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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Effects of horizontal-tail position and a wing leading-edge modification consisting of a full-span flap and a partial-span chord-extension on the aerodynamic characteristics in pitch at high subsonic speeds of a model with a 45 degree sweptback wing

Effects of horizontal-tail position and a wing leading-edge modification consisting of a full-span flap and a partial-span chord-extension on the aerodynamic characteristics in pitch at high subsonic speeds of a model with a 45 degree sweptback wing

Date: June 1, 1957
Creator: Morrison, William D , Jr & Alford, William J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of horizontal-tail position and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degree triangular-wing model having twin triangular all-movable tails

Effects of horizontal-tail position and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degree triangular-wing model having twin triangular all-movable tails

Date: May 23, 1952
Creator: Jaquet, Byron M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of horizontal-tail position, area, and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degrees triangular-wing model having various triangular-all-movable horizontal tails

Effects of horizontal-tail position, area, and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degrees triangular-wing model having various triangular-all-movable horizontal tails

Date: December 14, 1951
Creator: Jaquet, Byron M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of increasing Reynolds number from 2 x 10(exp 6) to 6 x 10(exp 6) on the aerodynamic characteristics at transonic speeds of a 45 degree swept wing with 6 degree leading-edge droop

Effects of increasing Reynolds number from 2 x 10(exp 6) to 6 x 10(exp 6) on the aerodynamic characteristics at transonic speeds of a 45 degree swept wing with 6 degree leading-edge droop

Date: January 1, 1955
Creator: Schmeer, James W & Cooper, J Lawrence
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of canopy, revised vertical tail, and a yaw-damper vane on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane at a Mach number of 2.01

Effects of canopy, revised vertical tail, and a yaw-damper vane on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane at a Mach number of 2.01

Date: August 30, 1954
Creator: Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of combinations of aspect ratio and sweepback at high subsonic Mach numbers

Effects of combinations of aspect ratio and sweepback at high subsonic Mach numbers

Date: June 4, 1947
Creator: Adler, Alfred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of chord discontinuities and chordwise fences on low-speed static longitudinal stability of an airplane model having a 35 degree sweptback wing

Effects of chord discontinuities and chordwise fences on low-speed static longitudinal stability of an airplane model having a 35 degree sweptback wing

Date: June 24, 1952
Creator: Jaquet, Byron M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of compressibility and large angles of yaw on pressure indicated by a total-pressure tube

Effects of compressibility and large angles of yaw on pressure indicated by a total-pressure tube

Date: April 1, 1945
Creator: Humphreys, Milton D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of combining auxiliary bleed with ejector pumping on the power requirements and test-section flow of an 8-inch by 8-inch slotted tunnel

Effects of combining auxiliary bleed with ejector pumping on the power requirements and test-section flow of an 8-inch by 8-inch slotted tunnel

Date: July 19, 1955
Creator: Little, B H , Jr & Cubbage, James M , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of compressibility on maximum lift coefficients for six propeller airfoils

Effects of compressibility on maximum lift coefficients for six propeller airfoils

Date: January 1, 1945
Creator: Cleary, Harold E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of compressibility on rotor hovering performance and synthesized blade-section characteristics derived from measured rotor performance of blades having NACA 0015 airfoil tip sections

Effects of compressibility on rotor hovering performance and synthesized blade-section characteristics derived from measured rotor performance of blades having NACA 0015 airfoil tip sections

Date: September 1, 1958
Creator: Shivers, James P & Carpenter, Paul J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of compressibility at Mach numbers up to 0.8 on internal-flow characteristics of a cowling-spinner combination equipped with an eight-blade dual-rotation propeller

Effects of compressibility at Mach numbers up to 0.8 on internal-flow characteristics of a cowling-spinner combination equipped with an eight-blade dual-rotation propeller

Date: June 26, 1953
Creator: Bingham, Gene J & Keith, Arvid L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of compressibility on the flow past a two-dimensional bump

Effects of compressibility on the flow past a two-dimensional bump

Date: January 22, 1947
Creator: Lindsey, W F & Daley, Bernard N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of compressibility on the flow past thick airfoil sections

Effects of compressibility on the flow past thick airfoil sections

Date: July 1, 1948
Creator: Daley, Bernard N & Humphreys, Milton D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of Compressibility on the Flow Past Thick Airfoil Sections

