Download or read book Stability and Control Tests of a 3 4 Scale Model of the KP 69 Airplane in the NACA Full Scale Tunnel written by and published by . This book was released on 1943 with total page 133 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Stability and Control Tests of a 3 4 scale Model of the XP 69 Airplane in the NACA Full scale Tunnel written by Harold H. Sweberg and published by . This book was released on 1943 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests have been made in the NACA full-scale tunnel to determine the longitudinal- and lateral-stability and control characteristics of a 3/4-scale model of the XP-69 airplane. The XP-69 airplane is a single-engine, low-wing monoplane with dual-rotating propellers. Engine cooling is obtained by means of a rear-underslung ducting system. Inasmuch as stability data on airplanes equipped with dual-rotating propellers are meager, the effects of propeller operation on the stability and control characteristics of this airplane are of particular interest.

Download or read book Preliminary Stability and Control Tests in Th NACA Free flight Wind Tunnel and Correlation with Full scale Flight Tests written by Joseph A. Shortal and published by . This book was released on 1941 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt: The study of stability and control of airplanes by means of dynamic scale models in the NACA 12-foot free-flight wind tunnel is described. Preliminary tests of a 1/12-scale model of the P-36A airplane were used to develop the testing technique and to afford a comparison of tests of a model in the tunnel with flight tests of the corresponding airplane. Qualitatively, the general behavior of the model was in agreement with the behavior of the airplane, but quantitatively, the longitudinal stability of the model was greater than that of the airplane and the aileron control was somewhat weaker. This quantitative disagreement is probably a result of local separation due to the low Reynolds numbers the tests, which affects a direct comparison with full-scale tests but which should not vitiate comparisons of different models or modifications to a given model. it is believed that the free-flight tunnel affords a useful means of determining the relative stability and control characteristics of different models and that it will be particularly useful in the development of new airplane design.

Download or read book Langley Full scale Tunnel Investigation of the Factors Affecting the Directional Stability and Trim Characteristics of a Fighter type Airplane written by Harold H. Sweberg and published by . This book was released on 1945 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Tests were made in the Langley full-scale tunnel of the Grumman XF6F-4 airplane in order to investigate the factors that affect the directional stability and trim characteristics of a typical fighter-type airplane. Eight representative flight conditions were investigated in detail. The separate contributions of the wing-fuselage combination, the vertical tail, and the propeller to the directional stability of the airplane in each condition were determined. Extensive air-flow surveys of sidewash angle and dynamic-pressure ratio along a line coincident with the rudder hinge line were made for each condition investigated to aid in evaluating the slipstream effects. The data obtained from the air-flow surveys were also used to investigate methods for calculating the contribution of the vertical tail to the airplane directional stability. The results of the tests showed that, for the conditions investigated, the directional stability of the airplane was smallest for the gliding condition with flaps retracted and was greatest for the wave-off condition with flaps deflected 50°. The variation of sidewash angle at the vertical tail with angle of yaw was destabilizing for all conditions investigated. Propeller operation increased the magnitude of the destabilizing sidewash but, at small angles of yaw, also increased the dynamic pressure at the vertical tail sufficiently to make the combined effect stabilizing.

Download or read book Power on Longitudinal stability and Control Tests of the 1 8 scale Model of the Brewster F2A Airplane Equipped with Full span Slotted Flaps and a New Horizontal Tail written by John G. Lowry and published by . This book was released on 1942 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were made in the NACA 7- by 10-foot wind tunnel of the 1/8-scale model of the Brewster F2A airplane equipped with full-span slotted flaps and a new horizontal tail. The object of the tests was to determine the power-on static longitudinal stability and control characteristics of the model with a new horizontal tail. Some additional tests to determine the characteristics of the model, both in free air and near the ground, were made after certain modifications had been made to the horizontal tail.

