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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15231 - 15254 of 18,906
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Investigation of aerodynamic characteristics of an airplane configuration having tail surfaces outboard of the wing tips at Mach numbers of 2.30, 2.97, and 3.51

Investigation of aerodynamic characteristics of an airplane configuration having tail surfaces outboard of the wing tips at Mach numbers of 2.30, 2.97, and 3.51

Date: June 23, 1958
Creator: Church, J. D.; Hayes, W. C., Jr. & Sleeman, W. C., Jr.
Description: Aerodynamic characteristics of aircraft configuration having tail surfaces outboard of wing tips at supersonic speeds - wind tunnel stability test.
Contributing Partner: UNT Libraries Government Documents Department
Some factors affecting the stability and performance characteristics of canard aircraft configurations

Some factors affecting the stability and performance characteristics of canard aircraft configurations

Date: June 23, 1958
Creator: Spearman, M Leroy & Driver, Cornelius
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of aerodynamically heated multiweb wing structures in a free jet at Mach number 2 and aluminum-alloy model of 40-inch chord with 0.125-inch-thick skin

Tests of aerodynamically heated multiweb wing structures in a free jet at Mach number 2 and aluminum-alloy model of 40-inch chord with 0.125-inch-thick skin

Date: June 23, 1958
Creator: Griffith, George E & Miltonberger, Georgene H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 45 deg swept wing fighter airplane model and aerodynamic loads on adjacent stores and missiles at Mach numbers of 1.57, 1.87, 2.16, and 2.53

Aerodynamic characteristics of a 45 deg swept wing fighter airplane model and aerodynamic loads on adjacent stores and missiles at Mach numbers of 1.57, 1.87, 2.16, and 2.53

Date: June 24, 1958
Creator: Oehman, W. I. & Turner, K. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model and aerodynamic loads on adjacent stores and missiles at Mach numbers of 1.57, 1.87, 2.16, and 2.53

Aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model and aerodynamic loads on adjacent stores and missiles at Mach numbers of 1.57, 1.87, 2.16, and 2.53

Date: June 24, 1958
Creator: Oehman, Waldo I & Turner, Kenneth L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several jet-spoiler controls on a 45 degree sweptback wing at Mach numbers of 1.61 and 2.01

Aerodynamic characteristics of several jet-spoiler controls on a 45 degree sweptback wing at Mach numbers of 1.61 and 2.01

Date: June 24, 1958
Creator: Lord, Douglas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data

Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data

Date: June 24, 1958
Creator: Shanks, Robert E.
Description: A theoretical method is presented for predicting the dynamic lateral stability characteristics of an airplane towed in tandem by a much larger airplane. Values of period and time to damp to one-half amplitude and rolling motions calculated by an analog computer have been correlated with results of two experimental investigations conducted in the Langley free-flight tunnel which were part of a U.S. Air Force program (Project FICON) to develop a satisfactory arrangement by which a bomber could tow a parasite fighter. In general, the theoretical results agree with the experimental results.
Contributing Partner: UNT Libraries Government Documents Department
An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers from 3.0 to 6.3

An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers from 3.0 to 6.3

Date: June 24, 1958
Creator: Gloria, H. R.
Description: Static longitudinal stability and control characteristics of wingless missile configuration at supersonic and hypersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of mass ratio on the transonic flutter characteristics of untapered 45 degree sweptback wings of aspect ratios 2 and 3.5

Some effects of mass ratio on the transonic flutter characteristics of untapered 45 degree sweptback wings of aspect ratios 2 and 3.5

Date: June 24, 1958
Creator: Kelly, H Neale
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Exploratory Investigation of Performance of Experimental Fuelrich Hydrogen Combustion System

Exploratory Investigation of Performance of Experimental Fuelrich Hydrogen Combustion System

Date: June 25, 1958
Creator: Grobman, J. S. & Smith, A. L.
Description: Exploratory investigation of performance characteristics of fuel-rich hydrogen combustor.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of the drag due to wedges along the trailing edge of a swept wing

Experimental investigation of the drag due to wedges along the trailing edge of a swept wing

Date: June 27, 1958
Creator: Gambucci, Bruno J & Wyss, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
HRP Radiation Corrosion Studies: In-Pile Loop L-4-11

HRP Radiation Corrosion Studies: In-Pile Loop L-4-11

Date: June 27, 1958
Creator: McWherter, J. R.; Baker, J. E.; Bohlmann, E. G.; Bradley, N. C.; Jenks, G. H.; Jones, D. T. et al.
Description: Report issued by the Oak Ridge National Laboratory discussing radiation corrosion studies. As stated in the introduction, "the purpose of this experiment was to compare the performance of a large number of materials under similar irradiation and exposure conditions" (p. 1). This report includes tables, illustrations, and photographs.
Contributing Partner: UNT Libraries Government Documents Department
Hydrodynamic characteristics of missiles launched under water

Hydrodynamic characteristics of missiles launched under water

Date: June 27, 1958
Creator: Dawson, J. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Maneuver performance of interceptor missiles

Maneuver performance of interceptor missiles

Date: June 27, 1958
Creator: Stone, D. G.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The prospects for laminar flow on hypersonic airplanes

The prospects for laminar flow on hypersonic airplanes

Date: June 27, 1958
Creator: Seiff, Alvin
Description: The factors which affect the extent of laminar flow on airplanes for hypersonic flight are discussed on the basis of the available data. Factors considered include flight Reynolds number, surface roughness, angle of attack, angle of leading-edge sweepback, and aerodynamic interference. Test data are presented for one complete configuration.
Contributing Partner: UNT Libraries Government Documents Department
A flight-test study of total-pressure distortion in a thick-lipped nose inlet

A flight-test study of total-pressure distortion in a thick-lipped nose inlet

Date: June 30, 1958
Creator: Wingrove, Rodney C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the static stability characteristics of five hypersonic missile configurations at Mach numbers from 2.29 to 4.65

Investigation of the static stability characteristics of five hypersonic missile configurations at Mach numbers from 2.29 to 4.65

Date: June 30, 1958
Creator: Turner, Kenneth L & Appich, W H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the static stability characteristics of five hypersonic missile configurations at Mach numbers from 2.29 to 4.65

Investigation of the static stability characteristics of five hypersonic missile configurations at Mach numbers from 2.29 to 4.65

Date: June 30, 1958
Creator: Appich, W. H., Jr. & Turner, K. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic investigation of yawed wings of aspect ratios 3 and 6 with a Sears-Haack body and with symmetrical and asymmetrical bodies indented for a Mach number of 1.20

Transonic investigation of yawed wings of aspect ratios 3 and 6 with a Sears-Haack body and with symmetrical and asymmetrical bodies indented for a Mach number of 1.20

Date: June 30, 1958
Creator: Holdaway, George H & Hatfield, Elaine W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Viscous flows in inlets

Viscous flows in inlets

Date: June 30, 1958
Creator: Scherrer, Richard; Lundell, John H & Anderson, Lewis A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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