SUMMARY OF FEATURES
1. Methods of data input and model definition
a) Aerodynamic components include fuselage, wings (standard and
double-delta), 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 30 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
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
n) AeroWindTunnel instructions distributed in HTML format using WinZip
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
n) Airplane velocity, M/SEC, FT/SEC and Mach
o) Airplane mass, KG, LB
p) Geometric angle of attack, deg
q) Flight angle for unaccelerated flight, deg
r) Elevator deflection, +TE down, deg
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,
c) Wing-body downwash angle, e
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),
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 climbing and level flight
a) Airplane drag coefficient, CD
b) Airplane lift coefficient, CL
c) Airplane lift to drag ratio, L/D
d) CL required for level flight
e) Thrust required for climbing and level flight
f) Angle of attack for level unaccelerated flight (deg)
g) Elevator angle at trim, +TE down (deg)
h) Climb Rate in meters/min or feet/min for Flight angle
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
b) Wing-body aerodynamic center (ac_wb) location marked on plan view as a
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
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 30).
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
Orthographic images of aircraft model geometry.
9. Much more ...
AeroWindTunnel 184.108.40.206 (2/10/12)
1) Increased maximum Mach number from Mach 4 to Mach 30 for all coefficient
plots verses Mach number and angle of attack.
2) Improved airframe hypersonic flow (greater than Mach 5) drag (Cd) and lift (CL)
correlation with experimental aerodynamic data.
a) Improved Cd verses Mach number comparison with text book aerodynamic data for
the Fighter Airplane Project.
b) Improved Cd verses Mach number comparison with test results from the
AeroRocket supersonic wind tunnel and VisualCFD results for the
c) Improved supersonic analysis prediction for airframe lift slope, CNa
and center of pressure location, Xcp for all supersonic Projects.
3) Fixed Slider-input "ON" and Import-Fuselage "OFF" error where Airplane
velocity (V2) increases orders of magnitude larger than the saved value for V2
when opening a Project.
4) Added the ability to save a file with the STK extension for importing
Cd verses Mach number information into the Satellite Trajectory Kit
routine recently added to StarTravel.
5) Added the ability to compute exact Maximum Body Frontal Area (Smax) by
specifying a Section-Factor area correction for the elliptical and rectangular
cross-sections used by AeroWindTunnel.
6) In the RESULTS section on the Fuselage Geometry and Wing-Fuselage
Aerodynamics Center Location screen, changed the text, Drag coefficient
at aoa=0:CD_0 =, to Skin friction drag coefficient: CD_0 =, for added
7) In the RESULTS section on the same screen declared that center of
gravity location (h_cg), vertical fin aerodynamic center location (h_ac_fin),
pitch aerodynamic center location (h_ac_pitch), yaw aerodynamic center location
(h_ac_yaw), horizontal tail aerodynamic center location (h_ac_tail), Wing-body
aerodynamic center location (h_ac_wb), Wing-body aerodynamic center location (h_ac_wb)
and Fuselage pitch/yaw aerodynamic center locations (h_ac_b) are normalized
by airframe length. In addition, the tool-tip also declares that Skin friction drag
(CD_0), Base drag (CD_base) and Wave drag (CD_wave) values are referenced to the exposed
8) Due to the extent of these modifications and error fixes users who
purchased AeroWindTunnel starting with version 220.127.116.11 can receive
a free upgrade to the newest version. In order to verify the validity of each
request for a FREE version of AeroWindTunnel please provide name, the exact
email used during original purchase and date of original purchase.
AeroWindTunnel 18.104.22.168 (3/07/10)
1) For AeroWindTunnel 22.214.171.124
the online instructions are accessed by clicking File then Online
Instructions then selecting either When Using Windows XP or When
Using Windows 7 or VISTA. Previously when operating under Windows 7 and
VISTA the message, Error displaying Online Instructions was displayed
when trying to access the online instructions.
This occurred because under Windows XP,
ShowHTML.exe is located in c:/Program Files/AeroWindTunnel but for Windows 7 and Windows VISTA the routine is located in c:/Program
AeroWindTunnel 126.96.36.199 (2/07/10)
1) Previously, in the Coefficient Plots Verses Angle of Attack screen
when the Save Coefficient Data As command is selected from the
File pull-down menu the values for Thrust Required (TR) and
Velocity Required (VR) for level flight displayed in the Cd verses
angle of attack listing were smaller than actual by 10^-6. Now, the actual value
is the displayed value multiplied by 1000 as described in the heading for TR and
2) Previously, in the Plots pull-down menu when the Coefficients
vs. Mach number command is selected the listing did not display coefficients
as a function of Mach number but incorrectly showed the variation as a function
of angle of attack in degrees.
AeroWindTunnel 188.8.131.52/184.108.40.206 (4/22/09)
1) Added the ability to determine Thrust Required for Climbing Flight and
level flight. In previous versions only thrust required for level flight was
computed. In addition, made Flight angle an input variable where Climb
Rate is displayed in feet/minute or meters/minute depending on initial
units. Validated these modifications using the existing
airplane analyses in addition to a new analysis for the Me-163 rocket plane
developed during World War II by Germany. AeroWindTunnel results for drag
coefficient (CD) and climb speed compare exactly with results found in
Fluid Dynamic Drag by S.F. Hoerner on pages 14-9 and 14-10 where in TABLE-A,
CD = 0.012 and in Figure-7, Climb Rate = 11,600 feet per minute for the
revolutionary rocket plane. Please request the new Me-163 analysis if you
already own AeroWindTunnel.
2) Corrected a CGS and IPS units error. MKS and FPS
units were not affected. This units error effected supersonic flight
coefficients and thrust requirements.
AeroWindTunnel 220.127.116.11 (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 18.104.22.168 (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 22.214.171.124 (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
versions prior to 126.96.36.199 AeroWindTunnel
must be installed in the default directory (C:/Program Files/AeroWindTunnel/)
for the online instructions to be accessed from within the program.
NOTE-2: Input data for all AeroRocket programs must use a period (.)
and not a comma (,) and the computer must be set to the English (United States)
language. For example, gas constant should be
written as Rgas = 355.4 (J / kg*K = m^2 / sec^2*K)
and not Rgas = 355,4. The English (United States)
language is set in the
Control Panel by clicking Date, Time, Language and
Regional Options then Regional and Language Options
and finally by selecting English (United States).
If periods are not used in all inputs and outputs the results will not be
(1) Screen resolution: 1024 X 768
(2) System: Windows 98, 2000, XP, Vista, Windows 7, NT or Mac with emulation
(3) Processor Speed: Pentium 3 or 4
(4) Memory: 64 MB RAM
English (United States) Language
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