Full-scale Aerodynamic Characteristics of a Propellar Installed on a Small Twin-engine Aircraft Wing Panel PDF Download
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Author:
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Category :
Languages : en
Pages : 26
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Author: John W. Draper
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 82
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Book Description
This report presents the results of an investigation conducted in the Langley 300 mph 7- 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author: Norman S. Land
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 14
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Introduction: The tests described in this report were made on a 1/8-full-size model of a large, long-range, twin-engine flying boat in NACA tank no. 1. The airplane had a wing loading of 43.9 pounds per square foot and a power loading of 11.5 pounds per horsepower. Its arrangement was such that 34.2 percent of the wing area and 56.1 percent of the horizontal tail area were included within the fore-and-aft projection of the propeller disks. The model was fitted with leading-edge slats to make the angle of attack for maximum lift coefficient correspond with that of the airplane at the low Reynolds number associated with the tank tests (3.28 x 105 based on the mean aerodynamic chord and the get-away speed of the model). The model was equipped with two three-blade metal propellers of scale diameter and form, power for which was furnished by two variable-frequency alternating-current motors. Sufficient power was available to develop scale thrust with the propellers. The tests were divided into two parts: (1) aerodynamic tests to determine the effect of the slipstream and thrust from the powered propellers on the lift and trimming-moment characteristics, and (2) hydrodynamic tests to determine the effect of the powered propellers on the range of stable locations of the center of gravity.
Author: Marvin Pitkin
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 82
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Summary: Tests have been made in the Langley free-flight tunnel to determine the influence of mode of propeller rotation and vertical-tail design upon the trim characteristics of a model of a twin-engine airplane with one engine inoperative. The test model was mounted on a trim stand, which allowed freedom in roll and yaw under conditions simulating those required by the NACA and the Army Air Forces for asymmetric-power operation in flight. The seven vertical-tail designs tested included three tails of low aspect ratio and of different area, one twin tail of low aspect ratio, two tails of high aspect ratio and with different rudder areas, and one all-movable tail of high aspect ratio equipped with a linked tab. All tests were made with the flaps down.
Author: Kenneth W. Goodson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
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"An investigation of the aerodynamic characteristics of a powered semispan tilting-shrouded-propeller configuration has been conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. The wing had an aspect ratio of 2.67 (based on wing span of 60 inches), a taper ratio of 0.67, and an NACA 2418 airfoil section with a 15-inch-diameter shrouded propeller mounted on the tip. The test results show that large nose-up pitching moments are obtained at transitional speeds of about 40 knots and duct angle of about 70°. Decelerating flight procedures further increases in the nose-up moment. Ground proximity reduces the nose-up pitching moments. The large nose-up moments can be trimmed by use of duct-exit control vanes. The results show that unloading the duct (shroud) by flying at a wing angle of attack of 15° reduces the power required by about 30 percent at 50 knots. Duct-lip stall produces large increases in power required. The results in general show that full-scale aerodynamic simulation can be made with small-scale wind-tunnel models if duct-lip separation at low Reynolds numbers is avoided."--Summary.
Author: Richard J. Margason
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 186
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Book Description
Author: Julian D. Maynard
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Category : Airplanes
Languages : en
Pages : 80
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Book Description
Author: Chester H. Wolowicz
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ISBN:
Category : Private planes
Languages : en
Pages : 300
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Book Description
Analytical procedures and design data for predicting the lateral-directional static and dynamic stability and control characteristics of light, twin engine, propeller driven airplanes for propeller-off and power-on conditions are reported. Although the consideration of power effects is limited to twin engine airplanes, the propeller-off considerations are applicable to single engine airplanes as well. The procedures are applied to a twin engine, propeller driven, semi-low-wing airplane in the clean configuration through the linear lift range. The calculated derivative characteristics are compared with wind tunnel and flight data. Included in the calculated characteristics are the spiral mode, roll mode, and Dutch roll mode over the speed range of the airplane.
Author: Albert J. Evans
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 102
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Book Description
An investigation of an NACA 10-(1.7)(062)-057-27 two-blade swept propeller has been conducted in the Langley 16-foot high-speed tunnel over a range of blade-angle setting from 20 to 60 degrees. The maximum value of helical tip Mach number was about 1.15.
