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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 109 records · Page 6
All sourcesNASA NTRSDOE OSTI
NASA NTRS1955

Flight Measurements of Base Pressure on Bodies of Revolution with and Without Simulated Rocket Chambers

Base pressures were measured on fin-stabilized bodies of revolution with and without rocket chambers and with and without a converging afterbody. At Mach numbers between 0.7 and 1.2, the results show that the presence of a "cold" rocket chamber increased the pressure (less suction) over the center portion of the bases. The effects of rocket chambers on pressures near the edge of the bases were not as consistent throughout the Mach number range nor as appreciable at most speeds as were the effects of pressures measured on the center line.

Peck, Robert F↗
NASA NTRS1955

Transonic Zero-Lift Drag Tests of Four Equivalent-Body-of-Revolution Models Representing Variations of the Convair F-102 Airplane

Four 0.01643-scale equivalent-body-of-revolution models, designed to aid in the evaluation of the relative merits of various degrees of redesign of the existing (1955) Convair F-102 airplane, were launched from the helium gun at Wallops Island, Va., to determine their zero-lift drag at Mach numbers from 0.8 to 1.3. The data are presented with only sufficient analysis to validate their general subsonic level. Estimated values of the friction drag are presented at all Mach numbers to allow a comparison of the pressure drag values alone.

Stoney, William E., Jr.↗
NASA NTRS1989

Computational/experimental study of the flowfield on a body of revolution at incidence

A joint computational-experimental study of the vortical flowfield on a pointed body of revolution is undertaken. The incompressible Navier-Stokes equations are solved numerically for steady flow around an ogive-cylinder at angle of attack. The three-dimensional vortical flow is investigated, with emphasis on the tip and the near-wake region. Comparisons of computational results with results of a companion towing-tank experiment are presented at Re(L) = 1000. Results of a wind tunnel experiment at Re(L) = 820,000, featuring use of a seven-hole pressure probe, also are presented. It was observed that at the low Reynolds number of the towing tank study, the leeside flow was symmetric at the angles of attack considered. For the same configuration at the higher Reynolds number of the wind tunnel study, the flow was asymmetric under equivalenat conditions for some of the angles of attack studied. The topology of the flow is discussed and conclusions are drawn concerning the growth and stability of the primary vortices.

Zilliac, G. G.↗
NASA NTRS1957

Base Pressure at Supersonic Speeds on Two-dimensional Airfoils and on Bodies of Revolution with and Without Fins Having Turbulent Boundary Layers

An analysis has been made of available experimental data to show the effects of most of the variables that are more predominant in determining base pressure at supersonic speeds. The analysis covers base pressures for two-dimensional airfoils and for bodies of revolution with and without stabilizing fins and is restricted to turbulent boundary layers. The present status of available experimental information is summarized as are the existing methods for predicting base pressure. A simple semiempirical method is presented for estimating base pressure. For two-dimensional bases, this method stems from an analogy established between the base-pressure phenomena and the peak pressure rise associated with the separation of the boundary layer. An analysis made for axially symmetric flow indicates that the base pressure for bodies of revolution is subject to the same analogy. Based upon the methods presented, estimations are made of such effects as Mach number, angle of attack, boattailing, fineness ratio, and fins. These estimations give fair predictions of experimental results. (author)

LOVE EUGENE S↗
NASA NTRS1951

The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack

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.

Seiff, Alvin↗
NASA NTRS1952

Forces and Moments on Pointed Blunt-nosed Bodies of Revolution at Mach Numbers from 2.75 to 5.00

Results of tests to determine the aerodynamic forces and moments on bodies of revolution at angles of attack from 0 degrees to 25 degrees are presented and compared with theory. Cones and ogives of fineness ratios 3 to 7 and two blunt-nosed body shapes with fineness ratios 3 and 5 were tested at Mach numbers from 2.75 to 5.00. Reynolds numbers were from 0.5 million to 6.4 million, depending on Mach number and body fineness ratio.

Dennis, David H↗
NASA NTRS1948

The effects of aerodynamic heating and heat transfer on the surface temperature of a body of revolution in steady supersonic flight

An approximate method for determining the convective cooling requirement in the laminar boundary-layer region of a body of revolution in high-speed flight was developed and applied to an example body. The cooling requirement for the example body was determined as a function of Mach number, altitude, size, and a surface-temperature parameter. The maximum value of Mach number considered was 3.0 and the altitudes considered were those within the lower constant-temperature region of the atmosphere (40,000 to 120,000 ft.). The extent of the laminar boundary layer was determined approximately at each condition as a function of the variables considered.

Scherrer, Richard↗
NASA NTRS1976

Flow over a slender body of revolution at supersonic velocities

The theory of small disturbances is applied to the calculation of the pressure distribution and drag of a closed body of revolution traveling at supersonic speeds. It is shown that toward the rear of the body the shape of the pressure distribution is similar to that for subsonic flow. For fineness ratios between 10 and 15 the theoretical wave drag is of the same order as probable values of the frictional drag.

Jones, R. T.↗
NASA NTRS1946

Flow over a slender body of revolution at supersonic velocities

The theory of small disturbances is applied to the calculation of the pressure distribution and drag of a closed body of revolution traveling at supersonic speeds. It is shown that toward the rear of the body the shape of the pressure distribution is similar to that for subsonic flow. For fineness ratios between 10 and 15 the theoretical wave drag is of the same order as probable values of the frictional drag.

FLOW VELOCITY, HIGH-SUPERSONIC↗
NASA NTRS1961

The Drag Coefficient of Parabolic Bodies of Revolution Operating at Zero Cavitation Number and Zero Angle of Yaw

The form-drag coefficient of parabolic bodies of revolution with fineness ratios greater than 1 operating at zero angle of yaw and zero cavitation number is determined both theoretically and experimentally. Agreement between theory and experiment is very good, The theoretical form-drag coefficient of paraboloids is about half the form-drag coefficient of cones of comparable fineness ratio.

Johnson, Virgil E., Jr.↗
NASA NTRS1953

Drag Measurements on Equivalent Bodies of Revolution of Six Configurations of the Convair MX-1964 (Originally MX-1626) Proposed Supersonic Bomber

Tests on equivalent bodies of revolution of six configurations of the Consolidated Vultee Aircraft Corporation proposed supersonic bomber (Convair MX-1964) have indicated that it is possible to reduce the drag of the configuration by designing it to have a favorable area distribution. The method of NACA RM L53I22c to predict the peak pressure drag of a configuration on the basis of its area distribution gave generally good agreement with the subject models.

Hall, James Rudyard↗
NASA NTRS1951

Aerodynamic Characteristics of a Slender Cone-cylinder Body of Revolution at a Mach Number of 3.85

An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for small angles of attack. The measured mean skin-friction coefficients agreed well with theoretical values obtained for laminar flow over cones.

FLOW, LAMINAR↗