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SUMMARY OF FEATURES
1. Methods of data input and model definition
a) Aerodynamic components include fuselage, wings, horizontal tail, elevator
and a user defined quantity of vertical fins.
b) Specify non-symmetric fuselage plan-view and side-view shapes using only
20 X-Y points arrayed in text (TXT) file format. AeroWindTunnel does not
require DXF and IGES format geometry files for operation because
AeroWindTunnel is not a CAD program.
Instead, AeroWindTunnel is a computer-based, conceptual-design wind tunnel
program that uses slider-bar entry and imported fuselage shapes to quickly
estimate stability of airplanes and gliders.
c) Results from 0.0 Mach to Mach 4 and angles of attack from -45 to +45 degrees
d) Manual entry of airplane flight coefficients from wind tunnel and CFD supplied data
with complete display of values.
e) Slider-bar entry of airplane dimensions using the built-in ability to
determine flight coefficients and flight derivatives with complete display of
values.
f) Define atmospheric properties (pressure, density, viscosity etc)
from Sea Level to 200,000 feet.
g) Velocity defined in meters/sec, feet/sec or Mach number.
h) For supersonic flow, wave drag includes propulsion inlet-area effects.
i) Geometry specifications include pointed nose, round nose, elliptical
fuselage cross-section, rectangular fuselage cross-section, turbulent flow,
laminar flow, and whether or not to include fuselage boat tail drag reduction.
j) Wave drag for wings having the following cross-sections may be specified:
Single wedge (KLE=1), Symmetrical double wedge (KLE=4), Biconvex section (KLE=5.3),
Streamline foil with x/c=50% (KLE=5.5), Round-nose foil with x/c=30% (KLE=6.0),
Slender elliptical airfoil section (KLE=6.5) and finally Double wedge with maximum
thickness at arbitrary x/c location (KLE=[c/x]/[1-x/c]).
k) Surface roughness effects for the following surfaces are used to
determine the cut-off Reynolds number for each aerodynamic component: None
(perfectly smooth), Camouflage paint on aluminum, smooth paint, production sheet
metal, polished sheet metal, and finally smooth molded composites.
l) Aerodynamic effects include swept wing contribution to drag and lift.
m) Basic units of measurement may be specified as meters, centimeters, feet, or
inches.
n) AeroWindTunnel instructions distributed in HTML format using WinZip
compression.
o) Display WING or BODY drag divergence Mach number (MDD) depending on the
effects of wing and body on wave drag.
2a. Input Flight coefficients and data
a) Flight altitude above sea level, Z
b) Main wing exposed surface area, Sref
c) Main wing mean aerodynamic chord, c
d) Horizontal tail exposed surface area, St
e) Vertical fin exposed surface area, Sf
f) Number of vertical fins, N_fins
g) Wing-body cg location from wing leading edge, h, c=ref
h) Distance from airplane cg to tail aerodynamic center, l_t
i) Airplane fineness ratio, L/D
j) Wing dihedral angle (+ up)
k) Main wing setting angle, -TE up, i_w
l) Tail dihedral angle (+ up)
m) Horizontal tail setting angle, +TE up, i_t
2b. Input Flight coefficients and data
Wind Tunnel or CFD supplied data (All required if using Manual Input)
a) Wing-body aerodynamic center from wing LE, h_ac_wb, c=ref
b) Zero-lift angle of attack,
a
@ L=0
c) Wing-body downwash angle, e
(a=0)
d) Wing-body down-wash gradient, e_a
e) Wing-body moment coefficient, Cm
f) Wing-body lift-slope coefficient, CLa
g) Horizontal tail lift-slope coefficient (if required), CLa
h) Elevator effectiveness lift-slope, CLde
i) Tailless elevator moment (if required), Cmde
3. Output Flight coefficients and parameters
a) Slope of pitch-moment coefficient, Cma
b) Pitch-moment coefficient around cg at initial angle of attack, Cm
c) Slope of yaw-moment coefficient due to sideslip, Cnb
d) Slope of rolling-moment coefficient due to sideslip, Clb
e) Absolute angle of attack for trimmed flight (Cm = 0),
aa
f) Moment coefficient around cg when lift (L) = 0, Cm, 0
g) Tail volume ratio, VH
h) Neutral point location for pitch measured from wing leading edge (LE) and normalized by main wing mean
aerodynamic chord (c), hn.
i) Airplane static margin for pitch: SM = hn - h where h is the wing-body
cg location from the wing LE.
j) Airplane neutral point location for yaw measured from the nose-tip and normalized
by the vertical fin mean aerodynamic chord (cf), hn_fb.
k) Airplane static margin for yaw, SM = hn_fb - h where h is the
wing-body cg location from the nose-tip.
l) Wing lift slope for pitch, CLa_w
m) Body lift slope for pitch, CLa_body
n) Horizontal tail lift slope for pitch, CLa_tail
o) Vertical fin lift slope for yaw, CLa_fin
p) Rate of change of lift coefficient
with elevator deflection, CLd
q) Rate of change of moment coefficient with elevator deflection, Cmd
4. Output Requirements for
level flight
a) Airplane drag coefficient, CD
b) Airplane lift coefficient, CL
c) Airplane lift to drag ratio, L/D
d) Velocity required for level flight
e) Thrust required for level flight
f) Absolute angle of attack at trim (deg)
g) Elevator angle at trim, +TE down (deg)
5. File and data manipulation
a) Plot total airplane moment coefficient (Cmcg) around center of gravity verses angle of attack (a).
b) Plot wing-body moment coefficient (Cmcg_wb) around center of gravity verses angle of attack (a).
c) Save project files as .DAT files to disk.
d) Save results to disk as .DAT files.
e) Print screen images to the printer.