Effects of Compressibility on the Flow Past Thick Airfoil Sections

Date: January 30, 1947
Creator: Daley, Bernard N. & Humphreys, Milton D.
Description: Six, 3-inch-chord symmetrical airfoil sections having systematic variations in thickness and thickness location were tested at Mach numbers near flight values for propeller-shank sections. The tests, the results of which are presented in the form of schlieren photographs of the flow past each model and pressure-distribution charts for two of the model, were performed to illustrate the effects of compressibility on the flow past thick symmetrical airfoil sections. Representative flow photographs indicated that at Mach numbers approximately 0.05 above the critical Mach number a speed region was reached in which the flow oscillated rapidly and the separation point and the location of the shock wave were unstable. Fixing the transition on both surfaces of the airfoil was effective in reducing these rapid oscillations. The pressure distributions showed that the section normal-force coefficients for thick airfoils were very erratic at subcritical speeds; at supercritical speeds the section normal-force coefficients for the thick airfoils became more regular. Drag coefficients showed that considerable drag decreases can be expected by decreasing the model thickness ratio.
Contributing Partner: UNT Libraries Government Documents Department
Effects of independent variations of mach number and reynolds number on the maximum lift coefficients of four NACA 6-series airfoil sections

Effects of independent variations of mach number and reynolds number on the maximum lift coefficients of four NACA 6-series airfoil sections

Date: November 1, 1952
Creator: Racisz, Stanley F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399

Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399

Date: June 5, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Description: A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by a combination of the modified inlets and extended rocket racks throughout the remainder of the test.
Contributing Partner: UNT Libraries Government Documents Department
Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model between Mach Numbers of 0.81 and 1.64, TED No. NACA AD 399

Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model between Mach Numbers of 0.81 and 1.64, TED No. NACA AD 399

Date: April 19, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Description: A flight investigation was conducted to determine the effects of an inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model which was flight tested at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. Results indicate that the combined effects of the modified inlet and fully extended rocket racks on the trim lift coefficient and trim angle of attack were small between Mach numbers of 0.94 and 1.57. Between Mach numbers of 1.10 and 1.57 there was an average increase in drag coefficient of about o,005 for the model with modified inlet and extended rocket racks. The change in drag coefficient due to the inlet modification alone is small between Mach numbers of 1.59 and 1.64.
Contributing Partner: UNT Libraries Government Documents Department
Effects of leading-edge radius on the longitudinal stability of two 45 degree sweptback wings as influenced by Reynolds numbers up to 8.20 x 10(exp 6) and Mach numbers up to 0.303

Effects of leading-edge radius on the longitudinal stability of two 45 degree sweptback wings as influenced by Reynolds numbers up to 8.20 x 10(exp 6) and Mach numbers up to 0.303

Date: July 28, 1955
Creator: Foster, Gerald V & Schneider, William C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of leading-edge devices and trailing-edge flaps on longitudinal characteristics of two 47.7 degree sweptback wings of aspect ratios 5.1 and 6.0 at a Reynolds number of 6.0 x 10(exp 6)

Effects of leading-edge devices and trailing-edge flaps on longitudinal characteristics of two 47.7 degree sweptback wings of aspect ratios 5.1 and 6.0 at a Reynolds number of 6.0 x 10(exp 6)

Date: August 30, 1950
Creator: Salmi, Reino J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of Mach Number and Reynolds Number on the Maximum Lift Coefficient of a Wing of NACA 230-Series Airfoil Sections

Effects of Mach Number and Reynolds Number on the Maximum Lift Coefficient of a Wing of NACA 230-Series Airfoil Sections

Date: May 1, 1947
Creator: Furlong, G. Chester & Fitzpatrick, James E.
Description: Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps. Chordwise pressure-distribution measurements were made for all flap configurations.. Peak values of maximum lift coefficient were obtained at relatively low free-stream Mach numbers and, before critical Mach number was reached, were almost entirely dependent on Reynolds Number. Lift coefficient increased by increasing Mach number or deflecting flaps while critical pressure coefficient was reached at lower free-stream Mach numbers.
Contributing Partner: UNT Libraries Government Documents Department
Effects of leading-edge radius on the longitudinal stability characteristics of two 60 degree sweptback wings at high Reynolds numbers

Effects of leading-edge radius on the longitudinal stability characteristics of two 60 degree sweptback wings at high Reynolds numbers

Date: March 19, 1956
Creator: Schneider, William C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of leading-edge slats on the aerodynamic characteristics of a 45 degree sweepback wing-fuselage configuration at Mach numbers  of 0.4 to 1.03

Effects of leading-edge slats on the aerodynamic characteristics of a 45 degree sweepback wing-fuselage configuration at Mach numbers of 0.4 to 1.03

Date: August 21, 1953
Creator: Runckel, Jack F & Steinberg, Seymour
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of body indentation on the drag characteristics of a delta-wing-body combination at transonic speeds

Effects of body indentation on the drag characteristics of a delta-wing-body combination at transonic speeds

Date: January 28, 1955
Creator: Wornom, Dewey E & Osborne, Robert S
Description: None
Contributing Partner: UNT Libraries Government Documents Department