Download or read book Analysis of Wind tunnel Stability and Control Tests in Terms of Flying Qualities of Full scale Airplanes written by Gerald G. Kayten and published by . This book was released on 1945 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Full scale Tunnel Tests of a Flying Model of the Curtiss XP 55 Airplane written by William J. Biebel and published by . This book was released on 1943 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests have been conducted in the NACA full-scale tunnel to provide data for estimating the longitudinal stability and control characteristics of the Curtiss XP-55 airplane. The XP-55 is a low-wing airplane with the engine and propeller located at the rear of the fuselage. Longitudinal and directional control are obtained by means of the "nose" elevator and by fins and rudders attached near the wing tips.

Download or read book Investigation of the Low subsonic Stability and Control Characteristics of a 1 3 scale Free flying Model of a Lifting body Reentry Configuration written by James L. Hassell and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Tests of a 0 16 Scale Model of the X 3 Airplane at High Subsonic Speeds Stability and Control Characteristics written by William T. Hamilton and published by . This book was released on 1950 with total page 129 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Determination of the Stability and Control Characteristics of Airplanes from Tests of Powered Models written by Isidore G. Recant and published by . This book was released on 1942 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: A technique of testing wind-tunnel powered models has been developed as a result of experience gained in the investigation of the static longitudinal and lateral stability and control characteristics of several powered models in the NACA 7- by 10-foot wind tunnel. As an important part of this technique, a minimum program of the tests considered necessary to specify satisfactorily the static stability and control characteristics for present-day airplanes has been tentatively established.

Download or read book Wind tunnel Tests of a 0 16 scale Model of the X 3 Airplane at High Subsonic Speeds Additional Stability and Control Characteristics and the Aerodynamic Effects of External Stores and Ram Jets written by Joseph W. Cleary and published by . This book was released on 1950 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Exploratory Tests for Airplane Stability and Control Effectiveness in a Low Density Wind Tunnel at Mach Numbers of 3 4 5 and 6 written by and published by . This book was released on 1966 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Tests of the Northrop MX 334 Glider Airplane in the NACA Full scale Tunnel written by Gerald W. Brewer and published by . This book was released on 1944 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: The primary purpose of these tests was to obtain sufficient data with which to determine the longitudinal and lateral stability and control characteristics of the airplane.

Download or read book Wind tunnel Tests of the 1 8 scale Powered Model of the Curtiss XBTC 2 Airplane written by Arthur R. Wallace and published by . This book was released on 1944 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lateral stability tests of the original 1/8-scale model of the Curtiss XBTC-2 airplane were made in the LMAL 7- by 10-foot tunnel. It was found that (1) a rudder-force reversal was evident; and (2) that a large reduction in effective dihedral was shown when flaps were lowered and take-off power applied. In an attempt to remove the rudder-force reversal, various dorsal fins and a modified vertical tail were tested. In an attempt to reduce the change in effective dihedral with flap deflection and power, the following modifications were tested: the outboard flaps skewed from their original position (effectively swept back), wing tips which could be made to turn up when the flaps were lowered, and three modifications to the wing plan form.

Download or read book Investigation of the Subsonic Stability and Control Characteristics of a 1 7 scale Model of the North American X 15 Airplane with and Without Fuselage Forebody Strakes written by James L. Hassell and published by . This book was released on 1960 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book High speed Wind tunnel Tests of a 1 16 scale Model of the D 558 Research Airplane Longitudinal Stability and Control of the D 558 1 written by John B. Wright and published by . This book was released on 1948 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Stability and Control Estimation Flight Test Results for the SR 71 Aircraft With Externally Mounted Experiments written by Timothy R. Moes and published by . This book was released on 2002 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: A maximum-likelihood output-error parameter estimation technique is used to obtain stability and control derivatives for the NASA Dryden Flight Research Center SR-71A airplane and for configurations that include experiments externally mounted to the top of the fuselage. This research is being done as part of the envelope clearance for the new experiment configurations. Flight data are obtained at speeds ranging from Mach 0.4 to Mach 3.0, with an extensive amount of test points at approximately Mach 1.0. Pilot-input pitch and yaw-roll doublets are used to obtain the data. This report defines the parameter estimation technique used, presents stability and control derivative results, and compares the derivatives for the three configurations tested. The experimental configurations studied generally show acceptable stability, control, trim, and handling qualities throughout the Mach regimes tested.