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 Decade: 1940-1949
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Aerodynamic characteristics of an airfoil-forebody swept flying-boat hull with a wing and tail swept back 51.3 degrees at the leading edge

Aerodynamic characteristics of an airfoil-forebody swept flying-boat hull with a wing and tail swept back 51.3 degrees at the leading edge

Date: September 9, 1949
Creator: Naeseth, Rodger L & Macleod, Richard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30

Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30

Date: November 10, 1948
Creator: Riebe, John M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Aerodynamic characteristics of several NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Date: May 27, 1948
Creator: Loftin, Laurence K , Jr & Poteat, M Irene
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Date: March 13, 1947
Creator: Riebe, John M. & Naeseth, Rodger L.
Description: An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of three deep-stepped planing-tail flying-boat hulls differing only in the amount of step fairing. The hulls were derived by increasing the unfaired step depth of a planing-tail hull of a previous aerodynamic investigation to a depth about 92 percent of the hull beam. Tests were also made on a transverse-stepped hull with an extended afterbody for the purpose of comparison and in order to extend and verify the results of a previous investigation. The investigation indicated that the extended afterbody hull had a minimum drag coefficient about the same as a conventional hull, 0.0066, and an angle-of-attack range for minimum drag coefficient of 0.0057 which was 14 percent less than the transverse stepped hull with extended afterbody; the hulls with step fairing had up to 44 percent less minimum drag coefficient than the transverse-stepped hull, or slightly more drag than a streamlined body having approximately the same length and volume. Longitudinal and lateral instability varied little with step fairing and was about the same as a conventional hull.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of two all-movable wings tested in the presence of a fuselage at a Mach number of 1.9

Aerodynamic characteristics of two all-movable wings tested in the presence of a fuselage at a Mach number of 1.9

Date: October 28, 1948
Creator: Conner, D William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

Date: June 30, 1949
Creator: Bandettini, Angelo & Reed, Verlin D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic effects of rockets and fuel tanks mounted under the swept-back wing of an airplane model

The aerodynamic effects of rockets and fuel tanks mounted under the swept-back wing of an airplane model

Date: April 23, 1948
Creator: Boddy, Lee E & Morrill, Charles P , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic measurements made during Navy investigation of human tolerance to wind blasts

Aerodynamic measurements made during Navy investigation of human tolerance to wind blasts

Date: March 11, 1947
Creator: Loving, Donald L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Date: October 7, 1949
Creator: Mccormack, Gerald M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics at a Mach number of 1.53 including effect of small variations of sweep

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics at a Mach number of 1.53 including effect of small variations of sweep

Date: January 26, 1949
Creator: Madden, Robert T
Description: Measured values of lift, drag, and pitching moment at a Mach number of 1.53 and Reynolds numbers of 0.31, 0.62, and 0.84 million are presented for a wing-fuselage combination having a wing leading-edge sweep angle of 63 degrees, an aspect ratio of 3.42, a taper ratio of 0.25, and an NACA 64A006 section in the stream direction. Data are also presented for sweep angles of 57.0 degrees, 60.4 degrees, 67.0 degrees, and 69.9 degrees. The experimentally determined characteristics were less favorable than indicated by the linear theory but the experimental and theoretical trends with sweep were in good agreement. Boundary-layer-flow tests showed that laminar boundary-layer separation was the primary cause of the differences between experiment and theory.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics for symmetrical wing sections at high subsonic and moderate supersonic Mach numbers

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics for symmetrical wing sections at high subsonic and moderate supersonic Mach numbers

Date: July 7, 1949
Creator: Mas, Newton A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics throughout the subsonic speed range with the wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics throughout the subsonic speed range with the wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Date: August 15, 1949
Creator: Jones, J Lloyd & Demele, Fred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects at subsonic speeds of a constant-chord elevon on a wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects at subsonic speeds of a constant-chord elevon on a wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Date: December 5, 1949
Creator: Jones, J Lloyd & Demele, Fred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects of split flaps, elevons, and leading-edge devices at low speed

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects of split flaps, elevons, and leading-edge devices at low speed

Date: May 19, 1949
Creator: Hopkins, Edward J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation at a Mach number of 1.53 to determine the effects of cambering and twisting the wing for uniform load at a lift coefficient of 0.25

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation at a Mach number of 1.53 to determine the effects of cambering and twisting the wing for uniform load at a lift coefficient of 0.25

Date: May 6, 1949
Creator: Madden, Robert T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation of a large-scale model at low speed

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation of a large-scale model at low speed

Date: January 21, 1949
Creator: Mccormack, Gerald M & Walling, Walter C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon

