Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781722915704
Category :
Languages : en
Pages : 184
Book Description
Pressure distributions on three NACA 1-series inlets have been obtained in the Langley 16-Foot Transonic Tunnel. The cowl diameter ratio (ratio of cowl highlight diameter to cowl maximum diameter) was 0.85 for all three inlets. The cowl length ratio (ratio of cowl length to cowl maximum diameter) was 1.0 for two of the inlets (NACA 1-85-100) and 0.439 for the other (NACA 1-85-43.9) inlet. One of the inlets with a cowl length ratio of 1.0 had an internal contraction ratio (ratio of highlight area to throat area) of 1.009 and the other had a contraction ratio of 1.250. The inlet with a cowl length ratio of 0.439 also had an internal contraction ratio of 1.250. All three inlets had longitudinal rows of static pressure orifices on the top and bottom external cowl surfaces. The inlet with a contraction ratio of 1.009 also had a row of static pressure orifices on the side of the cowl (external surface). The two inlets with a contraction ratio of 1.250 had a longitudinal row of static pressure orifices on the diffuser surface. Re, Richard J. and Abeyounis, William K. Langley Research Center WIND TUNNEL TESTS; PRESSURE DISTRIBUTION; STATIC PRESSURE; ENGINE INLETS; AIRCRAFT ENGINES; MACH NUMBER; ANGLE OF ATTACK; SUBSONIC FLOW; CONTRACTION; NACELLES; FOREBODIES; MASS FLOW; PRESSURE MEASUREMENT; AXISYMMETRIC BODIES...