6. Real-time airplane plan view and side view with the following information
a) Center of gravity (Cg) location marked on plan/side view as a
green
dot.
b) Wing-body aerodynamic center (ac_wb) location marked on plan view as a
red
dot.
c) Total airplane aerodynamic center (ac_pitch) or neutral point
marked on plan view as a black dot.
d) Tail aerodynamic center (ac_tail) location marked on plan view as a
red dot.
e) Vertical-fin-body aerodynamic center (ac_yaw) location marked on side-view as
a black dot.
f) Vertical-fin aerodynamic center (ac_fin) location marked on side-view as a red dot.
7. Real-time airplane design values displayed on plan view and side view
a) Airplane center of gravity (cg).
b) Airplane pitch aerodynamic center or neutral point location (ac_pitch).
c) Wing-body aerodynamic center location (ac_wb).
d) Exposed-wing aspect ratio (AR_wing).
e) Tail aerodynamic center location (ac_tail).
f) Airplane yaw aerodynamic center or neutral point location (ac_yaw).
g) Fin aerodynamic center location (ac_fin).
h) Horizontal Tail aspect ratio (AR_tail).
i) Vertical Fin aspect ratio (AR_fin).
8. Results Plots
a) Plot nine coefficients verses angle of attack (-25 to 25 degrees).
b) Plot nine coefficients verses Mach number (0.0 to Mach 4).
c) Plot coefficients using exposed wing area, total wing area, body planform
area or maximum body frontal area as plot reference.
d) Insert experimental data into coefficient plots for comparison.
e) Recent enhancements
include the ability to display
3-D
Orthographic images of aircraft model geometry.
9. Much more ...
AEROWINDTUNNEL REVISIONS
All AeroWindTunnel purchasers can receive the following upgrades at no additional cost.
The purchaser must contact AeroRocket
to receive a FREE upgrade. All upgrade requests will be validated against
the list of AeroWindTunnel purchasers before an upgrade can be issued.
AeroWindTunnel 6.3.0.0 (5/24/08)
1) Added double-delta wing geometry to the Fuselage Geometry and
Wing-Fuselage Aerodynamic-Center screen. After the double delta wing is
specified the user has the option of inserting a double-delta wing into the
plots or inserting an equivalent double-delta wing into the analysis and plots.
The double-delta wing and its variants are used to reduce the affect of the
rearward aerodynamic-center shift that occurs in the transition between subsonic
and supersonic flight.
AeroWindTunnel 6.2.0.2 (4/06/08)
1) Vertical fins could not be located at wing-tips and there was no fin vertical
control. Now, fin-to-fin spacing and fin Y-location inputs can locate one
vertical fin at each wing-tip location. This version adds a vertical fin
Y-location input to accurately locate up to two fins in the vertical direction.
2) Wing span appeared to change for imported models with variable fuselage diameter as the wing
location was modified using the LE location from nose tip slider-bar control. This
was a geometry problem that did not alter AeroWindTunnel results.
3) Effects for some data inputs on the Fuselage Geometry screen were not seen
immediately in the 3-D wire frame plots.
4) Added the HTV-3X or BlackSwift, XCOR's Lynx and AeroRocket's AeroEagle to AeroWindTunnel's collection of project files in Glider_Examples.zip.
Already included in the AeroWindTunnel collection are project files for the X-30 NASP,
HL-20 and F-16 type jet airplane in addition to several other gliders and
examples from text books.
AeroWindTunnel 6.2.0.1 (12/17/07)
1) For the Plot Coefficients screen, Cd verses angle of attack and Cd
verses Mach number are now displayed from 0.0 to a maximum value.
2) For the Plot Coefficients screen, plot error occurred for all
coefficients verses Mach number if geometric angle of attack equaled zero-lift
angle of attack.
3) Run-time error "6" overflow occurred for manual input if most values were
made zero in the MANUAL ENTRY: WIND TUNNEL DATA section.
4) Input blocks for Horizontal tail exposed surface area and Vertical
fin exposed surface area were sometimes zeroed when manual input was
specified.
SYSTEM REQUIREMENTS
(1) Screen resolution: 1024 X 768
(2) System: Windows 98, 2000, XP, Vista, NT or Mac with emulation
(3) Processor Speed: Pentium 3 or 4
(4) Memory: 64 MB RAM
(5)
English (United States) Language
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