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Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades
Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.
An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2
From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."
The use of a leading-edge area-suction flap to delay separation of air flow from the leading edge of a 35 degrees sweptback wing
No Description Available.
The use of area suction for improving the longitudinal characteristics of a thin unswept wing-fuselage model with leading- and trailing-edge flaps
No Description Available.
The use of area suction for the purpose of delaying separation of air flow at the leading edge of a 63 degree swept-back wing
No Description Available.
The use of area suction for the purpose of delaying separation of air flow at the leading edge of a 63 degree swept-back wing : effects of controlling the chordwise distribution of suction air velocities
No Description Available.
The use of area suction for the purpose of improving trailing-edge flap effectiveness on a 35 degree sweptback wing
No Description Available.
The use of area suction to increase the effectiveness of a trailing-edge flap on a triangular wing of aspect ratio 2
No Description Available.
The use of two-dimensional section data to estimate the low-speed wing lift coefficient at which section stall first appears on a swept wing
No Description Available.
Viscous flows in inlets
No Description Available.
Visual observations of the shock wave in flight
No Description Available.
The wave drag of arbitrary configurations in linearized flow as determined by areas and forces in oblique planes
No Description Available.
Wind-tunnel investigation at Mach numbers from 0.8 to 1.4 of static longitudinal and lateral-directional characteristics of an unswept-wing airplane model
No Description Available.
Wind Tunnel Development of Means to Alleviate Buffeting of the North American XP-82 Airplane at High Speeds
This report presents the results of wind-tunnel tests of a 0.22-scale model of the North American XP-82 airplane with several modifications designed to reduce the buffeting of the airplane. The effects of various modifications on the air flow over the model are shown by means of photographs of tufts. The drag, lift, and pitching-moment coefficients of the model with several of the modifications are shown. The result indicate that, by reflexing the trailing edge of the center section of the wing and modifying the radiator air-scoop gutter and the inboard lower-surface wing fillets, the start of buffeting can be delayed from a Mach number of 0.70 to 0.775, and that the diving tendency of the airplane would be eliminated up to a Mach number of 0.80.
Wind-tunnel investigation at a Mach number of 1.53 of an airplane with a triangular wing
No Description Available.
Wind-tunnel investigation at low speed of a wing having 63 degree sweepback and a drooped tip
No Description Available.
Wind-tunnel investigation at low speed of a wing swept-back 63 degrees and twisted and cambered for a uniform load at a lift coefficient of 0.5
No Description Available.
Wind-tunnel investigation at low speed of a wing swept back 63 degrees and twisted and cambered for uniform load at a lift coefficient of 0.5 and with a thickened tip section
No Description Available.
A wind-tunnel investigation at low speed of various lateral controls on a 45 degree swept-back wing
No Description Available.
Wind-tunnel investigation at Mach numbers from 0.6 to 1.4 of several ejected pilot-seat models
No Description Available.
Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps : flaps deflected in combination
No Description Available.
Investigation of the use of area suction to increase the effectiveness of trailing-edge flaps of various spans on a wing of 45 degree sweepback and aspect ratio 6
No Description Available.
An Investigation of the Wing and the Wing-Fuselage Combination of a Full-Scale Model of the Republic XP-91 Airplane in the Ames 40-by 80-Foot Wing Tunnel
Wind-tunnel tests of a full-scale model of the Republic XP-91 airplane were conducted to determine the longitudinal and lateral characteristics of the wing alone and the wing-fuselage combination, the characteristics of the aileron, and the damping in roll af the wing alone. Various high-lift devices were investigated including trailing-edge split flaps and partial- and full-span leading-edge slats and Krueger-type nose flaps. Results of this investigation showed that a very significant gain in maximum lift could be achieved through use of the proper leading-edge device, The maximum lift coefficient of the model with split flaps and the original partial-span straight slats was only 1.2; whereas a value of approximately 1.8 was obtained by drooping the slat and extending it full span, Improvement in maximum lift of approximately the same amount resulted when a full-span nose flap was substituted for the original partial-span slat.
An investigation of wing-body juncture interference effects at transonic speeds for several swept-wing and body combinations
No Description Available.
