2,629 Matching Results

Search Results

Advanced search parameters have been applied.

The Effect of a Change in Body Shape on the Loading of a 45 Degree Sweptback Wing-Body Combination at Transonic Speeds

Description: Memorandum presenting an investigation made in the 8-foot transonic tunnel of the pressure distribution on a wing-body combination with a 45 degree sweptback wing with aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The chordwise pressure distributions, which were determined at various spanwise stations, indicate that the flow about the two configurations is the same. Results regarding basic pressure measurements and loading and aerodynamic characteristics are provided.
Date: April 2, 1954
Creator: Loving, Donald L.
Partner: UNT Libraries Government Documents Department

Theoretical investigation of the effects upon lift of a gap between wing and body of a slender wing-body combination

Description: Report presenting the application of slender-body theory to the study of effects upon lift produced by the presence of a gap between the wing and cylindrical body of a slender wing-body combination.Two conditions were studied, one in which the wing and body have the same angle of attack and the other in which only the deflected wing had an angle of incidence to the free stream.
Date: August 1954
Creator: Dugan, Duane W. & Hikido, Katsumi
Partner: UNT Libraries Government Documents Department

Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination

Description: Report presenting the effects of an angle of incidence of 4 degrees and body indentation on wing loads of a sweptback wing-body combination at a range of Mach numbers. The wing had an aspect ratio of 4, taper ratio of 0.3, 45 degrees of sweepback of the quarter-chord line, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the effect of incidence and effect of body indentation are provided.
Date: January 11, 1956
Creator: Platt, Robert J., Jr.
Partner: UNT Libraries Government Documents Department

Body Image as Mediated by Age, Sex, and Relationship Status

Description: Traditionally, body image research has focused on young women. However, there are indications of cultural shifts which extend physical appearance pressures to both men and women, as well as to middle-aged and older adults. Two hundred and ten subjects were administered objective body image measures including the Figure Rating Scale, the Body Shape Questionnaire, and the Multidimensional Body-Self Relations Questionnaire, as well as projective measures including the Holtzman Inkblot Technique and the Draw-A-Person. The NEO-Five Factor Inventory and the Social Anxiety Subscale were also used to explore variables which might covary with body image. A 3 X 2 X 2 Multivariate Analysis of Covariance (MANCOVA) was utilized with social desirability as the covariate.
Date: December 1993
Creator: Cooper, Caren C. (Caren Connie)
Partner: UNT Libraries

Investigation of the Effect of Indentation on an M-Plan-Form-Wing--Body Combination at Transonic Speeds

Description: Report presenting an investigation of the effect of body indentation on the aerodynamic characteristics of an M-plan-form-wing-body combination for a variety of angles of attack and Mach numbers. The wing was tested on a plain body and a body with an indentation that was 65 percent of that required for a Mach number of 1.0. Results regarding drag characteristics, lift characteristics, pitching-moment characteristics, and estimated results are provided.
Date: August 4, 1954
Creator: Loving, Donald L.
Partner: UNT Libraries Government Documents Department

An Experimental Technique for the Objective Quantification of Body-Image Distortion

Description: The purpose of this study was to develop an experimental technique to objectively measure the deviation between an individual's perception of his body image and his actual image. In addition, this technique was utilized to compare the accuracy of perception of body image between institutionalized and non-institutionalized individuals. Half of each subject category was also compared in terms of performance on an additional perceptual task unrelated to body image.
Date: July 1971
Creator: Lemon, James M.
Partner: UNT Libraries

The Relationship of Body Cathexis and Motor Performance in Junior High School Girls of Three Ethnic Groups

Description: This investigation is concerned with the problem of determining whether or not a significant relationship exists between body cathexis and motor performance in junior high school girls. In addition, the study investigates whether or not there are significant differences among Negro, white, and Mexican--American girls and seventh-,eighth-, and ninth-grade girls in body cathexis and motor ability performance.
Date: August 1971
Creator: Bedford, Jane
Partner: UNT Libraries

On the Mutual Reaction of Wings and Body

Description: "At the suggestion of Professor Von Karman, I have made a few theoretical investigations of the mutual reaction of the wings and body of an airplane. There was assumed as the basis of my calculations, a strongly idealized body shape, namely, a cylinder extended to infinity at both ends and having its axis parallel to the direction of motion of the airplane. The results are to be regarded as rough approximations for a long airplane body and also for an airship with fins. In my calculations, I have considered only a monoplane in which the axis of the wing is rectilinear" (p. 1).
Date: February 1927
Creator: Lennertz, J.
Partner: UNT Libraries Government Documents Department

A pressure-distribution investigation of the aerodynamic characteristics of a body of revolution in the vicinity of a reflection plane at Mach numbers of 1.41 and 2.01

