Blockage Study of a 1/16-Scale B-1 Inlet Model in the 1-Ft Transonic and Supersonic Tunnels of the Propulsion Wind Tunnel Facility
Final rept. 7 Dec 1971-19 Jun 1972
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Tests were conducted in the 1-ft Aerodynamic Wind Tunnels 1T and 1S of the Propulsion Wind Tunnel Facility to obtain estimates of the performance available for the full-scale B-1 inletengine tests in the 16-ft Propulsion Wind Tunnels 16T and 16S. Data were obtained with two nacelle configurations and four wing configurations. The maximum test section blockage was 17 percent. Data were obtained at Mach numbers from 0.55 to 1.30 and from 1.71 to 2.30. The tunnel performance for each configuration was evaluated relative to the others and with regard to the capabilities of the 16-ft tunnels. The results of these tests indicate that the available tunnel performance is significantly compromised with the nacelle configuration which has been selected for the full- scale test. The maximum Mach number estimated to be available for the full-scale test in Tunnel 16T is 1.0. To obtain a full range of engine operating points, however, testing should be restricted to M or 0.90. The estimated starting and operating pressure ratio requirements for the full-scale B-1 test are within the Tunnel 16S capability. The minimum starting Mach number estimated to be available for the full-scale B-1 test in Tunnel 16S is 1.96. The minimum operating Mach numbers estimated to be available for the full-scale test are 1. 83 at full inlet airflow and 1.88 at windmill airflow.
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