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  Partner: UNT Libraries Government Documents Department
 Resource Type: Report
 Decade: 1950-1959
 Year: 1954
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics III : effect of turbine stator adjustment

Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics III : effect of turbine stator adjustment

Date: August 2, 1954
Creator: Rohlik, Harold E & Rebeske, John J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accepted Limit Values of Air Pollutants

Accepted Limit Values of Air Pollutants

Date: May 1954
Creator: Barkley, J. F.
Description: Report issued by the U.S. Bureau of Mines discussing, as stated in the introduction, the "accepted maximum permissible concentrations of air pollutants from the standpoints of health, damage to vegetation, damage to property, and requirements of industrial processes" (p. 1). This report includes tables.
Contributing Partner: UNT Libraries Government Documents Department
Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy

Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy

Date: March 10, 1954
Creator: Eaton, I D & Youra, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds

Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds

Date: January 1, 1954
Creator: Spreeman, Kenneth P. & Few, Albert G.
Description: Additional results on the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane were obtained in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.92. The maximum angle-of-attack range (obtained at the lower Mach numbers) was from -2 degrees to 25 degrees. The sideslip-angle range investigated was from -4 degrees to 12 degrees. The investigation included effects of various arrangements of wing fences, leading-edge chord-extensions, and leading-edge notches. Various fuselage fences, spoilers, and a dive brake also were investigated. From overall considerations of lift, drag, and pitching moments, it appears that there were two modifications somewhat superior to any of the others investigated: One was a configuration that employed a full-chord fence and a partial-chord fence located at 0.63 semispan and 0.55 semispan, respectively. The second was a leading-edge chord-extension that extended from 0.68 semispan to 0.85 semispan in combination with a leading-edge notch located at 0.68 semispan. With plus or minus 10 degrees aileron, the estimated wing-tip helix angle was reduced from 0.125 at a Mach number of 0.50 to 0.088 at a Mach number of 0.92, with corresponding rates of roll of 4.0 ...
Contributing Partner: UNT Libraries Government Documents Department
Additional static and fatigue tests of high-strength aluminum-alloy bolted joints

Additional static and fatigue tests of high-strength aluminum-alloy bolted joints

Date: July 1, 1954
Creator: Hartmann, E C; Holt, Marshall & Eaton, I D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees

Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees

Date: January 1, 1954
Creator: Critzos, Chris C.
Description: An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic characteristics of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 airfoil sections. Data were obtained at Mach numbers from 0.3 to that for tunnel choke, at angles of attack from -2deg to 30deg, and with the surface. of each airfoil smooth-and with roughness applied at the leading edge.The Reynolds numbers of the tests ranged from 0.8 x 10(exp 6) to 4.4 x 10(exp 6). The results are presented as variations of lift, drag, and quarter-chord pitching-moment coefficients with Mach number.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls

Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls

Date: August 30, 1954
Creator: Spearman, M Leroy & Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a 52.5 degree delta wing and a low, swept horizontal tail

Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a 52.5 degree delta wing and a low, swept horizontal tail

Date: March 29, 1954
Creator: Kehlet, Alan B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail

The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail

Date: April 5, 1954
Creator: Runckel, Jack F & Schmeer, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds

Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds

Date: March 18, 1954
Creator: Osborne, Robert S & Wornom, Dewey E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a circular cylinder at Mach number of  6.86 and angles of attack up to 90 degrees

Aerodynamic Characteristics of a circular cylinder at Mach number of 6.86 and angles of attack up to 90 degrees

Date: March 11, 1954
Creator: Penland, Jim A
Description: Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.86, a Reynolds number of 129,000 based on diameter, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and with a simple modification of the Newtonian flow theory. The comparison of experimental results shows that either theory gives adequate general aerodynamic characteristics but that the modified Newtonian theory gives a more accurate prediction of the pressure distribution. The calculated crossflow drag coefficients plotted as a function of crossflow Mach number were found to be in reasonable agreement with similar results obtained from other investigations at lower supersonic Mach numbers. Comparison of the results of this investigation with data obtained at a lower Mach number indicates that the drag coefficient of a cylinder normal to the flow is relatively constant for Mach numbers above about 4.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a cruciform-wing missile with canard control surfaces and of some very small span wing-body missiles at a Mach number of 1.41

