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Wind-Tunnel Investigation of the Static Longitudinal Stability Characteristics of a 0.15-Scale Model of the Hermes A-1E2 Missile at High Subsonic Mach Numbers

Description: "The static longitudinal stability characteristics of a 0.15-scale model of the Hermes A-lE2 missile have been determined in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.98, corresponding to Reynolds numbers, based on body length, of 12.3 x 10(exp 6) to 17.1 x 10(exp 6). This paper presents results obtained with body alone and body-fins combinations at 0 degrees (one set of fins vertical and the other set horizontal) and 45 degree angle of roll. The results … more
Date: September 11, 1952
Creator: Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation of the Static Stability Characteristics of a 1/8-Scale Ejectable Pilot-Seat Combination at a Mach Number of 0.8

Description: Report presenting an investigation of a model of an ejectable pilot seat combination with and without stabilizing fins. The main purpose of the investigation was to determine the static aerodynamic characteristics and effectiveness of various stabilizing fins at a high subsonic Mach number. Results regarding stability and force characteristics for the combinations are provided.
Date: December 7, 1951
Creator: Visconti, Fioravante & Nuber, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Use of Leading-Edge and Trailing-Edge Area-Suction Flaps on a 13-Percent-Thick Straight Wing and Fuselage Model

Description: Report presenting a wind-tunnel investigation to determine the effectiveness of area suction in increasing the lift of a moderately thick straight wing encountering trailing-edge air flow separation. Results regarding a model with undeflected leading-edge flap and tip tanks on and a model with the tip tanks removed are provided.
Date: January 24, 1958
Creator: Holzhauser, Curt A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation of the Use of Spoilers for Obtaining Static Longitudinal Stability of a Canard-Missile Model in Reverse Flight

Description: Report presenting an investigation in the stability tunnel of the use of spoilers for obtaining static longitudinal stability of a model of a canard missile in reverse flight. Results indicated that stable pitching-moment slopes can be obtained at angles of attack up to 11 degrees in the low speed range of the tests, but further investigation of high subsonic speeds will be necessary.
Date: June 21, 1954
Creator: Fletcher, Herman S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the vortex wake and downwash field behind triangular wings and wing-body combinations at supersonic speeds

Description: Report presenting an investigation of the flow field behind triangular wings alone and in combination with a pointed cylindrical body at Mach numbers of 1.5 and 2.0 through an angle-of-attack range of 0 to 24 degrees. Results regarding the geometric characteristics of the vortex system and downwash characteristics are provided.
Date: June 25, 1953
Creator: Spahr, J. Richard & Dickey, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds

Description: Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.
Date: July 21, 1958
Creator: Heath, Atwood R., Jr. & Igoe, Ann W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds

Description: Report presenting an investigation of the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination. The model had a wing of aspect ratio 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding chordwise pressure distributions, the effect of ailerons on wing section loadings, the effect of aileron on wing loading, and the effects of a deflected aileron on opposite-wing loading are presented.
Date: July 21, 1958
Creator: Heath, Atwood R., Jr. & Igoe, Ann W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of transonic aileron flutter

Description: Report presenting a partial-span wing tested to determine the cause of a flutter which had occurred in high-speed flight. Changes were made to the wing stiffness, location of the center of gravity of the wing, and the mass balance of the aileron. Results regarding the effect of wing changes on flutter, effect of aileron changes on flutter, shock-wave study, and static aerodynamic coefficients are provided.
Date: June 9, 1949
Creator: Erickson, Albert L. & Mannes, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of transonic aileron flutter of a semispan wing model with an NACA 23013 section

Description: Report presenting the results of a wind-tunnel investigation of aileron flutter up to 0.822 Mach number. The testing indicated the absence of flutter of significant amplitude when a considerable amount of wing-tip relief existed and the presence of flutter when the relief was minimized. Results regarding the testing without the end plate, with end plate, and comparison with theory are provided.
Date: July 12, 1948
Creator: Perone, Angelo & Erickson, Albert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Two Vertical-Takeoff-and-Landing Jet Bomber Airplane Configurations at Mach Numbers of 1.94 and 2.40

Description: Report presenting an investigation to obtain information about the basic aerodynamic characteristics of two vertical-take-off-and-landing jet bomber airplanes, one with a high wing and one with a low wing. Results regarding pitch and sideslip are provided. The high-tail configurations were found to have higher lift-drag ratios for both high- and low-wing models.
Date: October 31, 1956
Creator: Jones, Robert A. & Rainey, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane

Description: Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Date: March 11, 1947
Creator: Bartlett, Walter A., Jr. & Goral, Edwin B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation to Determine the Aerodynamic Characteristics in Steady Roll of a Model at High Subsonic Speeds

Description: Report presenting aerodynamic characteristics in steady roll on a complete model and its component parts. The model consisted of a wing and horizontal tail with a 45 degree sweepback at the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding rolling moment due to rolling, yawing moment due to rolling, and lateral force due to rolling are provided.
Date: January 21, 1953
Creator: Kuhn, Richard E. & Wiggins, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation to Determine the Effect of Various Head Designs on the Aerodynamic Characteristics in Pitch of the Army Ordnance Corps T205 3.5-Inch Heat Rocket

Description: "The aerodynamic characteristics in pitch of the Army Ordnance Corps T205 3.5-inch HEAT rocket with various head designs and one fin modification have been determined at velocities of 500, 700 and 900 feet per second in the Langley high-speed 7- by 10-foot tunnel. The results presented are those of the full-scale model. Comparison of results obtained at 500 feet per second shows, in general, that for changes on the forward portion of the head the missile configurations having the greatest stabi… more
Date: 1952
Creator: Morrison, William D., Jr. & Kuhn, Richard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation to Determine the Horizontal- and Vertical-Tail Contributions to the Static Lateral Stability Characteristics of a Complete-Model Swept-Wing Configuration at High Subsonic Speeds

Description: Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Generally, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
Date: July 10, 1953
Creator: Wiggins, James W.; Kuhn, Richard E. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Measurement of Static Forces on Internally Carried Bombs of Two Different Bluff Shapes in the Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.6

Description: Report discussing the influence of forces and moments on a fighter-bomber airplane with an open bomb bay and on two bluff bomb shapes in various positions below the fuselage and plane of symmetry. The wing was found to have a noticeable effect on bomb forces and that bluff bombs affect the longitudinal characteristics of the wing-fuselage combination.
Date: April 1, 1957
Creator: Geier, Douglas J. & Robins, A. Warner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Measurements at Subsonic Speeds of the Static and Dynamic-Rotary Stability Derivatives of a Triangular-Wing Airplane Model Having a Triangular Vertical Tail

Description: Report presenting the results of oscillation tests to measure the dynamic-rotary stability derivatives of an airplane model at high subsonic speeds. Measurements taken included the damping in pitch, damping in yaw, damping in roll, and the yawing moment due to rolling velocity.
Date: April 25, 1955
Creator: Beam, Benjamin H.; Reed, Verlin D. & Lopez, Armando E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Measurements of the Dynamic Cross Derivative (Rolling Moment Due to Yawing Velocity and to Acceleration in Sideslip) of the Douglas D-558-II Airplane and Its Components at Supersonic Speeds Including Description of the Technique

Description: Report presenting a technique and the results obtained of wind-tunnel forced-oscillation tests on a model of the Douglas D-558-II airplane which was instrumented to obtain the dynamic cross derivative and static derivative. Tests were conducted for a range of Mach numbers and angles of attack. Results regarding sample calculations of the period and damping of the full-scale airplane are provided despite not being conclusive due to the inadequate number of flight conditions investigated.
Date: November 3, 1955
Creator: Boatright, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Measurements of Wing Buffeting on 1/16-Scale Model of Douglas D-558-II Research Airplane

Description: Report presenting exploratory measurements of the fluctuations of wing bending moment during normal performance and wind-tunnel testing of a model of the Douglas D-558-II from Mach numbers 0.60 to 0.96. The effects of leading-edge chord-extensions and pylon-mounted underwing external stores were investigated. Results regarding the general nature of buffeting measurements, frequency distribution of buffeting response, interpretation of model buffeting measurements, and effects of changes in mode… more
Date: September 24, 1956
Creator: Kemp, William B., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel oscillation tests of the Bendix-Friez aerovane anemometer

Description: Report presenting a Bendix-Friez Aerovane Anenometer oscillated in the streamwise direction at several frequencies for each of several low wind-tunnel airspeeds. Records of the displacement of the anenometer and velocity indicated by the instrument during oscillation are provided. The over-registration of this anenometer was found to be much smaller than predicted by theory.
Date: August 11, 1953
Creator: Fisher, Lewis R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a 0.16-Scale Model of the Douglas MX-656 Airplane at High Subsonic Speeds, 1, Stability and Control Characteristics

Description: Wind tunnel tests of the 0.16-scale Douglas MX-656 model were made at low and high subsonic Mach numbers to investigate the static longitudinal- and lateral stability characteristics. The tests shows that undesirable changes in longitudinal stability at the stall were apparently caused by an altered downwash pattern at the tail. The jettisonable nose fins were highly destabilizing. Compressibility effects for the test Mach numbers were not detrimental to the longitudinal- or lateral-stability c… more
Date: April 26, 1949
Creator: Hamilton, William T. & Cleary, Joseph W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a 0.16-Scale Model of the Douglas MX-656 Airplane at High Subsonic Speeds. 2 - Wing and Fuselage Pressure Distribution

Description: From Summary: "Measurements of wing and fuselage pressure distributions were made at low and high subsonic Much numbers on a 0.16-scale model of the projected MX-656 research airplane. The MX-656 is a supersonic design utilizing a low-aspect-ratio wing and tail. Pressure-distribution measurements indicated that, although the critical Mach number of the wing was approximately 0.81 at 0 degree angle of attack, compressibility effects were of little significance below a Mach number of at least 0.9… more
Date: August 22, 1949
Creator: Cleary, Joseph W. & Mellenthin, Jack A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds : additional stability and control characteristics and the aerodynamic effects of external stores and ram jets

Description: Report presenting additional wind-tunnel tests of a model of the X-3 airplane at low and high subsonic numbers to investigate the lateral and longitudinal-stability and control characteristics. Results regarding the aerodynamic characteristics in pitch and aerodynamic characteristics in yaw are provided.
Date: June 13, 1950
Creator: Cleary, Joseph W. & Mellenthin, Jack A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: stability and control characteristics

Description: Report presenting static lateral- and longitudinal-stability tests of a scale model of a projected, low-aspect-ratio, supersonic airplane at low and high subsonic Mach numbers. The wing was equipped with leading-edge flaps and had a modified double-wedge airfoil with sharp leading and trailing edges. Results regarding lift characteristics, static longitudinal stability and control, lateral and directional stability, drag characteristics, and wing and fuselage tuft studies are provided.
Date: April 21, 1950
Creator: Hamilton, William T. & Cleary, Joseph W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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