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 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Date: January 14, 1947
Creator: Alexander, Sidney R.
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 coeeficient are described at Mach 1.0 and the greatest Mach number of 1.37.
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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

Flight Tests to Determine the Effect of Length of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Date: January 29, 1947
Creator: Alexander, Sidney R. & Katz, Ellis
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.
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Flight tests to determine the drag of fin-stabilized parabolic bodies at transonic and supersonic speeds

Flight tests to determine the drag of fin-stabilized parabolic bodies at transonic and supersonic speeds

Date: April 21, 1948
Creator: Alexander, Sidney R; Chauvin, Leo T & Rumsey, Charles B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of wing-fuselage flow fields on missile loads at subsonic speeds

Effects of wing-fuselage flow fields on missile loads at subsonic speeds

Date: June 27, 1955
Creator: Alford, W. J., Jr.
Description: Swept wing-fuselage flow fields on missile loads at subsonic speeds.
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Experimental static aerodynamic forces and moments at high subsonic speeds on a canard missile during simulated launching from the midsemispan location of a 45 deg sweptback wing-fuselage-pylon combination at zero sideslip

Experimental static aerodynamic forces and moments at high subsonic speeds on a canard missile during simulated launching from the midsemispan location of a 45 deg sweptback wing-fuselage-pylon combination at zero sideslip

Date: January 14, 1957
Creator: Alford, W. J., Jr. & King, T. J., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed

Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed

Date: January 18, 1957
Creator: Alford, William J & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: March 19, 1957
Creator: Alford, William J & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: January 10, 1957
Creator: Alford, William J & King, Thomas, Jr
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 missile model because of the wing-fuselage-pylon combination. Increasing the Mach number had little effect on the variations of the missile aerodynamic characteristics with angle of attack except that nonlinearities were incurred at smaller angles of attack for the higher Mach numbers. The effects of finite wing thickness on the missile characteristics, at zero angle of attack, increase with increasing Mach number. The effects of the pylon on the missile characteristics were to causeincreases in the rolling-moment variation with angle of attack and a negative displacement of the pitching-moment curves at zero angle of attack. The effects of skewing the missile in the lateral direction relative to and sideslipping the missile with the wing-fuselage-pylon combination were to cause additional increments in side force at zero angle of attack. ...
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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

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

Date: April 6, 1955
Creator: Alford, William J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of effects of moderate sideslip on the flow fields near a 45 degree swept-wing-fuselage combination at low speed

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

Date: July 12, 1957
Creator: Alford, William J , Jr & King, Thomas J , Jr
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 local angles of sideslip, which in some cases were nearly double the static angle of sideslip. In general, the effects of changing the angle of sideslip on the flow-field characteristics for all of the outboard underwing locations were qualitatively similar, although conditions at the more inboard and outboard locations were somewhat more severe for lifting conditions than at the one-half semispan location. The chordwise gradients in the flow parameters for the underwing locations were more severe than for the fuselage locations although the effect of changing the angle of sideslip was less severe, in that the incremental changes in the local angles of sideslip were approximately equal to the static angle of sideslip. Flow conditions near the wing tip were found to be critically dependent on ...
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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

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

Date: February 2, 1954
Creator: Alford, William J , Jr & Pasteur, Thomas B , Jr
Description: None
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Small-scale transonic investigation of a 45 degree sweptback wing of aspect ratio 4 with combinations of nose-flap deflections and wing twist

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

Date: January 9, 1953
Creator: Alford, William J , Jr & Spreemann, Kenneth P
Description: None
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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

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

Date: May 25, 1955
Creator: Alford, William J , Jr; Silvers, H Norman & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: September 11, 1952
Creator: Alford, William J., Jr.
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 indicate that the addition of the fins to the body insures static longitudinal stability and provides essentially linear variations of the lift and pitching moment at small angles of attack throughout the Mach number range. The slopes of the lift and pitching-moment curves vary slightly with Mach number and show only small effects due to the angle of roll.
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Small-Scale Transonic Investigation of the Effects of Partial-Span Leading-Edge Camber on the Aerodynamic Characteristics of a 50 Deg 38' Sweptback Wing of Aspect Ratio 2.98

