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Theoretical span load distributions and rolling moments for sideslipping wings of arbitrary plan form in incompressible flow

Description: From Summary: "A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings, this requirement should not seriously restrict the application of the present method. The basic method derived herein requires a mechanical differentiation and integration to obtain the rolling moment for the general wing in sideslip."
Date: October 6, 1955
Creator: Queijo, M. J.
Partner: UNT Libraries Government Documents Department

Calculated effects of geometric dihedral on the low-speed rolling derivatives of swept wings

Description: Report presenting a simple theory to determine the effects of geometric dihedral angle on the rolling derivatives of swept wings. Equations and charts are given to show these effects. A comparison of experimental and theoretical results for the theory are provided.
Date: October 1948
Creator: Queijo, M. J. & Jaquet, Byron M.
Partner: UNT Libraries Government Documents Department

Low-speed experimental investigation of the magnus effect on various sections of a body of revolution with and without a propeller

Description: Report presenting an investigation at low speed to determine the Magnus effect on various sections of a body of revolution of which several sections could be rotated either as individual units or in combinations. The investigation included the measurement of the Magnus effect on the body alone and on the body with a three-blade propeller.
Date: August 1957
Creator: Queijo, M. J. & Fletcher, Herman S.
Partner: UNT Libraries Government Documents Department

Approximate relations and charts for low-speed stability derivatives of swept wings

Description: Contains derivations, based on a simplified theory, of approximate relations for low-speed stability derivatives of swept wings. Method accounts for the effects and, in most cases, taper ratio. Charts, based on the derived relations, are presented for the stability derivatives of untapered swept wings. Calculated values of the derivatives are compared with experimental results.
Date: May 1948
Creator: Toll, Thomas A. & Queijo, M. J.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the effect of vertical-tail size and length of fuselage shape and length on the static lateral stability characteristics of a model with 45 degree sweptback wing and tail surfaces

Description: Report presenting an investigation to determine the effects of vertical-tail size and length and of fuselage shape and length on the lateral static stability characteristics of a model with a wing and vertical tails with the quarter-chord line swept back 45 degrees. Results indicated that the directional instability of the fuselage was about two-thirds as large as that predicted by classical theory. Results regarding wing characteristics, fuselage characteristics, vertical-tail effectiveness, and interference effects are provided.
Date: August 1950
Creator: Queijo, M. J. & Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department

The effects of high-lift devices on the low-speed stability of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow

Description: Contains results of tunnel tests to determine effects of various combinations of split flaps, slats, and nose slats on the stability characteristics of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow.
Date: November 9, 1948
Creator: Queijo, M. J. & Lichtenstein, Jacob H.
Partner: UNT Libraries Government Documents Department

Calculated subsonic span loads and resulting stability derivatives of unswept and 45 degrees sweptback tail surfaces in sideslip and in steady roll

Description: Report presenting a calculation of subsonic span loads and the resulting stability derivatives for a systematic series of vertical- and horizontal-tail combinations in sideslip and in steady roll in order to provide information embracing a wide range of probable tail configurations. The results of this investigation, which had a wide range of geometric variables than previous studies, showed trends which were in general agreement with the results of previous investigations.
Date: October 1954
Creator: Queijo, M. J. & Riley, Donald R.
Partner: UNT Libraries Government Documents Department

Effects of vertical fins near the nose of the fuselage on the directional and damping-in-yaw stability derivatives of an airplane model under steady-state and oscillatory conditions

Description: A wind-tunnel investigation has been made at low speed to determine the effects of vertical fins placed ahead of the vertical tail on the directional stability and damping-in-yaw characteristics of a swept-wing model under steady-state oscillatory conditions. Various sizes of fins were used above and below the fuselage center line. The vertical-tail size also was varied.
Date: December 1956
Creator: Queijo, M. J. & Wells, Evalyn G.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the effect of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with 45 degree sweptback wing and tail surfaces

Description: An investigation was made to determine the effects of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with wing and vertical tails having the quarter-chord lines swept back 45 degrees. The results indicate that the directional instability of the various isolated fuselages was about two-thirds as large as that predicted by classical theory.
Date: June 5, 1950
Creator: Queijo, M. J. & Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department

