A Method for Estimating Heat Requirements for Ice Prevention on Gas-heated Hollow Propeller Blades PDF Download
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Author: V. H. Gray
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 602
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Book Description
A detailed method is presented for determining temperature and flow minimums of heated gas necessary for ice prevention of hollow propellers with evaluation of surface temperatures, gas pressures, tip nozzle areas, flow passages, and heat source input.
Author: V. H. Gray
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 602
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Book Description
A detailed method is presented for determining temperature and flow minimums of heated gas necessary for ice prevention of hollow propellers with evaluation of surface temperatures, gas pressures, tip nozzle areas, flow passages, and heat source input.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994
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Author: United States. Federal Aviation Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 64
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 616
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
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Author: John A. Axelson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 696
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Book Description
An investigation of the two-dimensional aerodynamic characteristics of an NACA 64A010 airfoil with a slat has been conducted in the Mach number range from 0.25 to 0.85, with a corresponding Reynolds number range from 3.4 million to 8.1 million. Two families of slat positions were investigated, one with the slat leading edge extended forward along the airfoil chord line, and the other with the slat extended forward and displaced below the chord line.
Author: Robert V. Hess
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 734
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Book Description
The accuracy of the result obtained in a fundamental paper by Kantrowitz (NACA TN 1225) that a small short-time lowering of the back pressure in steady, shock-free, transonic diffuser flow causes a stationary or trapped shock to form near the critical sonic channel throat is investigated by considering the contribution of a higher-order term in the short-time calculations which was neglected in Kantrowitz's paper. In this higher approximation to the short-time effects, the shock is no longer stationary or trapped unless it is supported by a negative steady-flow back pressure; the result thus is no long in disagreement with steady-flow solutions for stationary shocks.
Author: Elbridge Z. Stowell
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 748
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Book Description
The landing of a simplified airplane structure, consisting of a uniform beam for the wings, a concentrated mass for the fuselage, and a linear spring for the landing gear, is analyzed exactly and is compared with several approximate solutions. The approximate solutions which neglect elasticity in the determination of landing-gear reaction but consider elasticity in computations of stresses give results of good accuracy and indicate that drop tests in which rigid masses are used may be a satisfactory approach to the landing problem.
Author: United States. Munitions Board. Aircraft Committee. Subcommittee on Air Force-Navy-Civil Aircraft Design Criteria
Publisher:
ISBN:
Category :
Languages : en
Pages : 508
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
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Book Description
