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  • 1
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    The Base Pressure at Supersonic Speeds on Two-Dimensional Airfoils and Bodies of Revolution (With and Without Fins) Having Turbulent Boundary Layers (1953)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An analysis has been made of available experimental data to show the effects of most variables that are predominant in determining base pressure at supersonic speeds. Two dimensional bases and bases of bodies of revolution, restricted to turbulent boundary layers, are covered.
    Keywords: Aerodynamics
    Type: NACA-RM-L53C02
    Format: application/pdf
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  • 2
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    Two-Dimensional Potential Flow Past an Ordinary Thick Wing Profile (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: This report deals with the development of a method which gives a lucid and convenient solution of the flow conditions in the vicinity of a common, thick airfoil section wherein the thickness of the profile is taken into account. The method consists in making the airfoil the streamline in a parallel flow by disposing on its mean line certain source and vortex distributions the fields of which are superposed on the parallel flow. These distributions of singularities are secured for the generalized Karman-Trefftz profile by means of conformal transformation from the flow about a circle. Five different distribution functions are afforded for the density of superposition, which combine in a specified manner to the necessary distributions of singularity and represent a generalized Karman-Trefftz profile in parallel flow. For these profiles the speed for each of the five distributions is then computed independently of the angle of attack.
    Keywords: Aerodynamics
    Type: NACA-TM-1023
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  • 3
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    Lift, Drag, and Pitching Moment of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds: Triangular Wing of Aspect Ratio 2 with NACA 0005-63 Thickness Distribution, Cambered and Twisted for a Trapezoidal Span Load Distribution (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A wing-body combination having a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, and twisted and cambered for a trapezoidal span load distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.60 to 0.90 and 1.30 to 1.70 at a Reynolds number of 3.0 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers.
    Keywords: Aerodynamics
    Type: NACA-RM-A50K27a
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  • 4
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    The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The subject of this paper is the drag of the nose section of bodies of revolution at zero angle of attack. The magnitude of the nose drag in relation to the total drag is very distinctly a function of the body design and the Mach number. It can range from a very small fraction of the total drag of the order of 10 percent to a very large fraction as high as 80 percent. The natural objective of nose design is to minimize the drag, but this objective is not always the primary one. Sometimes other factors overshadow the desire for minimum drag. The most conspicuous example of this is the proposal of guidance engineers that large-diameter spheres and other very blunt shapes be used at the nose tip. This paper will attempt to discuss both phases of the problem, noses for minimum drag and noses with very blunt tips. The state of the theory will also be reviewed and recent theoretical developments described, since the theory still remains a very valuable tool for assaying the effects of compromises in design and departure from shapes for which experimental data are available.
    Keywords: Aerodynamics
    Type: Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers; 1-12; NACA-RM-A51J25|NACA Conference on Aerodynamic Design Problems of Supersonic Guided Missiles; Oct 02, 1951 - Oct 03, 1951; Moffett Field, CA; United States
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  • 5
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    Base Pressure on Wings and Bodies with Turbulent Boundary Layers (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: At present there is no satisfactory theory for calculating the pressure which acts at the blunt base of an object traveling at supersonic velocity. In fact, the essential mechanism determining the base pressure is only imperfectly understood. As a result, the existing knowledge of base pressure is based almost entirely on experiments. The main object of this paper is to summarize the principal results of the many wind tunnel and free flight measurements of base pressure on both bodies of revolution and blunt trailing edge airfoils. A relatively simple method of estimating base pressure is presented, and an indication is given as to how the characteristics of base pressure play an essential role in determining the shape of an aerodynamically efficient object for supersonic flight.
    Keywords: Aerodynamics
    Type: Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers; 13-30; NACA-RM-A51J25|NACA Conference on Aerodynamic Design Problems of Supersonic Guided Missiles; Oct 02, 1951 - Oct 03, 1951; Moffett Field, CA; United States
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  • 6
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    Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The three papers collected here are: 'The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack.', 'Base Pressure on Wings and Bodies with Turbulent Boundary Layers', and 'Flow over Inclined Bodies'. The subject of the first paper is the drag of the nose section of bodies of revolution at zero angle of attack. The main object of the second paper is to summarize the prinicpal results of the many wind tunnel and free flight measurements of base pressure on both bodies of revolution and blunt trailing edge airfoils.
    Keywords: Aerodynamics
    Type: NACA-RM-A51J25
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  • 7
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    Damping in a Roll of a Missile Configuration with a Modified Triangular Wing and a Cruciform Tail at a Mach Number of 1.52 (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The damping-in-Toll stability derivatives of a missile configuration and its components were determined both experimentally and theoretically. The tests were conducted at a Mach number of 1.52 and at a Reynolds number, based on the mean aerodynamic chord of the wing, of 0.82 x 10(exp 6). The experimental damping derivative of the wing-body combination was 67 percent of the theoretical value. The difference is believed to have resulted mainly from the fact that the theory is not strictly applicable when the Mach number normal to the leading edge is almost unity, which was the case in the present investigation. For the tail-body combination the damping derivative was 86 percent of the theoretical value. In this case, the difference is believed to have been caused partially by mutual interference between the tail surfaces and partially by the low Reynolds number of the flow over the tail. It was found that the damping of the complete configuration was not equal to the sum of the damping derivatives of the components because of the effect of the wing downwash on the damping of the tail.
    Keywords: Aerodynamics
    Type: NACA-RM-A51A03
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  • 8
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    Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
    Keywords: Aerodynamics
    Type: NACA-WR-L-678
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  • 9
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    Tests at Mach Number 1.62 of a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces (1952)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An investigation at a Mach number of 1.62 was made in the Langley 9-inch supersonic tunnel of a series of missile configurations having tandem lifting surfaces of low aspect ratio and of newly equal span. Some of the variables investigated were interdigitation angle, wing and tail plan form, and longitudinal location of wing with respect to tail. All configurations were tested through an angle-of-attack range from -5 deg to 15 deg at roll angles of 0 deg and 45 deg. Lift, drag, and pitching moment data are presented, together with center-of-pressure locations and tail-lift efficiency factors.
    Keywords: Aerodynamics
    Type: NACA-RM-L51J15
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  • 10
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    The Use of the Rolled-up Vortex Concept for Predicting Wing-tail Interference and Comparison with Experiment at Mach Number of 1.62 for a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces (1952)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The method for predicting wing- tail interference whereby the trailing vortex system behind lifting wings is replaced by fully rolled-up vortices has been applied to the calculation of tail efficiency parameters, lift characteristics, and center -of-pressure locations for a series of generalized missile configurations. The calculations have been carried out with assumed and experimental vortex locations, and comparisons made with experimental data. The measured spanwise locations of the vortices for the inline case were found to be in good agreement with the asymptotic values computed from the center of gravity of the vorticity using the method of Lagerstrom and Graham. For the interdigitated configurations the measured spanwise locations were in only fair agreement with the asymptotic locations computed for the inline case. The vertical displacement of the vortices with angle of attack for both inline and interdigitated configurations was small. The method utilizing the rolled -up vortex concept was shown to give good results in the prediction of tail efficiency variations with angle of attack for inline configurations. Not as good correlation with experiment was shown for the interdigitated configurations. Complete configuration lift -curve slopes and center -of-pressure locations, obtained using t ail efficiency calculations together with the characteristics of the components obtained from available theoretical methods, showed excellent correlation with experimental results.
    Keywords: Aerodynamics
    Type: NACA-RM-L52H05
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