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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
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
Horizontal-tail parameters as determined from flight-test tail loads on a flexible swept-wing jet bomber

Horizontal-tail parameters as determined from flight-test tail loads on a flexible swept-wing jet bomber

Date: January 17, 1957
Creator: Aiken, William S , Jr & Fisher, Raymond A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Strain-Gage Measurements of Buffeting Loads on a Jet-Powered Bomber Airplane

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

Date: March 19, 1951
Creator: Aiken, William S., Jr. & See, John A.
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 were close to the natural frequencies of the structural components. The buffeting-load data, when extrapolated to low-altitude conditions, indicated loads on the elevators and stabilizers near the design limit loads. When the airplane was held in buffeting, the load increments were larger than when recovery was made immediately.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: February 20, 1947
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements of a swept-back wing having inverse taper as determined by flight tests at supersonic speeds

Drag measurements of a swept-back wing having inverse taper as determined by flight tests at supersonic speeds

Date: April 8, 1947
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: March 7, 1947
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigations at low supersonic speeds to determine the effectiveness of cones and a wedge in reducing the drag of round-nose bodies and airfoils

Flight investigations at low supersonic speeds to determine the effectiveness of cones and a wedge in reducing the drag of round-nose bodies and airfoils

Date: March 3, 1949
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: February 24, 1947
Creator: Alexander, Sidney R & Katz, Ellis
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests to determine the effect of taper on the zero-lift drag of wings at low supersonic speeds

Flight tests to determine the effect of taper on the zero-lift drag of wings at low supersonic speeds

Date: July 13, 1947
Creator: Alexander, Sidney R & Nelson, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: November 2, 1948
Creator: Alexander, Sidney R.
Description: 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 telemeters and a Doppler velocimeter radar unit. The results of this investigation indicated no unusual variation in the lateral acceleration characteristics. After the cessation of powered flight, the lateral oscillation quickly damped to zero. The data indicated that the airplane, at low lift coefficients, should not experience any abrupt trim changes until it attains a Mach number of 0.97. The change in normal-force coefficient associated with this trim change will amount to about 0.03 with the center of gravity located at 4.48% of the mean aerodynamic chord. At higher lift coefficients, on the basis of other data, the Mach number at which this trim change occurs would be expected to be decreased. The neutral point of the model at Mach numbers near 1.05 was estimated to ...
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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

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.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
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. ...
Contributing Partner: UNT Libraries Government Documents Department
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
Contributing Partner: UNT Libraries Government Documents Department
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
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department