Measurements of the Pressure Distribution on the Horizontal Tail Surface of a Typical Propeller-driven Pursuit Airplane in Flight PDF Download
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Author: Melvin Sadoff
Publisher:
ISBN:
Category : Fighter planes
Languages : en
Pages : 17
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Book Description
Measurements were made in sideslipping flight at a Mach number of 0.50 of the pressure distribution over the horizontal tail surfaces of a tractor-propeller-driven pursuit airplane, to determine the effects of angle of sideslip and propeller operation on the tail-load distribution. Measurements were also made on the tail-load distribution on the horizontal tail in steady unaccelerated flight over a Mach number range of 0.30 to 0.79 and 0.30 to 0.74, respectively, for the power-on and power-off conditions.
Author: Melvin Sadoff
Publisher:
ISBN:
Category : Fighter planes
Languages : en
Pages : 17
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Book Description
Measurements were made in sideslipping flight at a Mach number of 0.50 of the pressure distribution over the horizontal tail surfaces of a tractor-propeller-driven pursuit airplane, to determine the effects of angle of sideslip and propeller operation on the tail-load distribution. Measurements were also made on the tail-load distribution on the horizontal tail in steady unaccelerated flight over a Mach number range of 0.30 to 0.79 and 0.30 to 0.74, respectively, for the power-on and power-off conditions.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
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Book Description
The total horizontal-tail load and the root bending moment increments calculated by the use of existing rational procedures are compared with experimental values obtained in pull-up push-down maneuvers on a representative propeller-driven pursuit-type airplane for six different combinations of power, indicated airspeed, and pressure altitude. The computed loads were determined for the experimental elevator motions, and for two estimated linear design motions. There is also presented a comparison between the computed and the experimental load distributions. Briefly touched upon are two abbreviated static methods for predicting the maximum up-loads in pull-up push-down maneuvers.
Author: Melvin Sadoff
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 29
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Book Description
Pressure-distribution measurements were made in steady straight and accelerated flight over both sides of the horizontal-tail surface of a typical pursuit airplane up to a Mach number of 0.79. The results showed that a sharply increasing down-load was required to balance the increased diving moment of the wing-fuselage-propeller group at Mach numbers above about 0.70. There was little change, up to a Mach number of about 0.65, of the tail-load gradient (rate of increase of tail load for a unit change in acceleration factor); beyond that Mach number, however, a rapid decrease of tail-load gradient to a Mach number of about 0.73 and then a very sharp increase up to a Mach number of 0.785 was noted. The root bending moments increased considerably on the right tail and decreased, to a lesser extent, on the left tail at the higher Mach numbers, resulting in increased fuselage torsional moments at high speeds. At the higher values of lift coefficient (0.5 to 0.8), there was little change of the lateral distance to the center pressure up to a Mach number of about 0.73; at the highest speed and at low lift coefficients (0 to 0.1) the center of pressure was inboard approximately 3 feet on the left tail and 1.5 feet on the right tail as compared with the values at lower speeds. It appears that satisfactory quantitative data on total tail loads may be obtained from measurements at four stations, equally spaced along the entire tail span.
Author:
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 61
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Book Description
The total horizontal-tail load and root bending-moment increments calculated by the use of existing rational procedures are compared with the experimental values obtained in abrupt pull-up push-down maneuvers obtained on a representative pursuit-type airplane. The computed loads were determined for the experimental motions and for two estimated linear design motions. The results showed that the actual maximum maneuvering tail loads obtainable in flight could be predicted satisfactorily from either the experimental elevator motions measured in the maneuvers of from the estimated linear elevator motions, provided that good quantitative knowledge was had of pertinent aerodynamic parameters.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 616
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Book Description
Author: A. Kahane
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 578
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Book Description
Charts are presented to show the pressure rise that is obtainable in an engine-cooling installation with a typical airfoil-type propeller-speed fan. The charts cover fans of the stator-rotor, rotor-stator, and rotor alone configurations, with blades incorporating both the highly cambered 65-series blower-blade sections and the conventional low-cambered airfoil sections. The effects of operation of a geared fan with rotational speeds limited by compressibility considerations and the effects of initial rotational inflow are indicated. Use of the charts to predict the pressure rise obtainable with any fan of the types considered is illustrated in a sample calculation.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 434
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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 446
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1160
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Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1620
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