A Simple Method of Estimating the Subsonic Lift and Damping in Roll of Sweptback Wings PDF Download
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Author: Edward C. Polhamus Publisher: ISBN: Category : Airplanes Languages : en Pages : 26
Book Description
A method of modifying existing correction factors of lifting-surface theory to account approximately for the effects of sweep has been derived, and these factors have been applied to existing lifting-line theories for the lift and damping in roll of swept wings. A comparison with experimental data in the low-speed and low lift range indicated good agreement for wings of any plan form. If the Glauert-Prandtl transformation is used, the formulas obtained can be applied to swept wings at subsonic speeds below the critical speed.
Author: Edward C. Polhamus Publisher: ISBN: Category : Airplanes Languages : en Pages : 26
Book Description
A method of modifying existing correction factors of lifting-surface theory to account approximately for the effects of sweep has been derived, and these factors have been applied to existing lifting-line theories for the lift and damping in roll of swept wings. A comparison with experimental data in the low-speed and low lift range indicated good agreement for wings of any plan form. If the Glauert-Prandtl transformation is used, the formulas obtained can be applied to swept wings at subsonic speeds below the critical speed.
Author: Frank S. Malvestuto Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 48
Book Description
Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-roll derivative for given values of aspect ratio, taper ratio, Mach number, and leading edge sweep.
Author: Alex Goodman Publisher: ISBN: Category : Aerofoils Languages : en Pages : 38
Book Description
The development of three methods for calculating the damping in roll through the normal flight range of lift coefficient for wing plan forms having various sweep angles, aspect ratios, and taper ratios is presented and comparisons between experimental and calculated results are made.
Author: Albert P. Martina Publisher: ISBN: Category : Aerofoils Languages : en Pages : 52
Book Description
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and yawing-moment coefficients due to rolling for unswept wings with or without flaps or ailerons. The methods allow the use of nonlinear section lift data together with lifting-line theory. Two calculated examples are presented in simplified computing forms in order to illustrate the procedures involved.
Author: S. S. Manson Publisher: ISBN: Category : Aeronautics Languages : en Pages : 730
Book Description
A review is presented of available information on the behavior of brittle and ductile materials under conditions of thermal stress and thermal shock. For brittle materials, a simple formula relating physical properties to thermal-shock resistance are derived and used to determine the relative significance of two indices currently in use for rating materials. The importance of simulating operating conditions in thermal-shock testing is deduced from the formula and is experimentally illustrated by showing that BeO could be both inferior or superior to Al2O3 in thermal shock depending on the testing conditions. For ductile materials, thermal-shock resistance depends upon the complex interrelation among several metallurgical variables which seriously affect strength and ductility. These variables are briefly discussed and illustrated from literature sources. The importance of simulating operating conditions in tests for rating ductile materials is especially to be emphasized because of the importance of testing conditions in metallurgy. A number of practical methods that have been used to minimize the deleterious effects of thermal stress and thermal shock are outlined.
Author: George C. Deutsch Publisher: ISBN: Category : Carbides Languages : en Pages : 694
Book Description
On a strength-to-weight ratio basis, ceramals appeared promising as gas-turbine-blade materials in the temperature range of 1600 to 2400 degrees F.
Author: Edward C. Polhamus
Author: Edward C. Polhamus
Author: Frank S. Malvestuto
Author: Alex Goodman
Author: Bernard Jr Spencer
Author: Albert P. Martina
Author: Bernard Spencer
Author: United States. National Advisory Committee for Aeronautics
Author: S. S. Manson
Author: Edwin J. Saltzman
Author: George C. Deutsch