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Strain-Gage Measurements of Buffeting Loads on a Jet-Powered Bomber Airplane

Description: Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bending-moment increments for the stabilizers and wings as measured in gradual maneuvers for a jet-powered bomber airplane are presented. The buffeting-load increments were determined from strain-gage measurements at the roots or hinge supports of the various surfaces considered. The Mach numbers of the tests ranged from 0.19 to 0.78 at altitudes close to 30,000 feet. The predominant buffet frequencies… more
Date: March 19, 1951
Creator: Aiken, William S., Jr. & See, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Measurements of a 34 Degree Swept-Forward and Swept-Back NACA 65-009 Airfoil of Aspect Ratio 2.7 as Determined by Flight Tests at Supersonic Speeds

Description: Report presenting the results of flight testing to determine the zero-lift drag of an NACA 65-009 airfoil at a specified aspect ratio. The results are compared to previous testing of unswept and swept-back arrangements. The swept-forward and swept-back airfoils were found to produce lower values of zero-drag lift than the unswept airfoil.
Date: February 20, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Measurements of a Swept-Back Wing Having Inverse Taper as Determined by Flight Tests at Supersonic Speeds

Description: Report discussing the results of flight tests to determine the drag at zero lift of a swept-back wing of inverse taper using an NACA 65-009 airfoil. The data was compared to untapered wings with a similar degree of sweepback. The tapered wing was found to have a lower drag coefficient than the 34-degree swept-back untapered wing but a higher drag coefficient than the 45-degree swept-back untapered wing.
Date: April 8, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Measurements of Symmetrical Circular-Arc and NACA 65-009 Rectangular Airfoils Having an Aspect Ratio of 2.7 as Determined by Flight Tests at Supersonic Speeds

Description: Report discussing testing to determine the drag characteristics at zero lift of a wing with a circular-arc airfoil section with a maximum thickness of 9 percent chord. The results were compared to previous testing on an NACA 65-009 airfoil. It was found that the NACA airfoil had lower drag coefficients than the circular-arc airfoil tested in this experiment.
Date: March 7, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation to Determine the Aerodynamic Characteristics of Rocket-Powered Models Representative of a Fighter-Type Airplane Configuration Incorporating an Inverse-Taper Wing and a Vee Tail

Description: From Summary: "Two rocket-powered models representative of a fighter-type airplane were investigated in flight at Mach numbers up to 1.01 and 1.07 by the Langley Pilotless Aircraft Research Division at its testing station at Wallops Island, Va. These models incorporated an inverse-taper wing and a vee tail and were flown with controls undeflected and wing and stabilizer set at 0 deg incidence. Values of lateral acceleration, normal acceleration velocity, and drag were obtained by use of telemet… more
Date: November 2, 1948
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Description: Tests to evaluate the effect of a conical windshield on the drag of a bluff body at supersonic speeds were performed for the following configurations: a sharp nose fuselage with stabilizing fins,a blunt nose fuselage with a hemispherical shape, and a blunt nose fuselage with a conical point. Results of the drag coefficient are described at Mach 1.0 and the greatest Mach number of 1.37.
Date: January 14, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having aspect ratios of 1.5 and 2.7 as determined by flight tests at supersonic speeds

Description: Report presenting tests to determine the effects of sweepback angle and aspect ratio on the drag of an NACA 65-009 airfoil at supersonic speeds. The results indicated that for the range of Mach numbers investigated, increasing the sweepback angle and decreasing the aspect ratio reduced the value of the wing drag coefficient.
Date: February 24, 1947
Creator: Alexander, Sidney R. & Katz, Ellis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests to Determine the Effect of Length of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Description: Flight tests were conducted to determine the effect of length of a conical windshield on the drag of a bluff body moving at supersonic speeds. A comparison is made between results obtained and results of previous drag tests of body-windshield combinations.The effect of increasing the length of the windshield is discussed.
Date: January 29, 1947
Creator: Alexander, Sidney R. & Katz, Ellis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests to Determine the Effect of Taper on the Zero-Lift Drag of Wings at Low Supersonic Speeds

Description: Report presenting the results of tests to determine the effect of taper on the zero-lift drag of wings of constant exposed aspect ratio at low supersonic speeds. Findings indicated that maximum thickness, leading-edge, and trailing-edge sweep are all important in determining the drag coefficient of a tapered wing.
Date: July 13, 1947
Creator: Alexander, Sidney R. & Nelson, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests to Determine the Drag of Fin-Stabilized Parabolic Bodies at Transonic and Supersonic Speeds

Description: Report presenting testing on parabolic bodies of revolution of two fineness ratios in the transonic and supersonic range. One had a body fineness ratio of 7.87 and one had a ratio of 12 and were tested under different Mach number ranges. Experimental results and drag estimates of various portions of the body are provided.
Date: April 21, 1948
Creator: Alexander, Sidney R.; Chauvin, Leo T. & Rumsey, Charles B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds

Description: "The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).
Date: June 27, 1955
Creator: Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Static Aerodynamic Forces and Moments at Low Speed on a Canard Missle During Simulated Launching From the Midsemispan and Wing-Tip Locations of a 45 Degree Sweptback Wing-Fuselage Combination

Description: Report presenting an investigation at low speed to determine the static aerodynamic forces and moments on a canard missile model during launching from the midsemispan and wing-tip locations of a wing-fuselage combination with a 45 degree sweptback wing. When the missile was mounted under the wing at the midsemispan location, changes in chordwise position produced large changes in missile forces and moments.
Date: April 6, 1955
Creator: Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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
open access