Date: October 11, 1948
Creator: Reynolds, Robert M & Smith, Donald W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical characteristics of a three-blade propeller having NACA 10-(3)(08)-03 blades

Aeronautical characteristics of a three-blade propeller having NACA 10-(3)(08)-03 blades

Date: October 29, 1948
Creator: Davidson, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Date: April 24, 1947
Creator: Beeler, De E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Date: April 8, 1947
Creator: Foster, Gerald V.
Description: The XF-12 airplane was designed by Republic Aviation Corporation to provide the Army Air Forces with a high performance, photo reconnaissance aircraft. A series of air-stream surveys were made n the vicinity of the empennage of a 1/8.33-scale powered model of the XF-12 airplane in the Langley 19-foot pressure tunnel. Surveys of the vortical-tail region were made through a range of yaw angles of plus or minus 20 degrees at a high and low angle of attack. The horizontal-tail surveys were made over a fairly wide range of angles of attack at zero degrees yaw. Several power and flap conditions were investigated. The results are presented in the form a dynamic pressure ratios, sidewash angles, and downwash angles plotted against vertical distance from the fuselage center line. The results of the investigation indicate that a vertical tail located in a conventional position would be in a field of flow where the dynamic pressure ratios at the horizontal tail to be increased; for equal lift coefficients, the effect of power or flap deflection on the direction of flow at any particular point in the region of the horizontal tail is small.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-chamber performance of British Rolls-Royce Nene II engine I : standard 18.75-inch-diameter jet nozzle

Altitude-chamber performance of British Rolls-Royce Nene II engine I : standard 18.75-inch-diameter jet nozzle

Date: September 23, 1949
Creator: Barson, Zelmar & Wilsted, H D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-chamber performance of British Rolls-Royce Nene II engine II : 18.41-inch-diameter jet nozzle

Altitude-chamber performance of British Rolls-Royce Nene II engine II : 18.41-inch-diameter jet nozzle

Date: October 26, 1949
Creator: Wilsted, H D; Armstrong, J C & Vincent, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude cooling investigation of the R-2800-21 engine in the P-47G airplane II : investigation of the engine & airplane variables affecting the cylinder temperature distribution

Altitude cooling investigation of the R-2800-21 engine in the P-47G airplane II : investigation of the engine & airplane variables affecting the cylinder temperature distribution

Date: October 9, 1946
Creator: Pesman, Gerard J & Kaufman, Samuel J
Description: The data obtained from cooling tests of an R-2800-21 engine installed in a p-47G airplane were studied to determine which engine and airplane operation variables were mainly responsible for the extremely uneven temperature distribution among the 18 engine cylinders obtained at the medium and high engine-power conditions. The tests consisted of flights at altitudes from 5000 to 35,000 feet for the normal range of engine and airplane operation. The results of the study showed that a flow condition in the induction system associated with the wide-open throttle position, which affected either the fuel air or charge distribution, was primarily responsible for the uneven temperature distribution. For the range of fuel-air ratios tested (0.080 to 0.102), the temperature distribution remained essentially unchanged. The individual effects of thrust-axis inclination, cowl-flap opening, and quantity of auxiliary air were found to be secondary in importance. At low angles of throttle opening, engine speed was found to have little effect on the temperature pattern.
Contributing Partner: UNT Libraries Government Documents Department
Altitude cooling investigation of the R-2800-21 engine in the P-47g airplane III : individual-cylinder temperature reduction by means of intake-pipe throttle and by coolant injection

Altitude cooling investigation of the R-2800-21 engine in the P-47g airplane III : individual-cylinder temperature reduction by means of intake-pipe throttle and by coolant injection

Date: October 9, 1946
Creator: Bell, E Barton; Valerino, Michael F & Manganiello, Eugene J
Description: Flight tests were conducted on a R-2800-21 engine in the P-47G airplane to determine the effect on the wall temperatures of cylinder 10 of throttling the charge in the intake pipe and of injecting a water-ethanol coolant into the intake pipe. Cylinder 10 was chosen for this investigation because it runs abnormally hot (head temperatures of the order of 45 F higher than those of the next hottest cylinder) at the medium and high-power conditions. Tests with interchanged cylinders showed that the excessive temperatures of cylinder 10 were inherent in the cylinder location and were not due to the mechanical condition of the cylinder assembly. Throttling the charge in the intake pipe is a simpler method than coolant injection into the intake pipe particularly when only one cylinder is considerably hotter than any other. Coolant injection into the individual cylinders is a more efficient method than throttling in the intake pipe and is warranted when several cylinders are to be cooled or when parts of the complex equipment required are already available.
Contributing Partner: UNT Libraries Government Documents Department