Showing papers on "Vortex lift published in 1971"
TL;DR: In this article, the leading edge suction analogy for predicting low speed lift and drag due-to-lift characteristics of sharp edge delta and related wing planforms was used to predict a low speed aircraft.
Abstract: Leading edge suction analogy for predicting low speed lift and drag-due-to-lift characteristics of sharp edge delta and related wing planforms
497 citations
01 Apr 1971
TL;DR: In this paper, the authors predict aerodynamic characteristics of arrow, delta, and diamond wing platforms using Prandtl-Glauert transformation for predicting the flight characteristics of a single-winged aircraft.
Abstract: Predicting aerodynamic characteristics of arrow, delta, and diamond wing platforms using Prandtl-Glauert transformation
33 citations
01 Sep 1971
TL;DR: In this paper, thin-shock-layer theory is used to study the lifting properties of caret and flat-bottomed wings and of wings with concave lower surfaces, and it is found that significant gains in lift coefficient can be achieved with moderately recessed lower surfaces.
Abstract: It has been suggested that in the conditions of lifting re-entry caret wings are likely to have higher lift coefficients than flat-bottomed wings with the same ratio of lift to drag. Thus, for given speed and wing loading, they can re-enter at higher altitudes with a consequent reduction in stagnation point heating rate. In this paper thin-shock-layer theory is used to study the lifting properties of caret and flat-bottomed wings and of wings with concave lower surfaces. It is found that significant gains in lift coefficient can be achieved with moderately recessed lower surfaces. These results hold for both perfect and real gas flows.
5 citations
01 Aug 1971
TL;DR: Induced lift characteristics of swept wing-body configuration with partial-span jet in flow at Mach 0.20 to 1.30 were derived in this article, where the full-span wing was used.
Abstract: Induced lift characteristics of swept wing-body configuration with partial-span jet in flow at Mach 0.20 to 1.30
4 citations
22 Oct 1971
TL;DR: In this article, the authors deal with the lift increase of small span-chord ratio wings with lateral fluid jets in the plane of the wings, directed along the span, and some theoretical considerations as well as the experimental results obtained in the wind tunnel for a series of wings with different spanchord ratios are presented.
Abstract: : The article deals with the lift increase of small span-chord ratio wings with lateral fluid jets in the plane of the wings, directed along the span. Some theoretical considerations as well as the experimental results obtained in the wind tunnel for a series of wings with different span-chord ratios are presented.
3 citations
01 Jul 1971
2 citations
01 Aug 1971
1 citations
TL;DR: In this paper, the authors measured the geometry of the trailing vortex generated behind a jet-flapped wing and found that these vortices persist for some time and have maximum tangential velocities which increase linearly with the lift coefficient.
Abstract: : The purpose of the investigation was to measure the geometry of the trailing vortex generated behind a jet-flapped wing Such vortices can pose a serious hazard to aircraft that penetrate them Previous investigations performed on conventional wings indicate that these vortices persist for some time and have maximum tangential velocities which increase linearly with the lift coefficient As future aircraft may employ high lift devices such as jet-flapped wings, the vortices generated could be even stronger Two semispan models of a jet-flapped wing were tested in a subsonic wing tunnel Parameters varied during testing included the jet flap angle, angle of attack, aspect ratio, and jet momentum coefficient Vortex measurements were obtained using a vortex meter which measured the rotational speed of the fluid within the vortex Values obtained were numerically integrated to yield the tangential velocity and circulation distributed through the vortex Experimental results indicate that the maximum tangential velocity increases to a maximum and then decreases with continually increasing jet blowing At high values of jet blowing, the vortex was found to decay rapidly downstream (Author)