Investigation of wing characteristics at a Mach number of 1.53 I : triangular wings of aspect ratio 2
No Description Available.
Investigation of wing characteristics at a Mach number of 1.53 II : swept wings of taper ratio 0.5
Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings varying in sweep angle from 60 degrees sweepforward to 60 degrees sweepback. All wings had a cambered, double-wedge section 5-percent thick and a common taper ratio of 0.5. The experimental results are compared with the predictions of the linear theory.
Investigation of wing characteristics at a Mach number of 1.53 III : unswept wings of differing aspect ratio and taper ratio
No Description Available.
Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces
Wind tunnel tests of wingless low aspect ratio folding control missile configurations.
Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices
No Description Available.
Large-scale wind-tunnel tests of an airplane model with a 45 degree sweptback wing of aspect ratio 2.8 with area suction applied to trailing-edge flaps and with several wing leading-edge modifications
No Description Available.
Lateral control characteristics and dihedral effect of a wing-body combination with a variable incidence triangular wing and wing-tip ailerons at a Mach number of 1.52
No Description Available.
Lateral and directional dynamic-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements
No Description Available.
Lateral-directional aerodynamic characteristics of several coplanar triple-body missile configurations at Mach numbers from 0.6 to 1.4
No Description Available.
The lateral control characteristics of constant-percent-chord trailing-edge elevons on a pointed wing of aspect ratio 2 at Mach numbers up to 0.95
No Description Available.
Leading-edge contours for thin swept wings : an analysis of low-and high-speed data
No Description Available.
Lift and moment characteristics at subsonic Mach numbers of four 10-percent-thick airfoil sections of varying trailing-edge thickness
No Description Available.
Lift and pitching-moment interference between a pointed cylindrical body and triangular wings of various aspect ratios at Mach numbers of 1.50 and 2.02
No Description Available.
Lift, drag, and hinge moments at supersonic speeds of an all-movable triangular wing and body combination
No Description Available.
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds
Results are presented, in graphical and tabular form, from a wind tunnel investigation of the lift, drag, and pitching moment characteristics of thin, low-aspect-ratio wings in combination with a body at Mach numbers from 0.25 to as high as 1.9. The following are analyzed and compared with existing theoretical results: 1. Effects of aspect ratio on 3-percent-thick triangular wings; 2. Effects of plan form on 3-percent-thick triangular, sweptback, and unswept wings of aspect ratios 2 and 3; 3. Effects of wing thickness on triangular wings of aspect ratio 2; 4. Effects of profile shape on triangular, sweptback, and unswept wings; and 5. Effects of camber and twist on triangular wings of aspect ratios 2 and 4.
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : an investigation at large Reynolds numbers of the low-speed characteristics of several wing-body combinations
No Description Available.
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : body of revolution
No Description Available.
Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : comparison of three wings of aspect ratio 2 of rectangular, swept-back and triangular plan form, including effects of thickness distribution
No Description Available.
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, biconvex section
No Description Available.
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
No Description Available.
The low-speed lift and drag characteristics of a series of airplane models having triangular or modified triangular wings
No Description Available.
Low-Speed Wind-Tunnel Investigation of the Drag of a Lockheed F-94C Airplane (A.F. No. 50-956)
The aerodynamic characteristics in pitch of an F-94C airplane, with the primary attention given to its drag characteristics, have been evaluated at low speed in the Ames 40- by 80-foot wind tunnel. The increments of drag due to various surface irregularities, ports, and component parts of the production airplane were determined. Wing-wake surveys were taken to determine the section drag coefficients at midsemispan for the smooth and the production wing. Base-pressure and internal drags of the air-induction system were measured at low inlet-velocity ratios. The characteristics of the airplane in the landing configuration are also included.
Measurements in flight of the longitudinal characteristics of two jet aircraft, one with a diving tendency and the other with a climbing tendency at high Mach numbers
No Description Available.
Measurements of boundary-layer transition at low speed on two bodies of revolution in a low-turbulence wind tunnel
No Description Available.
Measurements of downwash and sidewash behind cruciform triangular wings at Mach number 1.4
No Description Available.
Measurements of the damping in roll of large-scale swept-forward and swept-back wings
No Description Available.