Author: Franklin W. DiederichPublisher:
ISBN:
Category :
Languages : en
Pages : 12
Book Description
A Simple Approximate Method for Obtaining Spanwise Lift Distributions Over Swept Wings
Author: Franklin W. DiederichPublisher:
ISBN:
Category :
Languages : en
Pages : 12
Book Description
A Simple Approximation Method for Obtaining the Spanwise Lift Distribution
Author: Oskar SchrenkPublisher:
ISBN:
Category : Lift (Aerodynamics)
Languages : en
Pages : 6
Book Description
The approximation method described makes possible lift-distribution computations in a few minutes. Comparison with an exact method shows satisfactory agreement. The method is of greater applicability than the exact method and includes also the important case of the wing with end plates.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1082
Book Description
Technical Note
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
Book Description
An Improved Approximate Method for Calculating Lift Distributions Due to Twist
Author: James C. SivellsPublisher:
ISBN:
Category : Lift (Aerodynamics)
Languages : en
Pages : 35
Book Description
A new method is presented for calculating the lift distribution due to twist which gives a much closer approximation than the empirical method of Schrenk (NACA TM 948) and requires about the same amount of computing. The new method, based on lifting-line theory, makes use of the lift distribution due to angle of attack and takes into account the aspect ratio of the wing. Examples are presented for the four main types of twist: symmetrical, antisymmetrical, continuous, and discontinuous. The applicability of the method for swept wings is also presented.
A Project Method for Calculating Spanwise Lift Distributions on Swept and Unswept Wings at Subsonic Speeds
Author: Bernd ChudobaResearch Memorandum
Author: Tests of Two-blade Propellers in the Langley 8-foot High-speed Tunnel to Determine the Effect on Propeller Performance of a Modification of Inboard Pitch Distribution
Author: James Benjamin DelanoPublisher:
ISBN:
Category : Propellers, Aerial
Languages : en
Pages : 724
Book Description
This paper presents propeller characteristics for two propellers that differ only in inboard pitch distribution. The forward Mach number range extended to 0.062 and the blade-angle range was from 20 to 55 degrees. Section thrust-coefficient data are also presented to afford a more detailed analysis of the effects of modifying the pitch distribution of the inboard sections of a propeller.
Effect of Structural Flexibiligy on Aircraft Loading
Author: Theodore H. H. PianPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 216
Book Description
Author: