Download or read book Effect of Propeller Location and Flap Deflection on the Aerodynamic Characteristics of a Wing propeller Combination for Angles of Attack from 0 to 80 Degrees written by William A. Newsom and published by . This book was released on 1957 with total page 714 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made to determine the effect of propeller location and flap deflection on the lift, drag, and pitching-moment characteristics of a wing-propeller combination over an angle-of-attack range from 0 to 80 degrees. The model had four propellers, the slipstream from which covered practically the entire span of the wing. The wing had a 30-percent-chord slotted flap and an 8.5-percent-chord slat. Data were obtained for flap deflections of 0, 20, 40, and 60 degrees with the slat off and on. For one propeller position the power input to the model was measured and tuft studies of the flow on the wing were made. The data are analyzed to assess the feasibility, from consideration of stability and control, of a tilting-wing vertical-take-off-and-landing airplane with the wing pivoted behind the primary wing structure to provide a desirable structural configuration. The main object of the investigation was to determine whether advantage might be taken of the forward shift of the center of gravity of the airplane, as the wing is tilted from an angle of attack of 90 to 0 degrees, to minimize the change in trim pitching moment throughout the transition speed range for such a configuration. The results indicate that with proper propeller position and programming of flap deflection, it is possible to design a configuration of this type in which essentially no change in trim is required throughout the transition from hovering to normal unstalled forward flight.
Download or read book Aeronautical Engineering Review written by and published by . This book was released on 1957 with total page 1908 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Aerodynamic Characteristics of a Model Wing propeller Combination and of the Wing and Propeller Separately at Angles of Attack Up to 90 written by John W. Draper and published by . This book was released on 1954 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of an investigation conducted in the Langley 300 mph 7- 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1948 with total page 630 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Aerodynamic Characteristics of a Model Wing propeller Combination and of the Wing and Propeller Separately at Angles of Attack Up to 90 Degrees written by and published by . This book was released on 1954 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effect of Trailing edge Extension Flaps on Propeller Characteristics written by John L. Crigler and published by . This book was released on 1945 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An analysis was made to determine the effect on propeller performance of extension flaps added to the trailing edge of a propeller blade. A method of calculating the changes in the ideal angle of attack, the angle of zero lift, and the design lift coefficient of a propeller blade section having a trailing-edge extension flap was utilized to calculate the performance of a six-blade dual-rotating propeller with extension flaps varying up to 40 percent chord. The method was used to determine the angle that the flap extension must make with the chord in order to obtain a particular load distribution. Although the analysis in this report was made for a wind-tunnel propeller designed to operate at low advance-diameter ration, the method is directly applicable to any propeller section under any operating condition.
Download or read book Wind tunnel Investigation of Effects of a Pusher Propeller on Lift Profile Drag Pressure Distribution and Boundary layer Transition of a Flapped Wing written by Carl A. Sandahl and published by . This book was released on 1945 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Some of the effects of pusher-propeller operation on the aerodynamic characteristics of a flapped wing were measured in the Langley propeller-research tunnel. The effects of propeller operation on the lift and profile drag of the wing, on pressure distribution, and on the position of boundary-layer transition were obtained. The results indicated that, at fixed angles of attack and with flaps deflected, the wing lift increased appreciably with increasing thrust coefficient. With flaps retracted, no appreciable increase in lift with increases in thrust coefficient was measured. Chordwise pressure distributions at several spanwise stations indicated that the effect of propeller operation was greatest in the region immediately ahead of the propeller and that the effect extended out-board from the propeller axis for about 2.5 propeller radii. Measurements of boundary-layer velocity on the forward part of the upper surface of the wing showed no appreciable shift of transition in the range of thrust coefficients investigated.
Download or read book Wind tunnel Study of the Effects of Propeller Operation and Flap Deflection on the Pitching Moments and Elevator Hinge Moments of a Single engine Pursuit type Airplane written by H. R. Pass and published by . This book was released on 1942 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: A mock-up of a pursuit airplane has been tested in the NACA full-scale wind tunnel and the effects of propeller operation and flap deflection on the aerodynamic characteristics of the wing-fuselage combination and of the horizontal tail have been determined. The results of these tests have been compared with the results of previous tests and with available theories and, in general, satisfactory comparisons have been obtained. These results have also been used to develop empirical procedures for determining the effect of propeller operation on the lift and on the pitching moments of a flapped wing and to evaluate empirical factors for calculating the downwash angles at the tail with the propeller operating. The general applicability of these empiricisms has not been determined. The elevator hinge-moment characteristics have also been determined from tests on the mock-up and indicate the inadequacy of available data on the hinge-moment parameters. The procedure for calculating stick forces from wind-tunnel data has been outlined.
