Air flow system bypassing a balance in a model airplane being te

Measuring and testing – Wind tunnel: aerodynamic wing and propeller study

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G01M 900

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active

046639675

ABSTRACT:
A model airplane for testing inside a wind tunnel has a fuselage and is mounted on a sting. A balance or force transducer is mounted on a forward end of the sting inside the fuselage of the model airplane and is of the strain gauge type for measuring forces acting on the model airplane. A plenum chamber for receiving air is mounted forwardly of the balance inside of the fuselage of the model airplane. At least one air feed line extends from the sting to the plenum chamber and bypasses or bridges over the balance. An external air source feeds air from the sting through the air feed line to the plenum chamber. Inside the plenum chamber, there is an externally pressurized bellow assembly having an internal cavity at a pressure equal to the static pressure existing in the fuselage of the model airplane. A fitting at the end of the bellow assembly allows air to enter the plenum chamber so that such below assembly is externally pressurized. Thus, by this arrangement, negligible force interactions from the air flowing in the sting, the air feed line, and the plenum chamber are transferred to the balance for measuring forces acting on the model airplane. To aid further in avoiding force interactions on the balance, a flexured bellow element is arranged in each air feed line so that undesirable torsion, pitch, and other forces are absorbed thereby and are prevented from being transferred to the balance.

REFERENCES:
patent: 3019643 (1962-02-01), Curry
patent: 3159027 (1964-12-01), Curry
patent: 3233452 (1966-02-01), Jones
patent: 3447369 (1969-06-01), Horanoff
patent: 3455155 (1969-07-01), Greenberg et al.
patent: 3587306 (1971-06-01), Bryan
patent: 3878713 (1975-04-01), Mole
patent: 4074567 (1978-02-01), Horanoff

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