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dc.creatorArcher, C. E.en_US
dc.date.accessioned2016-05-25T19:44:44Z
dc.date.available2016-05-25T19:44:44Z
dc.date.created1924-03-15en_US
dc.date.issued1924-03-15en_US
dc.identifier.urihttp://hdl.handle.net/11200/48599
dc.descriptionTo obtain full data on the following conditions: 1. Lift, drag, L/D, and moment curve about the center of gravity for angles from below zero lift to above maximum lift (with and without tail plane and with and without elevator). 2. Moment curves for angles of elevator settings, -30°, -20°, -10°, 0°, +10°, +20°, +30°. 3. Downwash of complete model. 4. Yawing moment for rudder angles of 5°, 10°, and 20° at angles of attack of 0°, 8°, and 16°. 5. Rudder moments. All tests run at 40 miles per hour. Angle of attack is referred to thrust line. All stabilizer and elevator settings are referred to the thrust line. The test was conducted at the Massachusetts Institute of Technology during May, 1922, in the new 4-foot wind tunnel.en_US
dc.formatPDFen_US
dc.publisherWashington, D.C. : Chief of Air Serviceen_US
dc.relation.ispartofseriesAir Service information circular (Aviation) ; v. 5, no. 453en_US
dc.relation.ispartofseriesMcCook Field report ; Serial no. 2236en_US
dc.subjectAeronautics--Researchen_US
dc.subjectAeronautics--Systems engineeringen_US
dc.subjectAirplanes--Design and constructionen_US
dc.subjectWind tunnel testingen_US
dc.subjectAirplanes--Models--Aerodynamicsen_US
dc.titleWind tunnel test of a CO-2A model airplane (airplane section report)en_US
dc.typeTexten_US


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