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

Date: June 23, 1952
Creator: Alford, William J., Jr. & Byrnes, Andrew L., Jr.
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 uncambered wing and the other had the forward 45 percent of the chord cambered over the outboard 55 percent of the span. The semispan wings had 50deg 38ft sweepback of their quarter-chord lines, aspect ratio of 2.98, taper ratio of 0.45, and modified NACA 64A-series airfoil sections tapered in thickness ratio. Lift, drag, pitching moment, and root-bending moment were obtained for these configurations. The results indicated that, for the wing-alone configuration, use of the partial-span leading-edge camber provided an increase in maximum lift-drag ratios up to a Mach number of 0.95, after which no gain was realized. For the wing-fuselage combination, the partial-span leading-edge camber appeared to cause no gain in maximum lift-drag ratio throughout the test range of Mach numbers. The ...
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Preliminary Low-Speed Wind-Tunnel Investigation of Some Aspects of the Aerodynamic Problems Associated with Missiles Carried Externally in Positions Near Airplane Wings

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

Date: December 27, 1954
Creator: Alford, William J., Jr.; Silvers, H. Norman & King, Thomas J., Jr.
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 traversed by the missiles showed abrupt gradients in both flow angularity and in local dynamic pressure. Through the use of aerodynamic data on the isolated missile and the measured flow-field characteristics, the longitudinal forces and moments acting on the missile while in the presence of the wing-fuselage combination could be estimated with fair accuracy. Although the lateral forces and moments predicted were qualitatively correct, there existed some large discrepancies in absolute magnitude.
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Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Date: August 19, 1957
Creator: Algranti, J. S.; Braithwaite, W. M. & Fenn, D. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison of two methods for computing the wave of wing-body combinations

A comparison of two methods for computing the wave of wing-body combinations

Date: April 7, 1955
Creator: Alksne, Alberta
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of the effects of plan-form taper on the aerodynamic characteristics of symmetrical unswept wings of varying aspect ratio

Experimental investigation of the effects of plan-form taper on the aerodynamic characteristics of symmetrical unswept wings of varying aspect ratio

Date: May 29, 1953
Creator: Allen, Edwin C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of a triangular wing in conjunction with a fuselage and horizontal tail to determine downwash and longitudinal-stability characteristics : transonic bump method

Investigation of a triangular wing in conjunction with a fuselage and horizontal tail to determine downwash and longitudinal-stability characteristics : transonic bump method

Date: August 17, 1951
Creator: Allen, Edwin C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Estimation of the forces and moments acting on inclined bodies of revolution of high fineness ratio

Estimation of the forces and moments acting on inclined bodies of revolution of high fineness ratio

Date: November 14, 1949
Creator: Allen, H Julian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

Date: January 1, 1955
Creator: Allen, H Julian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Problems of performance and heating of hypersonic vehicles

Problems of performance and heating of hypersonic vehicles

Date: March 5, 1956
Creator: Allen, H Julian & Neice, Stanford E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of flow over inclined bodies of revolution

Characteristics of flow over inclined bodies of revolution

Date: March 5, 1951
Creator: Allen, H Julian & Perkins, Edward W
Description: Experimental force, moment, and center-of-pressure variations for a large number of bodies of revolution have been compared with the calculated characteristics based on the approximate theory developed in NACA-RM-A9I26. The bodies varied in fineness ratio from 4.5 to 21.1, from blunt unboattailed bodies to airship hulls, and the experimental results are given for widely varying Mach number ranges of angle of attack. It is shown that the lift and drag characteristics are fairly accurately predicted by the theory but that the actual center of pressure is more rearward than the theory indicates. Experimental pressure distributions and visual-flow studies which have been used to investigate the characteristics of the cross flow for inclined bodies of revolution have demonstrated that the development of the cross flow with distance along the body on a long body of constant about a circular cylinder impulsively started from rest. This factor assists in explaining the observed differences between center-of-pressure location determined from experiment and that calculated using the approximate theory.
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