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Drag and Longitudinal Trim at Low Lift of the North American YF-100A Airplane at Mach Numbers from 0.76 to 1.77 as Determined from the Flight Test of a 0.11-Scale Rocket Model

Description: Drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.76 to 1.77 as determined from the flight test of a 0.11-scale rocket model are presented herein. Also included are some longitudinal stability and some qualitative pitch-damping data.
Date: May 14, 1953
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

Effect of conical and flat sting-mounted windshields on the zero-lift drag of a flare-stabilized bluff body at Mach numbers from 0.6 to 1.15

Description: Report presenting zero-lift drag data for a flare-stabilized bluff body of fineness ratio 4.4 alone and with conical and flat windshields at a range of Mach and Reynolds numbers. The model with the flat windshield was found to have the lowest drag at Mach numbers up to 1.05, but there was little difference in drag among the models above 1.05.
Date: September 12, 1957
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

Free-flight investigation of jet effect on the low-lift drag and longitudinal trim of a supersonic interceptor-type airplane configuration with an overhanging tail boom at Mach numbers from 1.09 to 1.34

Description: Report presenting a rocket-powered free-flight model of an interceptor-type airplane with an overhanging tail boom with the jet on and off at a range of Mach numbers. Results regarding longitudinal trim, drag, and lift are provided.
Date: September 19, 1957
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

Low-lift drag and stability data from rocket models of a modified-delta-wing airplane with and without external stores at Mach numbers from 0.8 to 1.36

Description: Report presenting a flight investigation to determine the drag and stability at low lift coefficients of models of a modified-delta-wing airplane at a range of Mach and Reynolds numbers. A summary of the drag and stability data from the tests is provided.
Date: March 26, 1953
Creator: Mitcham, Grady L. & Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

Summary of the Aerodynamic Characteristics and Flying Qualities Obtained from Flights of Rocket-Propelled Models of an Airplane Configuration Incorporating a Sweptback Inversely Tapered Wing at Transonic and Low-Supersonic Speeds

Description: From Summary: "Flight tests have been conducted on rocket-propelled models of an airplane configuration incorporating a sweptback wing with inverse taper to investigate the drag, stability, and control characteristics at transonic and supersonic speeds. The models were tested with a conventional tail arrangement in the Mach number range from 0.55 to 1.2. In addition to the various aerodynamic parameters obtained, the flying qualities were computed for a full-scale airplane with the center-of-gravity location at 18 percent of the mean aerodynamic chord. Also, included in this investigation are drag measurements made on relatively simple fixed-control models tested with both conventional and V-tail arrangements."
Date: September 7, 1950
Creator: Mitcham, Grady L. & Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

A flight investigation to determine the effectiveness of Mach number 1.0, 1.2, and 1.41 fuselage indentations for reducing the pressure drag of a 45 degree sweptback wing configuration at transonic and low supersonic speeds

Description: Report presenting a flight investigation to determine the effectiveness of three fuselage indentations for reducing the pressure drag of a 45 degree sweptback-wing-body configuration at a range of Mach numbers. The results indicate that the supersonic area rule can be used to determine indentations with low pressure drag over a Mach number range in which the blunt leading edge is subsonic. Information about total drag and pressure drag is provided.
Date: May 16, 1957
Creator: Blanchard, Willard S., Jr. & Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Drag and longitudinal trim characteristics of a low-tail version of the North American YF-100A airplane as determined from the flight test at low lift of a 0.11-scale rocket-powered model at Mach numbers between 0.75 and 1.78

Description: Report presenting drag and longitudinal trim characteristics at low lift of a low-tail version of the North American YF-100A airplane as obtained from the flight test of a 0.11-scale rocket model at a range of Mach numbers. Longitudinal stability data and some qualitative damping-in-pitch data are also provided.
Date: March 29, 1954
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

Minimum drag of 0.11-scale rocket-powered models of the Chance Vought XF8U-1 airplane, with and without nose modifications, at Mach numbers between 0.85 and 1.30 : TED No. NACA DE 392

Description: Report presenting drag data obtained from flight tests of two scale rocket-powered models of the Chance Vought XF8U-1 airplane. Results regarding the minimum drag coefficient and effect of nose modifications are provided.
Date: June 14, 1954
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

A summary of the drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.75 to 1.77 as determined by flight tests of 0.11-scale rocket models

Description: Report presenting longitudinal trim and drag at low lift of the North American YF-100A airplane at a range of Mach numbers as obtained with rocket-propelled models for an airplane, with the horizontal tail removed, and with wing removed conditions. Results regarding drag, longitudinal trim, longitudinal stability, and flutter and buffet are provided.
Date: January 29, 1954
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

Summary of Low-Lift Drag and Directional Stability Data from Rocket Models of the Douglas XF4D-1 Airplane with and without External Stores and Rocket Packets at Mach Numbers from 0.8 to 1.38: TED No. NACA DE-349

Description: At the request of the Bureau of Aeronautics, Department of the Navy, an investigation at transonic and low supersonic speeds of the drag and longitudinal trim characteristics of the Douglas XF4D-1 airplane is being conducted by the Langley Pilotless Aircraft Research Division. The Douglas XF4D-1 is a jet-propelled, low-aspect-ratio, swept-wing, tailless, interceptor-type airplane designed to fly at low supersonic speeds. As a part of this investigation, flight tests were made using rocket- propelled 1/10- scale models to determine the effect of the addition of 10 external stores and rocket packets on the drag at low lift coefficients. In addition to these data, some qualitative values of the directional stability parameter C(sub n beta) and duct total-pressure recovery are also presented.
Date: July 18, 1952
Creator: Mitcham, Grady L.; Blanchard, Willard S., Jr. & Hastings, Earl C., Jr.
Partner: UNT Libraries Government Documents Department

Flight-Determination of the Low-Lift Drag and Longitudinal Stability of a 1/10-Scale Rocket-Powered Model of the Douglas XF4D-1 Airplane at Mach Numbers from 0.7

Description: A flight investigation has been made to determine the drag and longitudinal stability of a 1/10- scale model of the Douglas XF4D-1 airplane from Mach numbers 0.7 to 1.4 at lift coefficients near zero. The drag rise occurred near M = 0.95. The external drag coefficient was a constant value of about 0.012 at subsonic speeds up to the point of drag rise where it increased abruptly to a value of 0.030 at M = 1.0 followed by a more gradual increase to a value of 0.038 at M = 1.25. The model indicated that, at 35,000 feet and a level-flight free-stream Mach number of 1.0, the drag of the full-scale airplane would exceed the thrust available from an XJ40-WE-8 engine with after-burning. The transonic trim change was small. The aerodynamic center moved gradually from the most forward location of 21.0-percent mean aerodynamic chord at M = 0.9 to the most rearward location of 40-percent mean aerodynamic chord at M = 1.25. The damping in pitch was low.
Date: 1951
Creator: Mitcham, Grady L.; Blanchard, Willard S., Jr. & Hastings, Earl C., Jr.
Partner: UNT Libraries Government Documents Department