An investigation of the aerodynamic characteristics of a model of a VTOL configuration with a lifting fan mounted in the fuselage has been conducted to determine the effects of scale and the effects of tunnel walls on the characteristics of this configuration, which had previously been investigated at full scale. The investigation was conducted in three phases: first, in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel in which significant differences between the model and full-scale results were found;second, in the 4.4— by 7.0-foot test section of the same tunnel to determine wall effects;and third, in the 4.4- by 7.0-foot test section to obtain detailed pressure distributions on the wing and fuselage to determine regions of possible scale effect.
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