Technological gaps in V/STOL development
Noise, traffic control, instrument flight, and other problems related to V/STOL aircraft
Kuhn, R. E.↗
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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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Large-scale wind-tunnel investigation of an airplane model with a tilt wing of aspect ratio 8.4, and four propellers, in the presence of a ground plane
Aerodynamic characteristics of large-scale model of tilt-wing V/STOL aircraft
Deckert, W. H.↗
V/STOL Session Introductory and Review Paper
Basic characteristics of propeller, fan, and jet V/STOL aircraft
Campbell, J. P.↗
Experimental and theoretical investigation of wind tunnel geometry, emphasizing factors pertinent to V/STOL vehicle testing Progress report, 16 Mar. - 15 Sep. 1968
Progress on experimental program using jet flapped wing model in wind tunnel facilities for testing V/STOL aircraft
Joppa, R. G.↗
Use of superposition in digital computers to obtain wind tunnel interference factors for arbitrary configurations, with particular reference to V/STOL models
Computer program for calculating wall interference factors of V/STOL aircraft and conventional airplanes
Heyson, H. H.↗
Wind-tunnel data from a 0.16-scale V/STOL model with direct-lift and lift-cruise jets
Wind tunnel tests for V/STOL aircraft having direct-lift and lift-cruise jet nozzles
Winston, M. M.↗
V/STOL Inertial Navigation with Radar Update Capability
Radar data for updating inertial navigation system onboard V/STOL aircraft
Source record↗
Pressure Distribution of a Large Semispan Tilting Wing with 0.4-diameter-chord, Single- Slotted Flap, and a Single Propeller 0.22 Chord Below Wing
Aerodynamic pressure distribution on semispan tilting wing-propeller combination of V/STOL aircraft
Fink, M. P.↗
V/STOL session introductory and review paper.
V/STOL aircraft characteristics, emphasizing propeller, ducted fan and turbojet types
Campbell, J. P.↗
NASA aviation electronics research.
NASA civil aviation electronics research program, discussing feasibility of V/STOL aircraft all-weather operations
Hayes, R. J.↗
Conjugate gradient methods with an application to V/STOL flight-path optimization.
Conjugate gradient methods for optimization problems with terminal constraints, noting minimum time paths for V/STOL aircraft climb phase
Bryson, A. E., Jr.↗
Flight evaluation of radar-inertial systems.
V/STOL aircraft radar inertial navigation system, describing approach and landing phase flight test results
Madigan, R. J.↗
Analysis of a jet in a subsonic crosswind
Jet exhaust flow effects on aerodynamic characteristics of V/STOL aircraft during transition flight
Source record↗
A general jet efflux simulation model
Semiempirical solution and mathematical model for jet efflux induced flow fields of V/STOL aircraft
Heltsley, F. L.↗
Analysis of the flow field of a jet in a subsonic crosswind
Jet induced flow field effects on V/STOL aircraft in subsonic transition flight
Margason, R. J.↗
Study program for lift fan noise reduction and suppression
V/STOL aircraft lift fan noise reduction and suppression
Benzakein, M. J.↗
Effect of the city center environment on VTOL terminal operations
Optimum flight paths for V/STOL aircraft operating in short haul transportation near city centers
De Maio, D. A.↗
Experimental investigation of stability and stall flutter of a free-floating wing V/STOL model
An experimental investigation was made of the static and dynamic stability characteristics of a one-fourth scale model of a tilt-propeller free-wing V/STOL aircraft. The effects of wing pivot location, wing chord, trailing-edge angle, propeller tilt angle, and thrust were studied, and a limited evaluation was made of high-lift devices. A dynamically similar wing was used to measure frequency and damping ratio from transient response data in the linear aerodynamic regime and the results were compared to quasi-steady and unsteady aerodynamic theory. It was found that at high trim angles of attack, in the nonlinear aerodynamic regime, stall flutter oscillations occurred with typical amplitudes ranging from 15 to 20 deg. Wing control tab deflection was effective in initiating and terminating stall flutter but variations in configuration or operating conditions did not greatly influence the occurrence of characteristics of the oscillations.
Ormiston, R. A.↗