Supplementary analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass and aerodynamic parameters

Description: Report presenting the application of an estimation of the derivative of yawing moment due to rolling to the dynamic lateral stability characteristics of the Bell X-2. Results regarding the airplane with flaps and gear retracted and airplane with flaps and gear lowered are provided.
Date: June 26, 1950
Creator: Michael, William H., Jr. & Queijo, M. J.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the effect of tab balance on tab and control-surface characteristics

Description: An investigation was conducted to furnish data on the effect of tab balance on tab and control-surface characteristics. The airfoil tested had a modified NACA 65(1)-012 contour with a plain flap having a chord equal to 25 percent of the wing chord and with a tab having a chord equal to 25 percent of the flap chord and having several nose shapes and overhang lengths. The results of the investigation indicated that, in general, tab balance affected tab hinge-moment characteristics in much the same manner that flap balance affects flap hinge-moment characteristics. A moderate amount of tab balance did not seem to have any adverse effect on flap hinge-moment characteristics.
Date: August 1947
Creator: Brewer, Jack D. & Queijo, M. J.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the low-speed static and rotary stability derivatives of a 0.13-scale model of the Douglas D-558-II airplane in the landing configuration

Description: Report presenting a wind-tunnel investigation to determine the low-speed static and rotary stability derivatives of a model of the Douglas D-558-II airplane in the landing configuration. Results regarding the static longitudinal characteristics, static lateral characteristics, characteristics in rolling flow, and characteristics in yawing flow are provided.
Date: August 27, 1952
Creator: Queijo, M. J. & Wells, Evalyn G.
Partner: UNT Libraries Government Documents Department

Low-speed wind-tunnel investigation of lateral control characteristics of a 60 degrees triangular-wing model having half-delta tip controls

Description: Report presenting a low-speed investigation in the stability tunnel to determine the lateral control characteristics of a 60 degree triangular wing model equipped with half-delta tip controls with areas of 5, 10, and 15 percent of the wing area. Results regarding lateral control effectiveness, rolling effectiveness, and a comparison of control and effectiveness with theory are provided.
Date: November 27, 1951
Creator: Jaquet, Byron M. & Queijo, M. J.
Partner: UNT Libraries Government Documents Department

Analysis of the effects of various mass, aerodynamic, and dimensional parameters on the dynamic lateral stability of the Douglas D-558-2 Airplane

Description: Report presenting an investigation of the effects of various mass, aerodynamic, and dimensional parameters on the dynamic lateral stability of the Douglas D-558-2 airplane. Results regarding an airplane with the flaps and gear retracted, airplane at sea level with flaps deflected 50 degrees and landing gear lowered, and effect of assumed modifications to airplane are provided.
Date: April 15, 1949
Creator: Queijo, M. J. & Michael, W. H., Jr.
Partner: UNT Libraries Government Documents Department

Analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters

Description: Report presenting an analysis of the dynamic-lateral-stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters by means of calculations of the period and rate of damping of the lateral oscillation. Results regarding the airplane with flaps and gear retracted, airplane with flaps and gear lowered, and effects of assumed modifications to the airplane are provided.
Date: August 10, 1949
Creator: Michael, W. H., Jr. & Queijo, M. J.
Partner: UNT Libraries Government Documents Department

Investigation of effects of geometric dihedral on low-speed static stability and yawing characteristics of an untapered 45 degree sweptback-wing model of aspect ratio 2.61

Description: Report presenting an investigation to determine the effects of geometric dihedral on the low-speed static stability and yawing characteristics of an untapered 45 degree sweptback wing model of aspect ratio 2.61. Dihedral was found to have an effect on the rolling moment due to sideslip, lift-curve slope, and variation of lateral force with sideslip, but did not have an effect on the yawing moment due to sideslip.
Date: September 1948
Creator: Queijo, M. J. & Jaquet, Byron M.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Static Longitudinal and Lateral Stability Characteristics of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane

