Add to ORKGThe results of preliminary acoustic tests of the engine over the wing concept are summarized. The tests were conducted with a small wing section model (32 cm chord) having two flaps set at the landing position, which is 30 and 60 deg respectively. The engine exhaust was simulated by an air jet from a convergent nozzle having a nominal diameter of 5.1 centimeters. Factors investigated for their effect on noise include nozzle location, wing shielding, flap leakage, nozzle shape, exhaust deflectors, and internally generated exhaust noise
Noise measurements were obtained on models of jet-augmented lift systems which are currently being c...
Future STOL aircraft may utilize engine-over-the-wing installations in which the exhaust nozzles are...
Noise data were taken for variations to a large scale model of an externally blown flap lift augment...
Preliminary acoustic tests of the engine-over-the-wing concept as a method for reducing the aerodyna...
The noise caused by the interaction of the jet exhaust and a wing was measured under static conditio...
Noise tests were conducted with a nozzle exhausting over a small scale model of an externally blown ...
Small-model experiments were conducted of the engine-over-the-wing concept using a D-shaped nozzle i...
On the basis of static aero/acoustic data obtained at model scale, the effect of exhaust nozzle size...
Small scale model acoustic experiments were conducted to measure the noise produced in the flyover a...
A highly suppressed TF-34 engine was used to investigate engine and flap interaction noise associate...
A method is presented for estimating the noise generated by deflection of the engine exhaust for und...
Noise data were obtained with a large externally blown flap model. A fan-jet engine exhaust was simu...
June 1972Also issued as an M.S. thesis, Massachusetts Institute of Technology, Dept. of Aeronautics ...
Screening tests of upper surface blowing on externally blown flaps configurations were conducted. No...
Jet noise shielding benefits for CTOL engine-over-the-wing installations were obtained with various ...
Noise measurements were obtained on models of jet-augmented lift systems which are currently being c...
Future STOL aircraft may utilize engine-over-the-wing installations in which the exhaust nozzles are...
Noise data were taken for variations to a large scale model of an externally blown flap lift augment...
Preliminary acoustic tests of the engine-over-the-wing concept as a method for reducing the aerodyna...
The noise caused by the interaction of the jet exhaust and a wing was measured under static conditio...
Noise tests were conducted with a nozzle exhausting over a small scale model of an externally blown ...
Small-model experiments were conducted of the engine-over-the-wing concept using a D-shaped nozzle i...
On the basis of static aero/acoustic data obtained at model scale, the effect of exhaust nozzle size...
Small scale model acoustic experiments were conducted to measure the noise produced in the flyover a...
A highly suppressed TF-34 engine was used to investigate engine and flap interaction noise associate...
A method is presented for estimating the noise generated by deflection of the engine exhaust for und...
Noise data were obtained with a large externally blown flap model. A fan-jet engine exhaust was simu...
June 1972Also issued as an M.S. thesis, Massachusetts Institute of Technology, Dept. of Aeronautics ...
Screening tests of upper surface blowing on externally blown flaps configurations were conducted. No...
Jet noise shielding benefits for CTOL engine-over-the-wing installations were obtained with various ...
Noise measurements were obtained on models of jet-augmented lift systems which are currently being c...
Future STOL aircraft may utilize engine-over-the-wing installations in which the exhaust nozzles are...
Noise data were taken for variations to a large scale model of an externally blown flap lift augment...