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Aerodynamic Characteristics of 2, 3, & 4, Caliber Tangent Ogive Cylinders with Nose Bluffness Ratios of 0.00, 0.25, 0.50, & 0.75 at Mach Numbers from 0.6 to 4.0

Wind Tunnel 
The tests were conducted in the AEDC PWT/IT, and VKF/A continuous 
flow test facilities at the Arnold Engineering Development Center. 
The (IT) is a 12-inch-square perforated test section. The 40-inch supersonic 
test faci lity utilizes a solid wall test section. Detailed descriptions of 
the tunnels are given in Reference I and typical model installations are 
shown in Figures I and 2. 
2. Test Articles 
The test articles consisted of interchangeable nose, midsection, and 
afterbody configurations: 
20 nose configurations, 4 cylindrical midsections 
Of fineness ratio ranging from 5 to Il and a I-cal iber cylindrical after- 
body configuration as shown in Figures 3 and 4. Nose fineness varied from 
I to 4 calibers. Two-, 3— and 4 -caliber tangent ogive noses (N 14 through 
N25) were truncated and hemispherical nose caps added to provide three 
bluffness variations (RN/RB = 0.25, 0.50, 0.75).Grit other means of 
fixing transition were not used to el iminate the drag increment due to the 
trip and also incremental drag changes resulting from loss of the grit 
during tunnel operations. 
Although only a I-cal iber cylindrical afterbody is eonsidered in this 
report, various fin configurations were utilized in previous transonic 
tests (References 2, 3, and 4), which include data for body-cruciform fin 
configurations with noses NIC), N13, and N14. Scale effects utilizing a 
larger body-fin configuration in the 4T test facility are shown in Ref- 
erence 5. 
A typical assembly of model components is shown in Figure 4 . The 
cylindrical midsections and noses were fabricated from stainless steel 
(type 303) with a 32-microinch surface finish. Model configuration iden- 
tifications are shown in Table l.