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Results 15251 - 15260 of 18,906
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Aerodynamic Research on Fuselages with Rectangular Cross Section

Aerodynamic Research on Fuselages with Rectangular Cross Section

Date: July 1, 1958
Creator: Maruhn, K.
Description: The influence of the deflected flow caused by the fuselage (especially by unsymmetrical attitudes) on the lift and the rolling moment due to sideslip has been discussed for infinitely long fuselages with circular and elliptical cross section. The aim of this work is to add rectangular cross sections and, primarily, to give a principle by which one can get practically usable contours through simple conformal mapping. In a few examples, the velocity field in the wing region and the induced flow produced are calculated and are compared with corresponding results from elliptical and strictly rectangular cross sections.
Contributing Partner: UNT Libraries Government Documents Department
Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6

Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6

Date: July 1, 1958
Creator: Groesbeck, Donald E. & Peters, Daniel J.
Description: The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel injection. At an afterburner-inlet pressure of approximately 3100 pounds per square foot absolute, corresponding to an altitude of 38,700 feet and a_ flight Mach number of 1.5, the combustion efficiency of both configurations reached peak values of 0.80 to 0.85 at equivalence ratios of 0.35 to 0.40. However, further reduction in the afterburner-inlet pressure severely affected combustion efficiency. For example, at an afterburner inlet pressure level of 700 to 1000 pounds per square foot absolute, the efficiency for both configurations was 0.20 to 0.40.
Contributing Partner: UNT Libraries Government Documents Department
A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge

A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge

Date: July 1, 1958
Creator: Pitts, William C. & Nielsen, Jack Norman
Description: Ward's slender-body-theory formula for zero-lift drag contains three integrals plus a base-drag term. Two of these integral terms depend only upon the cross-sectional area distribution of the body. The third integral term depends only upon the body shape and axial slopes at the base of the body. This term is neglected in the transonic area rule because in many cases it is zero; however, there are also many cases in which it is not zero. This paper examines the term for the possibility of drag reduction for a particular case. The model considered consists of a body of revolution in combination with any wing that has an unswept trailing edge and a constant trailing-edge angle along its span. It is found that (neglecting any change in base drag) a drag reduction is obtainable which, for the case considered, is an additional 12 percent of that obtained with the area-rule modification. The probable effect of viscosity on this theoretical result is discussed.
Contributing Partner: UNT Libraries Government Documents Department
Compressive strength and creep of 17-7 PH stainless-steel plates at elevated temperatures

Compressive strength and creep of 17-7 PH stainless-steel plates at elevated temperatures

Date: July 1, 1958
Creator: Stein, Bland A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Dynamic stability of vehicles traversing ascending or descending paths through the atmosphere

Dynamic stability of vehicles traversing ascending or descending paths through the atmosphere

Date: July 1, 1958
Creator: Tobak, Murray & Allen, H Julian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of favorable pressure gradients on transition for several bodies of revolution at Mach 3.12

Effect of favorable pressure gradients on transition for several bodies of revolution at Mach 3.12

Date: July 1, 1958
Creator: Jack, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of boundary-layer displacement and leading-edge bluntness on pressure distribution, skin friction, and heat transfer of bodies at hypersonic speeds

Effects of boundary-layer displacement and leading-edge bluntness on pressure distribution, skin friction, and heat transfer of bodies at hypersonic speeds

Date: July 1, 1958
Creator: Bertram, Mitchel H & Henderson, Arthur, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of fabrication-type roughness on turbulent skin friction at supersonic speeds

Effects of fabrication-type roughness on turbulent skin friction at supersonic speeds

Date: July 1, 1958
Creator: Czarnecki, K R; Sevier, John R , Jr & Carmel, Melvin M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of fixing transition on the transonic aerodynamic characteristics of a wing-body configuration at Reynolds numbers from 2.4 to 12 million

Effects of fixing transition on the transonic aerodynamic characteristics of a wing-body configuration at Reynolds numbers from 2.4 to 12 million

Date: July 1, 1958
Creator: Hunton, Lynn W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of nose shape and spray control strips on emergence and planing spray of hydro-ski models

Effects of nose shape and spray control strips on emergence and planing spray of hydro-ski models

Date: July 1, 1958
Creator: Mcgehee, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department