STOL aircraft transient ground effects. Part 2: Experimental techniques feasibility study

Abstract

Verbatim from NASA NTRS. Not paraphrased, not summarized.

Procedures for simulating transient effects associated with STOL aircraft landings and takeoffs were examined and a basis was developed for selection of an experimental approach based on consideration of simulation requirements, experimental techniques, facilities, and costs. The results are generally applicable to STOL aircraft employing any of the following powered lift systems: externally blown flap, upper surface blown flap, augmentor wing, or internally ducted jet flap. Scaling relationships were developed to apply the simulation requirements to model test situations. Procedures for the derivation of aerodynamic forces from the measured data were discussed. Various means of expressing the aerodynamic data in forms convenient for use in performance or stability and control applications were described. Five different experimental techniques were presented that depend on two different types of experimental facilities, wind tunnels and test tracks, and involving different types of model motion, and factors pertinent to selection were summarized.

Authors

• Crowder, J. P. Douglas Aircraft Co., Inc.
• Goldhammer, M. I. Douglas Aircraft Co., Inc.
• Smyth, D. N. Douglas Aircraft Co., Inc.