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1

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INVESTIGATION OF STATIC PRESSURES AND BOUNDARY-LAYER CHARACTERISTICS ON THE FORWARD PARTS OF NINE FUSELAGES OF VARIOUS CROSS-SECTIONAL SHAPES AT M INFINITY EQUAL 2.01 (1957)

Hasel, L. E. ; Kouyoumjian, W. L.

In: CASI

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Publikationsdatum: 2019-05-11

Beschreibung: Boundary layer characteristics of fuselages of various cross sectional shapes at static pressure

Schlagwort(e): AIRCRAFT

Materialart: NACA-RM-L56I13

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2

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Nuclear logistic carrier (1957)

Smith, R. L. ; Johnson, P. G. ; Miser, J. W.

In: CASI

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Publikationsdatum: 2005-04-26

Schlagwort(e): GENERAL

Materialart: NACA 1957 Flight Propulsion Conf.; p 1-12

Format: text

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3

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Satellite and space propulsion systems (1957)

Baldwin, L. V. ; English, R. E. ; Lubarsky, B. ; [weitere]

In: CASI

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Publikationsdatum: 2005-03-24

Schlagwort(e): GENERAL

Materialart: NACA 1957 Flight Propulsion Conf.; p 27-65

Format: text

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4

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Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01 (1957)

Kouyoumjian, W. L.

In: CASI

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Publikationsdatum: 2019-05-31

Beschreibung: A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor plate, and modifications to the area of the boundary-layer diverter bleed slots. The highest overall pressure recovery at an angle of attack of 0 deg (average total-pressure recovery, 0.84 mass-flow ratio, 0.98) was achieved with configuration having an inlet leading-edge sweep angle of 58 deg with no leading-edge stagger. Stagger was found to improve the angle-of- attack performance, but at a sacrifice in inlet efficiency for an angle of attack of 0 deg. The boundary-layer diverter floor height, of the order of one boundary-layer thickness, was satisfactory for bypassing the fuselage boundary layer. The boundary-layer diverter-plate bleed slots were effective in increasing the total-pressure recovery of the inlet. The total-pressure-recovery contour plots, taken at the compressor-face station, indicate the existence of high-velocity "cores" throughout the inlet operating range.

Schlagwort(e): Aerodynamics

Materialart: NACA-RM-SL56L12

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5

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Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399 (1957)

Dickens, Waldo L. ; Hastings, Earl C., Jr.

In: CASI

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Publikationsdatum: 2019-07-10

Beschreibung: A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by a combination of the modified inlets and extended rocket racks throughout the remainder of the test.

Schlagwort(e): Aerodynamics

Materialart: NACA-RM-SL57D30

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6

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Investigation of Drag and Static Longitudinal and Lateral Stability and Control Characteristics of 1/20-Scale Model of McDonnell F4H-1 Airplane at Mach Numbers of 1.57, 1.87, 2.16, and 2.53. Phase II Model (1957)

Turner, Kenneth L. ; Carmel, Melvin M.

In: CASI

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Publikationsdatum: 2019-07-12

Beschreibung: Tests were performed in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability and control characteristics of a 1/20-scale model of the McDonnell F4H-1 airplane at Mach numbers of 1 57, 1 87, 2.16, and 2.53. This is the second phase in a series of tests performed on this model. The Reynolds numbers for these tests, based on the mean aerodynamic chord of the wing, are 1.446 x 10 (exp 6), 1.269 x 10 (exp 6), 1.116 x 10 (exp 6), and 0.714 x 10 (exp 6) at Mach numbers of 1.57, 1.87, 2.16, and 2.53, respectively. The model had a 12 deg. wing tip dihedral, a larger vertical tail, and a modified duct.

Schlagwort(e): Aerodynamics

Materialart: NACA-RM-SL7A14

Format: application/pdf

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