Results 111 to 120 of about 43,130 (185)

NASA research objectives and roles [PDF]

open access: yes
A chronology of airfoil development is presented in order to put the present NASA airfoil program in perspective. The impact of the NACA series airfoils is considered. Development of advanced analytical and experimental methods for the design and for the
Gessow, A.
core   +1 more source

Low-speed aerodynamic characteristics of a 13.1-percent-thick, high-lift airfoil [PDF]

open access: yes
Low speed sectional characteristics of a high lift airfoil are studied and a comparison is made of those characteristics with the predictions of the theoretical methods used in the airfoil's design.
Awker, R. W.   +2 more
core   +1 more source

Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors. Part 1: Analysis and design of stages A, B, and C [PDF]

open access: yes
A conventional rotor and stator, two dual-airfoil tandem rotors, and one dual-airfoil tandem stator were designed. The two tandem rotors were each designed with different percentages of the overall lift produced by the front airfoil.
Brent, J. A.   +2 more
core   +1 more source

Design of transonic airfoil sections using a similarity theory [PDF]

open access: yes
A study of the available methods for transonic airfoil and wing design indicates that the most powerful technique is the numerical optimization procedure. However, the computer time for this method is relatively large because of the amount of computation
Nixon, D.
core   +1 more source

Weak wall boundary conditions for compressible flows. [PDF]

open access: yesEng Comput
Jaiswal M   +4 more
europepmc   +1 more source

Transonic airfoil design using Cartesian coordinates [PDF]

open access: yes
A numerical technique for designing transonic airfoils having a prescribed pressure distribution (the inverse problem) is presented. The method employs the basic features of Jameson's iterative solution for the full potential equation, except that ...
Carlson, L. A.
core   +1 more source

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