Effect of hinge-line bleed on heat transfer and pressure distribution over a wedge-flap combination at Mach 10.4
Effect of boundary layer bleed on heat transfer and pressure distributions over wedge-flap surface at hypersonic speeds
Dearing, J. D.↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Performance of a wind tunnel model of an aerodynamically positioned variable flap ejector at Mach numbers from 0 to 2.0
Wind tunnel model tests of variable flap ejector nozzle with aerodynamically positioned shroud
Jones, J. R.↗
Flow phenomena and separation over highly swept delta wings with trailing-edge flaps at Mach 6.
Hypersonic flow distribution and separation types over highly swept delta wings with trailing edge flaps at Mach 6
Keyes, J. W.↗
Calculated and experimental hinge moments on a trailing-edge flap of a 75 deg swept delta wing at Mach 6
Calculated and experimental hinge moments on trailing-edge flaps of swept delta wings at hypersonic speeds and positive deflection angles
Ashby, G. C., Jr.↗
Heat-transfer and pressure distributions inside the hinge-line gap of a wedge-flap combination at Mach number 10.4
Heat transfer and pressure distributions inside hinge line gap of wedge-flap combination at hypersonic speeds
Dearing, J. D.↗
Wind-tunnel investigation of a large jet transport model equipped with an external-flow jet flap
Wind tunnel tests of large jet transport aircraft model with external flow jet flap
Fink, M. P.↗
Detail Design and Installation of a Direct Lift Control Flap for the Boeing 367-80 Airplane
Direct lift control flap for Boeing 367-80 aircraft
Source record↗
Jet-flap rotor preliminary application study, volume 1
Jet flap rotor evaluated for application in high speed, heavy lift helicopters - summary report
Domanovsky, P.↗
Investigation of a 0.3-Scale Jet-Transport Model Having a Jet-Augmented Boundary-Layer- Control Flap with Direct-Lift Control Capability
Trailing-edge flap system with boundary layer control and external jet augmentation for subsonic jet transport
Aoyagi, K.↗
Flight-determined aerodynamic properties of a jet-augmented, auxiliary-flap, direct-lift- control system including correlation with wind-tunnel results
Auxiliary flap system tests using Boeing 367-80 transport aircraft and wind tunnels
Cook, A. M.↗
Wind-Tunnel Investigation of a STOL Aircraft Configuration Equipped with an External-Flow Jet Flap
Wind tunnel tests of static longitudinal and lateral characteristics of short takeoff aircraft with external flow jet flap
Parlett, Lysle P.↗
Pressures and heat transfer on a 75 degree swept delta wing with trailing-edge flap at Mach 6 and angles of attack to 90 degrees
Pressure and heat transfer on swept delta wing with trailing-edge flap
Keyes, J. W.↗
Static and dynamic stability derivatives of a model of a jet transport equipped with external-flow jet-augmented flaps
Static and dynamic stability derivatives of model jet transport equipped with external flow jet augmented flaps
Damato, R.↗
Experimental investigation in an angular cascade sector of highly loaded turbine stator blading. Volume 4 - Performance of a jet- flapped blade
Performance tests of jet flapped blade in six blade annular cascade
Bettner, J. L.↗
Flight test results of a trailing edge flap designed for direct-lift control
Boundary layer control and trailing edge flaps for direct-lift control
Taylor, C. R., Jr.↗
Flow phenomena and separation over delta wings with trailing-edge flaps at Mach 6.
Hypersonic flow distribution and separation types over highly swept delta wings with trailing edge flaps at Mach 6
Keyes, J. W.↗
Flapping response of lifting rotor blades to atmospheric turbulence.
Lifting rotor blades flapping response to atmospheric turbulence, discussing time averaging and perturbation schemes
Gaonkar, G. H.↗
Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail
Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a weng, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4. A 1/10-scale steel-wing model of the missile was flown with modifications to the basic wing plan form consisting of leading-edge chord-extensions deflected 7 deg downward together with the forward 15 percent of the wing chord, and inboard trailing-edge flaps deflected 5 deg downward. In addition, the model had a static-pressure tube mounted at the tip of the vertical tail for position-error measurements and had a speed brake also mounted on the vertical tail to trim the model to positive lift coefficients and to permit determination of the trim and drag effectiveness of the brake. The data are uncorrected for the effects of wing elasticity, but experimental wing influence coefficients are presented.
Arbic, R. G.↗