Description: An experimental investigation has been made in the Langley stability tunnel at low speed to determine the static longitudinal and lateral stability characteristics of a l/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller-blade angle were investigated briefly for the complete model. Most of the tests were made through an angle-of-attack range from about -4 deg. to 29 deg, and the thrust-coefficient range was from 0 t o 0.7. In order to expedite distribution of these data to interested persons, no analysis of the data has been prepared for this report,.
Date: February 11, 1953
Creator: Queijo, M. J.; Wolhart, W. D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Tests of a Modified Koppers Aeromatic Impeller-Generator Combination, TED No. NACA ARR 2901

Description: From Summary: "An investigation was conducted in the 6- by 6-foot test section of the Langley stability tunnel on a modified Koppers Aeromatic wind-driven impeller-generator combination. This investigation consisted of a few fixed pitch tests and a series of variable pitch tests. The fixed pitch tests indicated that the impeller should operate between the blade-pitch angles of 20 and 32deg at the specified output of 11.7 kilowatts in order to remain within the specified rotational speed of from 5000 to 8000 rpm for airspeeds of from 130 to 175 miles per hour. The requirement that the impeller maintain rotational speeds of - between 5000 and 8000 rpm as the impeller output varied from 0 to ll.7 kilowatts at airspeeds of from 130 to 175 miles per hour was not met at any time during the variable pitch tests."
Date: December 26, 1946
Creator: Queijo, M. J.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the effects of surface-covering distortion on the characteristics of a flap having undistorted contour maintained for various distances ahead of the trailing edge

Description: Report presenting tests of a modified NACA 65(sub 1)-012 airfoil with a 30-percent airfoil-chord flap with contours simulating various distorted surface-covering shapes for the purpose of investigating practicability of reducing distortion effects to a negligible amount by maintaining an undistorted contour over a small part of the flap chord.
Date: May 1947
Creator: Toll, Thomas A.; Queijo, M. J. & Brewer, Jack D.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of the effects of chordwise wing fences and horizontal-tail position on the static longitudinal stability characteristics of an airplane model with a 35 degree sweptback wing

Description: From Summary: "Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal tail located well above the extended wing-chord plane indicated static longitudinal instability at moderate angles of attack for all configurations tested. An investigation therefore was made to determine whether the longitudinal stability could be improved by the use of chordwise wing fences, by lowering the horizontal tail, or by a combination of both."
Date: November 24, 1954
Creator: Queijo, M. J.; Jaquet, Byron M. & Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department

Preliminary measurements of the aerodynamic yawing derivatives of a triangular, a swept, and an unswept wing performing pure yawing oscillations, with a description of the instrumentation employed

Description: Report presenting an investigation to determine the effect of motion periodicity on the aerodynamic derivatives due to yawing velocity and yawing acceleration for a 60 degree delta wing, a 45 degree sweptback wing, and an unswept wing. Results were obtained from steady-state yawing-flow tests and tests of model performing pure sinusoidal yawing oscillations. Results regarding the static longitudinal characteristics, derivatives due to yawing velocity, and derivatives due to yawing acceleration are provided.
Date: April 2, 1956
Creator: Queijo, M. J.; Fletcher, Herman S.; Marple, C. G. & Hughes, F. M.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Low-Speed Static Stability and Control Characteristics of a Model of Bell MX-776

Description: An investigation has been made in the Langley stability tunnel to determine the low-speed static stability and control characteristics of a model of the Bell MX-776. The results of the investigation indicated that the basic model configuration was longitudinally stable in the angle-of-attack range from about -16 deg. to 16 deg. but that the stability was a minimum near O deg angle of attack. The data indicated an aerodynamic-center position about 0.64 body diameters behind the center of gravity at low angles of attack. Reduction in the size of the front horizontal fins increased the longitudinal stability. With 20 percent of the span of the normal front horizontal fins cut off the aerodynamic center was about 1.04 body diameters behind the center of gravity, and with front horizontal fins having the same area as the front vertical fins, the aerodynamic center was 2.26 body diameters behind the center of gravity (at low angles of attack).
Date: July 6, 1949
Creator: Queijo, M. J. & Michael, W. H., Jr.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.
Date: July 23, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the rolling stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model. Most of the tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.
Date: May 20, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department