Schveiber 3 Bentkowsky and Kerr 



operated, by the Arnold Research Organization under contract with 

 NASA. The operating Reynolds number per foot versus Mach- num- 

 ber range of the tunnel is presented in Fig, 12, With a l/30 scale 

 model of the bottomed submarine, Reynolds numbers up to 6 X 10® 

 based on the model diameter could be achieved at a Mach number of 

 0.2. This corresponded to the full-scale Reynolds number in a 

 i.5 knot current. Compressibility effects at a Mach number of 0,2 

 are known to be insignificant. Because of the large size of the test 

 channel and the available equipment and instrumentation this facility 

 afforded a unique capability for the DSRV program. 



3 4 5 6 7 



REYNOLDS NUMBER PER FOOT (xlO"^ 



Fig, 12, Operating Characteristics of the Am^es i 2-Foot Pressure 

 Wing Tunnel 



Test Section and Model Support System 



The test section is circular in cross section except for flat 

 fairings. Figure 13 presents a schematic sketch of the general 

 arrangement of the test section and the DSRV model support system. 

 As illustrated, the sting-type model support consists of a fixed strut 

 mounted vertically in the wind tunnel to which is attached a movable 

 body of revolution carrying the sting and. In turn, the DSRV model. 

 The strut functions as a support and guide for the body of revolution 

 which can be pitched in the vertical plane by means of motor-driven 

 lead screws. The range of pitch angles Is 10 to 20 degrees; however. 



1152 



