Download or read book Aerodynamic Investigation of a Four blade Propeller Operating Through an Angle of attack Range from 0 degree to 180 degrees written by H. Clyde McLemore and published by . This book was released on 1954 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Investigation of a Four blade Propeller Operating Through an Angle of attack Range from 0 to 180 Degrees written by H. Clyde McLemore and published by . This book was released on 1954 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the aerodynamic characteristics of a four-blade rigid model propeller has been conducted in the Langley full-scale tunnel for angles of attack from 0 to 180 degrees, blade angles from 0 to 67.5 degrees, and a range of advance ratio from 0 to 6.2. The investigation included a preliminary exploration of vertical descent and a comparison with theory of the rate of change of the normal-force coefficient with angle of attack and of the aerodynamic characteristics of the propeller at zero angle of attack.

Download or read book Aerodynamic Investigation of a Four blade Propeller Operating Through an Angle of attack Range from 0 degree to 180 degrees written by H. Clyde McLemore and published by . This book was released on 1954 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Investigation of a Four blade Propeller Operating Through an Angle of attack Range from 0 u00BA to 180 u00BA written by H. Clyde McLemore and published by . This book was released on 1954 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Wind tunnel Investigation of Three Propellers Through an Angle of attack Range from 0 Degree to 85 Degrees written by Paul F. Yaggy and published by . This book was released on 1960 with total page 86 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 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 Aerodynamic Loads on an Isolated Shrouded propeller Configuration of Angles of Attack from 10 Degrees to 110 Degrees written by Kalman J. Grunwald and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 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 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamics of the Propeller written by Fritz Weinig and published by . This book was released on 1948 with total page 546 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of Flutter of a Propeller with Clark Y Section Operating at Zero Forward Velocity at Positive and Negative Blade angle Settings written by John E. Baker and published by . This book was released on 1949 with total page 686 pages. Available in PDF, EPUB and Kindle. Book excerpt: The highest flutter speeds were found in the vicinity of the angle of zero aerodynamic moment and the flutter speed increased considerably in this region with decreasing pressure. Over the rest of the pitch range, the flutter speeds were much lower and varied little with pressure.

Download or read book Aerodynamic Characteristics of a Small Scale Shrouded Propeller at Angles of Attack from 0 Deg to 90 Deg written by and published by . This book was released on 1955 with total page 14 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 deg. 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 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 Aerodynamic Loads on an Isolated Shrouded propeller Configuration for Angles of Attack from 10 Degrees to 110 Degrees written by KALMAN J. GRUNWALD and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the division of loads between the propeller and the shroud of a shroudedpropeller configuration was conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. This investigation covered an angle-of-attack range from -10 to 110 degrees and a range of advance ratios (0 to 0.595) typical of the transition speed range of a tilt-duct VTOL aircraft. For the configurations with fixed blade angle (24 degrees at the three-quarter radius), the normal force and pitching moment developed by the propeller and spinner were only a relatively small part of the over-all normal force and pitching moment of either a stalled or an unstalled shroud. The ratio of the thrust of the propeller and spinner to total thrust was found to vary from about 0.4 in hovering to about 0.7 at the highest advance ratio of the tests, 0.595, with the shroud at zero angle of attack. (Author).

Download or read book The Theory of Propellers written by Theodore Theodorsen and published by . This book was released on 1944 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: As the conditions of the ultimate wake are of concern both theoretically and practically, the magnitude of the slipstream contraction has been calculated. It will be noted that the contraction in a representative case is of the order of only 1 percent of the propeller diameter. In consequence, all calculations need involve only first-order effects. Curves and tables are given for the contraction coefficient of two-blade and four-blade propellers for various values of the advance ratio; the contraction coefficient is defined as the contraction in the diameter of the wake helix in terms of the wake diameter at infinity. The contour lines of the wake helix are also shown at four values of the advance ratio in comparison with the contour lines for an infinite number of blades.

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.