: Fischel, Jack & Tamburello, Vito
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Notes on the stalling of vertical tail surfaces and on fin design

Notes on the stalling of vertical tail surfaces and on fin design

Date: October 1, 1940
Creator: Thompson, F L & Gilruth, R R
Description: A discussion is given of the important aspects of the stalling of vertical tail surfaces. The type of instability encountered is described and the possibilities of inadvertent occurrence are noted. The influence of directional flight tests on the behavior of a airplane when the tail stall takes place is discussed. In this connection, flight tests of a twin-engine airplane in which the vertical fin area was increased are cited. The reasons for inadequate directional stability in certain modern designs are accounted for and the properties and applications of dorsal fins are discussed. In addition, the chief factors regulating the requirements for conventional area are given, in which connection simplified criterion for directional stability is presented. It may be concluded that the stalling of vertical tail surfaces is not in itself a dangerous condition. Provided sufficient directional stability exists at large angles of sideslip, the tail stall may occur with modern airplanes, as with those of the past, without the knowledge or concern to the pilot.
Contributing Partner: UNT Libraries Government Documents Department
Notes on the technique of landing airplanes equipped with wing flaps

Notes on the technique of landing airplanes equipped with wing flaps

Date: January 1, 1936
Creator: Gough, Melvin N
Description: The proper landing of airplanes equipped with flaps, although probably no more difficult than landing without them, requires a different technique. The effects of flaps on the aerodynamics characteristics of a wing are given and, with the aid of figures and diagrams, a detailed comparison of the glide and landing of an airplane with and without flaps is made. The dangers attending improper execution and the importance of such factors as air speed fuselage attitude, glide-path angle, and control manipulation, upon all of which a pilot bases his judgement, are emphasized. Of most importance in connection with the use of flaps are: the maintenance of a sufficient margin of speed above the stall; a decisive use of the controls at the proper time; more cautious use of power during the approach glide; and, above all, the willingness to accept the steep nose-down attitude necessary in the glide resulting from the use of flaps.
Contributing Partner: UNT Libraries Government Documents Department
Notes on the theoretical characteristics of two-dimensional supersonic airfoils

Notes on the theoretical characteristics of two-dimensional supersonic airfoils

Date: January 1, 1947
Creator: Ivey, H Reese
Description: The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic characteristics of two-dimensional supersonic airfoils. A discussion is given of the effect of thickness ratio, free-stream Mach number, angle of attack, camber, thickness distribution, and aileron deflection. The calculations indicated that the minimum drag of supersonic airfoils is obtained when the maximum thickness is behind the 0.50 chord. The center of pressure obtained for a symmetrical supersonic airfoil was found to be ahead of the 0.50 chord.
Contributing Partner: UNT Libraries Government Documents Department