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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 ...
Contributing Partner: UNT Libraries Government Documents Department