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1963 with total page 642 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a Small scale Shrouded Propeller at Angles of Attack from 0 to 90 Degrees written by Lysle P. Parlett and published by . This book was released on 1955 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made to determine the effects of airspeed and angle of attack on the lift, drag, and pitching moment of a shrouded-propeller model, having a shroud length of about two-thirds the propeller diameter, over an angle-of-attack range from 0 deg to 90 degrees. Tests were made of the complete model with the propeller operating and also of the shroud and motor combination with the propeller removed. The effect of inlet-lip cross-sectional radius on the static-thrust characteristics was also studied. These tests were made in connection with the design of a vertical-take-off free-flight model and the results are presented herein without analysis as it is felt that they may be useful in the design or analysis of other aircraft.
Download or read book Analysis of Wind tunnel Tests to a Mach Number of 0 90 of a Four engine Propeller driving Airplane Configuration Having a Wing with 40 Degrees Sweepback and an Aspect Ratio of 10 written by George G. Edwards and published by . This book was released on 1956 with total page 658 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted at speeds up to a Mach number of 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration having a 40 degrees swept wing with an aspect ratio of 10. Results of wind-tunnel tests of a model representing such an airplane configuration (see NACA TN 3789) show that these effects are of most concern in the low-speed high-thrust flight regime. In the present report the low-speed data are analyzed to determine the source of the various effects and to indicate how the adverse effects can be reduced, and the high-speed data are discussed primarily from the standpoint of Mach number effects. The analysis of the low-speed data indicates that the large variations of longitudinal stabil.itywith angle of attack resulted primarily from passage of the tail into and out of the slipstream. The slipstream also created large lift increments on the wing, particularly with flaps deflected, which resulted in increases in stability (with increasing thrust coefficient) from the outboard propeller and decreases in stability from the inboard propeller. It was concluded that the longitudinal stabiltty characteristics of the model couldbe improved by moving the nacelles outward, increasing the tail height, and reducing the tail span.
Download or read book The Effect on Stability and Control of a Pusher Propeller Behind Conventional Tail Surfaces as Determined by Tests of a Powered Model in the Free flight Tunnel written by John P. Campbell and published by . This book was released on 1943 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The effects on stability and control of a pusher propeller behind conventional horizontal and vertical tail surfaces have been determined in the NACA free-flight tunnel by tests of a 1/10-scale model of an NACA submerged-engine pusher airplane design. The investigation consisted of flight and balance tests at windmilling and high-power conditions with a partial-span Zap extensible flap extended and retracted. The effects of changes in vertical-tail area, horizontal-tail incidence, and center-of-gravity location were also determined.
Download or read book Investigation of a Three blade Propeller in Combination with Two Different Spinners and an NACA D type Cowl at Mach Numbers Up to 0 80 written by George C. Kenyon and published by . This book was released on 1954 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effect of Blade section Thickness Ratios on the Aerodynamic Characteristics of Related Full scale Propellers at Mach Numbers Up to 0 65 written by A. J. Eggers and published by . This book was released on 1953 with total page 286 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Propeller axis Angle of Attack on Thrust Distribution Over the Propeller Disk in Relation to Wake survey Measurement of Thrust written by Robert E. Pendley and published by . This book was released on 1945 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were made to investigate the variation of thrust distribution over the propeller disk with angle of pitch of the propeller thrust axis and to determine the disposition and the minimum number of rakes necessary to measure the propeller thrust. The tests were made at a low Mach number for a low and a high blade angle with the propeller operating at three small angles of pitch, and some of the tests were repeated at a higher Mach number. The data obtained show that, for small angles of pitch, large changes occur in the energy distribution in the wake which prohibit the use of a single survey rake for thrust measurement in flight tests and limit the use of a single rake in wind-tunnel tests. Under certain conditions, the energy distribution in the wake took on a symmetrical form and two diametrically opposed survey rakes were shown to be satisfactory for obtaining propeller thrust.
Download or read book The Effect of Simulated Icing on Propeller Performance written by Blake W. Corson and published by . This book was released on 1946 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests of a 10-foot-diameter three-blade Curtiss 89301-15 propeller with Clark Y blade sections have been conducted in the Langley 16-foot high-speed tunnel in order to determine the effect of simulated iceon the aerodynamic characteristics of the propeller. The irregular coat of cement and fabric was used on the blades to simulate in outline and thickness a formation of glaze ice that might be formed in flight. The propellers were tested on a new 2000-horsepower dynamometer, a brief description of which is included. All tests were made at a rotational speed of 1800 rpm for blade angles of 20, 25, 35, and 40 degrees at the 42-inch radius and at airspeeds varying from 120 to 420 miles per hour. The results are representative of full-scale constant-speed propeller operation.
Download or read book The Effects of Compressibility on the Upwash at the Propeller Planes of a Four engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback and an Aspect Ratio of 10 written by Armando E. Lopez and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results indicate that for Mach numbers up to 0.60 the upwash angles can be predicted accurately by the available theoretical methods. At Mach numbers above 0.60 the experimental values were less than those predicted by theory and this difference increased with increasing Mach number.