Description: The changes in the aerodynamic characteristics of a body of revolution with a fineness ratio of 8 have been determined at Mach numbers of 1.41 and 2.01, a Reynolds number, based on body length, of 4.54 x 10 to the 6th power, and angles of incidence of 0 degrees and plus or minus 3 degrees as the position of the body is varied with respect to a reflection plane. The data are compared with theoretical results.
Date: January 20, 1955
Creator: Gapcynski, John P. & Carlson, Harry W.
Partner: UNT Libraries Government Documents Department

A study of the zero-lift drag-rise characteristics of wing-body combinations near the speed of sound

Description: Comparisons of the shock phenomena and drag-rise increments for representative wing and central-body combinations with those for bodies of revolution with the same axial distributions of cross-sectional area normal to the air stream. An investigation was also presented of representative wing-body combinations with the body so indented that the axial distributions of cross-sectional areas for the combinations were the same as that for the original body. Results regarding unswept wing and cylindrical body, delta wing and cylindrical body, swept wing and cylindrical body, swept wing and curved body, and applications of the transonic drag-rise concept are provided.
Date: September 3, 1952
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department

Investigation of symmetric body indentations designed to reduce the transonic zero-lift wave drag of a 45 degree swept wing with an NACA 64A006 section and with a thickened leading-edge section

Description: Report presenting a wind-tunnel investigation at Reynolds numbers of about 7,000,000 based on the mean aerodynamic chord of the wing and over a range of Mach numbers. Two airfoils were tested to evaluate the effect of a large leading-edge radius with increased thickness over the forward 40 percent of the chord on the reliability of the predictions of the supersonic area rule. Results regarding the comparison of basic- and modified-wing models, comparison of experimental and computed drag coefficients, and a comparison of indentations are provided.
Date: March 19, 1957
Creator: Holdaway, George H. & Hatfield, Elaine W.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0008-63 section

Description: Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0008-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 1, 1951
Creator: Smith, Donald W. & Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

An experimental investigation of two methods for reducing transonic drag of swept-wing and body combinations

Description: Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.
Date: April 29, 1955
Creator: McDevitt, John B.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: twisted and cambered triangular wing of aspect ratio 2 with NACA 0003-63 thickness distribution

Description: This report presents the results of an investigation to ascertain the lift, drag, and pitching moment of a wing-body combination having a triangular wing of aspect ratio 2 with NACA 0003-63 thickness distribution in streamwise planes and twisted and cambered for a nearly elliptical span load distribution. Results are shown for Mach numbers from 0.60 to 0.90 and from 1.30 to 1.70 at Reynolds numbers of 3.0 million and 7.5 million.
Date: June 12, 1951
Creator: Hall, Charles F. & Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: effect of Reynolds number at supersonic Mach numbers on the longitudinal characteristics of a wing twisted and cambered for uniform load

Description: Report presenting a wind-tunnel investigation of the longitudinal characteristics of a wing-body combination with a wing with leading edge swept back 63 degrees. Lift, drag, and pitching-moment measurements were made over a range of Mach and Reynolds numbers. Results regarding the general characteristics and effect of Reynolds number are provided.
Date: October 9, 1950
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with NACA 0005-63 section

Description: Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 4 and NACA 0005-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 2, 1951
Creator: Heitmeyer, John C. & Stephenson, Jack D.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0005-63 section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0005-63 sections in streamwise planes has been investigated at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 1, 1951
Creator: Smith, Donald W. & Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane tapered wing of aspect ratio 3.1 with 3-percent-thick rounded-nose section

Description: Report presenting a wing-body combination with a plane tapered wing of aspect ratio 3.1, taper ratio of 0.39, and 3-percent-thick, rounded-nose sections in streamwise planes at subsonic and supersonic Mach numbers. The lift, drag, and pitching moment are presented for a range of Mach numbers and Reynolds numbers.
Date: July 9, 1952
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 2 with NACA 0003-63 section

Description: Report presenting testing of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0003-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 2, 1951
Creator: Heitmeyer, John C. & Smith, Willard G.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Twisted and cambered triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution

Description: Report presenting the results of a wind-tunnel investigation at subsonic and supersonic Mach numbers to determine the aerodynamic characteristics of a wing-body combination with a triangular wing of aspect ratio 2. The mean surface of the wing was twisted and cambered to support a nearly elliptical span load distribution at Mach number 1.53 and a lift coefficient of 0.25. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: April 10, 1952
Creator: Heitmeyer, John C. & Petersen, Robert B.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with 3-percent-thick rounded nose section

Description: Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick rounded nose sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: August 29, 1951
Creator: Heitmeyer, John C. & Hightower, Ronald C.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 3 with NACA 0003-63 section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 3 and NACA 0003-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: September 13, 1951
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with 3-percent-thick, biconvex section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick, biconvex sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: June 8, 1951
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department