Small-Scale Transonic Investigation of the Effects of Partial-Span Leading-Edge Camber on the Aerodynamic Characteristics of a 50 Degree 38' Sweptback Wing of Aspect Ratio 2.98

Description: "A small-scale transonic investigation of two semispan wings of the same plan form was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range of 0.70 to 1.10 and a mean-test Reynolds number range of 745,000 to 845,000 to determine the effects of partial-span leading-edge camber on the aerodynamic characteristics of a swept-back wing. This paper presents the results of the investigation of wing-alone and wing-fuselage configurations of the two wings; one, was an uncamber… more
Date: June 23, 1952
Creator: Alford, William J., Jr. & Byrnes, Andrew L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of effects of moderate sideslip on the flow fields near a 45 degree swept-wing-fuselage combination at low speed

Description: The flow fields near a 45 degree swept-wing-fuselage combination at moderate angles of sideslip (plus-or-minus 8 degrees), as determined experimentally at low speed, are presented as variations with chordwise distance for various spanwise and vertical locations and angles of attack. The results indicated that for positions close to the fuselage (on and near the plane of symmetry) changes in the angle of sideslip caused large changes in the flow-field characteristics and particularly in the loca… more
Date: July 12, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed

Description: Report presenting an experimental determination of the flow fields near swept- and unswept-wing-fuselage combinations at zero sideslip as determined experimentally at low speed for various spanwise and vertical locations and angles of attack as variations with chordwise distance. Results regarding the swept-wing-fuselage flow fields, unswept-wing-fuselage flow fields, and a comparison of wing-fuselage and fuselage-alone flow fields are provided.
Date: January 18, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Canard Missile During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination at Zero Sideslip

Description: Report presenting an investigation at high subsonic speeds to determine the static aerodynamic forces and moments on a canard missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. Significant variations in all the aerodynamic components were noted with changes in chordwise location of the missile. Results regarding force and moment characteristics and effects of angle of attack and Mach number are provided.
Date: January 14, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Missile Model During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination

Description: "An investigation was made at high subsonic speeds in the Langley high-speed 7- by 10-foot tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. The results indicated significant variations in all the aerodynamic components with changes in chordwise location of the missile. Increasing the angle of attack caused increases in the induced effects on the miss… more
Date: January 10, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Missile Model During Simulated Launching From Unswept-, Sweptback-, and Modified-Delta-Wing-Fuselage Combinations at Zero Sideslip

Description: Report presenting an investigation in the high-speed tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from midsemispan locations of various types of wings. The purpose of the investigation is to determine the nature and origin of the mutual interference experienced by various combinations of wing-fuselage models and externally carried missiles. Results regarding isolated missile characteristics, the effect of varying chordwise position,… more
Date: March 19, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effects of Changes in Aspect Ratio and Tail Height on the Longitudinal Stability Characteristics at High Subsonic Speeds of a Model With a Wing Having 32.6 Degree Sweepback

Description: Report discussing an investigation to determine the effects of changes in aspect ratio and tail height on the longitudinal stability characteristics of a model with a 32.6-degree sweptback wing. The effects of a leading-edge discontinuity were also examined.
Date: February 2, 1954
Creator: Alford, William J., Jr. & Pasteur, Thomas B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of finned and unfinned bodies mounted at various locations from the wings of unswept- and swept-wing--fuselage models, including measurements of body loads

Description: Report presenting an investigation to determine the effects of location of bodies (finned and unfinned) on the aerodynamic characteristics of unswept- and swept-wing--fuselage models and to determine the aerodynamic loads on the bodies in the presence of the wings. Results for the complete model characteristics and for the body are provided.
Date: April 1, 1954
Creator: Alford, William J., Jr. & Silvers, H. Norman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Small-scale transonic investigation of a 45 degree sweptback wing of aspect ratio 4 with combinations of nose-flap deflections and wing twist

Description: Report presenting a small-scale transonic investigation of a semispan wing sweptback 45 degrees and of aspect ratio 4 with combinations of nose-flap deflections and wing twist in the high-speed 7- by 10-foot tunnel over a range of Mach numbers. Lift, drag, and pitching-moment data were obtained for several different configurations.
Date: January 9, 1953
Creator: Alford, William J., Jr. & Spreemann, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Static Aerodynamic Forces and Moments at Low Speed on a Missile Model During Simulated Launching From the 25-Percent-Semispan and Wing-Tip Location of a 45 Degree Sweptback Wing-Fuselage Combination

Description: Report presenting an investigation at low speed in the 300 mph tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from 25-percent-semispan and wing-tip locations of a wing-fuselage combination. Results regarding the differences in location and effects induced by the fuselage are provided.
Date: May 25, 1955
Creator: Alford, William J., Jr.; Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Low-Speed Wind-Tunnel Investigation of Some Aspects of the Aerodynamic Problems Associated with Missiles Carried Externally in Positions Near Airplane Wings

Description: A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems associated with the use of air-to-air missiles when carried externally on aircraft. Measurements of the forces and moments on a missile model for a range of positions under the mid-semispan location of a 45deg sweptback wing indicated longitudinal and lateral forces with regard to both carriage and release of the missiles. Surveys of the characteristics of the flow field in the region likely to be tr… more
Date: December 27, 1954
Creator: Alford, William J., Jr.; Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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