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