Basic Information: summary_WTdata.txt
Tunnel data fixes: correction_log.txt (Updated 2/14/03)
Wind tunnel model: f6_cfml1_s2_onera.jpg
Flow Visualization Photos: wing-top.jpg wing-bot.jpg
The following internal nacelle drag was measured using the ONERA S4B
test bench.
The reference surface area is 0.1454 square meters, the same as the
wind tunnel model. Internal
area is defined as starting at the bell-mouth connection and ends at
the trailing edge. The bell-mouth
was part of the calibration fixture, and was not included on the wind
tunnel model. (See sketch
)
| Mach | Internal drag coefficient
for a single nacelle |
|---|---|
| 0.60 | 0.00065 |
| 0.70 | 0.00062 |
| 0.72 | 0.00060 |
| 0.74 | 0.00058 |
| 0.75 | 0.00058 |
| 0.76 | 0.00058 |
| 0.77 | 0.00058 |
DPW_pressure_WB_270:
Alpha = -0.304 CL = 0.4012 Wing/Body
DPW_pressure_WB_273:
Alpha = 0.490 CL = 0.4984 Wing/Body
DPW_pressure_WB_275:
Alpha = 1.230 CL = 0.5979 Wing/Body
DPW_pressure_WBPN_184:
Alpha = 0.190 CL = 0.4008 Wing/Body/Nacelle/Pylon
DPW_pressure_WBPN_183:
Alpha = 1.003 CL = 0.4981 Wing/Body/Nacelle/Pylon
DPW_pressure_WBPN_182:
Alpha = 1.738 CL = 0.5985 Wing/Body/Nacelle/Pylon
Location of Pressure Taps on Nacelle/Pylon
TAP X
Y Z
61 37.00 206.31
12.62
62 56.00 206.66
13.95
63 77.00 207.03
15.42
64 97.00 200.42
9.50
65 97.00 214.22
9.50
66 116.00 200.75
7.50
67 116.00 214.55
7.50
68 170.00 202.32
2.00
69 170.00 214.80
2.00
Nacelle Centerline:
Point 1: x: -8.73756 y: -205.39937
z: -28.54676
Point 2: x: 203.95542 y: -209.07073
z: -35.98394
All wind tunnel data files are in TECPLOT format.
For those not familiar with this format, the first line (TITLE) describes
the file contents.
The second line (VARIABLES) contains variable names for each column
of data. Data sets are separated by
a line containing the word "ZONE"
NASA Official Responsible for Content
Dr. Neal T. Frink
Last Updated
June 5, 2003
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