Aerodynamic characteristics of a cruciform-wing missile with canard control surfaces and of some very small span wing-body missiles at a Mach number of 1.41

Date: April 12, 1954
Creator: Spearman, M Leroy & Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a spoiler at Mach number 1.61

Aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a spoiler at Mach number 1.61

Date: March 10, 1954
Creator: Lord, Douglas R & Czarnecki, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several flap-type trailing-edge controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01

Aerodynamic characteristics of several flap-type trailing-edge controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01

Date: June 14, 1954
Creator: Lord, Douglas R & Czarnecki, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several tip controls on a 60 degree wing at a Mach number of 1.61

Aerodynamic characteristics of several tip controls on a 60 degree wing at a Mach number of 1.61

Date: August 5, 1954
Creator: Lord, Douglas R & Czarnecki, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)

Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)

Date: August 1, 1954
Creator: Loftin, Laurence K , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of two flat-bottomed bodies at Mach number of 3.12

Aerodynamic characteristics of two flat-bottomed bodies at Mach number of 3.12

Date: April 2, 1954
Creator: Jack, John R & Moskowitz, Barry
Description: The aerodynamic characteristics of two flat-bottomed bodies having a semicircular and a semielliptical cross section have been determined at a Mach number of 3.12 for a range of angles of attack from -10 degrees to 10 degrees and for Reynolds numbers of 8 x 10 (superscript)6 and 14 x 10 (superscript)6 (based on model length). A comparison of the flat-bottomed body characteristics with those previously determined for an equivalent cone-cylinder body of revolution shows that significant increases in lift and lift-drag ratio are obtained with a flat bottom. Additional improvement in lift and lift-drag ratio was achieved at positive angles of attack by expanding the plan form in the spanwise direction.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of two series of lifting bodies at Mach number 6.86

The aerodynamic characteristics of two series of lifting bodies at Mach number 6.86

Date: May 24, 1954
Creator: Ridyard, Herbert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Date: November 1, 1954
Creator: Sacks, Alvin H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Date: November 1, 1954
Creator: Sacks, Alvin H.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic investigation of a four-blade propeller operating through an angle-of-attack range from 0 to 180 degrees

Aerodynamic investigation of a four-blade propeller operating through an angle-of-attack range from 0 to 180 degrees

Date: June 1, 1954
Creator: Mclemore, H Clyde & Cannon, Michael D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic loads on a leading-edge flap and a leading-edge slat on the NACA 64A010 airfoil section

Aerodynamic loads on a leading-edge flap and a leading-edge slat on the NACA 64A010 airfoil section

Date: June 1, 1954
Creator: Kelly, John A & Mccullough, George B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) IV : aerodynamic characteristics of series of four bodies having near-parabolic noses and cylindrical afterbodies

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) IV : aerodynamic characteristics of series of four bodies having near-parabolic noses and cylindrical afterbodies

Date: January 25, 1954
Creator: Jack, John R & MOSKOWITZ BARRY
Description: Pressure distributions and forces for a series of four bodies of revolution having nose-fineness ratios varying from 4 to 10 have been obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2x10(sup)6 to 14x10(sup)6, and angles of attack from zero to 9 degrees. In general, a comparison of the experimental data with a second-order theory showed good agreement for the range of variables investigated.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) V : aerodynamic load distributions for a series of four boattailed bodies

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) V : aerodynamic load distributions for a series of four boattailed bodies

Date: May 6, 1954
Creator: Moskowitz, Barry & Jack, John R
Description: Pressure distributions for a series of four boattailed bodies of revolution were obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2 x 10 to 6th power to 14 x 10 to the 6th power, and angles of attack from zero to 9 degrees. Second-order theory adequately predicted the pressure distribution for regions free of the effects of cross-flow separation.
Contributing Partner: UNT Libraries Government Documents Department
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