Development of a Method for Predicting the Performance and Stresses of VTOL-type Propellers PDF Download
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Author: Andrew Richard Trenka
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 134
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Book Description
The report presents a theoretical method which allows the prediction of performance and stress characteristics of a single VTOL-type of propeller-wing-nacelle combination operating in various flight conditions from hovering through transition and into axial flight. The method includes (1) the effects of a distorted wake, i. e., the effects of contraction and radial and axial velocity variations; (2) the effects of hovering close to the ground; (3) the interference effects from a nacelle and wing buried in the propeller slipstream. Also presented are experimental thrust and torque data. However, because of the insufficient accuracy of the experimental data collected, no definite evaluation of the model is made. (Author).
Author: Andrew Richard Trenka
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 134
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Book Description
The report presents a theoretical method which allows the prediction of performance and stress characteristics of a single VTOL-type of propeller-wing-nacelle combination operating in various flight conditions from hovering through transition and into axial flight. The method includes (1) the effects of a distorted wake, i. e., the effects of contraction and radial and axial velocity variations; (2) the effects of hovering close to the ground; (3) the interference effects from a nacelle and wing buried in the propeller slipstream. Also presented are experimental thrust and torque data. However, because of the insufficient accuracy of the experimental data collected, no definite evaluation of the model is made. (Author).
Author: Andrew R. Trenka
Publisher:
ISBN:
Category : Propellers
Languages : en
Pages : 206
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Book Description
Experimental performance and blade stresses measured on a three-bladed VTOL-type propeller tested in free air are presented. The isolated propeller was tested over ranges of prop speed, forward velocity, blade angle setting, and thrust axis to free-stream angle. Correlation with a theoretical method of predicting propeller performance and blade stresses was made. It was found that when the propeller was operating in a flight condition for which the theory was developed, correlation between theory and experiment was good. When the propeller was operating in a flight condition where very small positive or negative effective angles of attack were encountered, correlation between theory and experiment was poor. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 978
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 712
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Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 732
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Author: Irving Carl Statler
Publisher:
ISBN:
Category : Short take-off and landing aircraft
Languages : en
Pages : 466
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Author: F. A. DuWaldt
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 110
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Book Description
The report presents the development of a wake model for a lifting propeller (rotor) in ground effect and the computational procedure used to determine the spacial distribution of wake vorticity and the induced velocity field accompanying that vorticity distribution. Sample calculations for a two-bladed rotor were carried out on an IBM 7044 computer. Locations of wake vortical elements and the associated induced velocities at selected field points are presented for advance ratios of 0, 0.02, 0.05, and 0.10 for an H/R (ratio of rotor height above ground to rotor radius) of 1.0. Also, a few results for a hovering case with H/R = 0.5 are presented. A calculated root-mean-square velocity map is compared with measured hovering data (time averaged) and good agreement is obtained in the outer half of the slipstream. The implications of computed results with respect to the flow field at a horizontal stabilizer or tail rotor are noted as examples of the use of the model. The wake vortex model used for these calculations is a distorted continuous helix emanating from each blade tip. (Author).
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 928
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Author:
Publisher:
ISBN:
Category : Government reports announcements & index
Languages : en
Pages : 1018
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Author:
Publisher:
ISBN:
Category : American literature
Languages : en
Pages : 812
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