The following series of tests were conducted in the AeroRocket subsonic wind tunnel to determine Pitch (nose-up/nose-down) and Yaw (side-to-side) center of pressure location for the X-30 NASP. The AeroRocket low friction caliper was used successfully to determine two-axis center of pressure location. Figure-10 illustrates measurement of the Pitch center of pressure and Figure-11 illustrates measurement of the Yaw center of pressure. The following table of X-30 NASP center of pressure location was generated using the AeroRocket subsonic wind tunnel with results tabulated verses AeroWindTunnel results for the X-30 NASP.
 

AeroWindTunnel is also great for determining flight characteristics of gliders and simple airplanes using the Manual Input mode of operation. This glider was analyzed and successfully flown after being analyzed using AeroWindTunnel.

AeroCFD® 2D-WING bonus feature addition to AeroWindTunnel Back

AeroWindTunnel™ includes a new program called 2D-WING™ for the aerodynamic analysis of two-dimensional (2-D) and finite aspect ratio (AR) airfoil sections. 2D-WING uses vortex lift panels to compute CD, CL and Cm,c/4 for airfoil sections using NACA four digit airfoils, streamlined, flat plate, double wedge (D'Wedge) and imported custom shapes for a wide range of 2-D and finite AR airfoils. Several NACA five-digit airfoils from Appendix III in the book Theory of Wing Sections allow the user to rapidly specify complex imported shapes. Other useful input variables include wing Reynolds number (Re) and angle of attack in degrees. Also, 2D-WING produces filled color contour plots and line color contour plots for pressure coefficient (Cp) and U/U0 where the number of contour levels can be specified from 3 to 256 levels. In addition, the following standard plots are produced, Cp verses chord length and U/U0 verses chord length for the upper and lower airfoil surfaces. Also, CL verses AOA, CD verses AOA, CD verses CL, CL/CD verses AOA and Cm verses AOA are quickly plotted. Finally, the total number of 2-D vortex panels that define the upper and lower surfaces of an airfoil can be specified as 100, 200 or 300.

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 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
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 (New)
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, 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, CL_de
i) Tailless elevator moment (if required), Cm_de

3. Output Flight coefficients and parameters
a) Slope of pitch-moment coefficient, C_ma
b) Pitch-moment coefficient around cg at initial angle of attack, C_m
c) Slope of yaw-moment coefficient due to sideslip, C_nb
d) Slope of rolling-moment coefficient due to sideslip, C_lb
e) Absolute angle of attack for trimmed flight (Cm = 0), a_a
f) Moment coefficient around cg when lift (L) = 0, C_{m, 0}
g) Tail volume ratio, V_H
h) Neutral point location for pitch measured from wing leading edge (LE) and normalized by main wing mean aerodynamic chord (c), h_n.
i) Airplane static margin for pitch: SM = h_n - 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 (c_f), h_{n_fb}.
k) Airplane static margin for yaw, SM = h_{n_fb} - h where h is the wing-body cg location from the nose-tip.
l) Wing lift slope for pitch, CL_{a_w}
m) Body lift slope for pitch, CL_{a_body}
n) Horizontal tail lift slope for pitch, CL_{a_tail}
o) Vertical fin lift slope for yaw, CL_{a_fin}
p) Rate of change of lift coefficient with elevator deflection, CL_d
q) Rate of change of moment coefficient with elevator deflection, Cm_d

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 (New)
e) Thrust required for climbing and level flight (New)
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 (New)

5. File and data manipulation
a) Plot total airplane moment coefficient (Cm_cg) around center of gravity verses angle of attack (a).
b) Plot wing-body moment coefficient (Cm_{cg_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
AeroWindTunnel 6.4.0.4 (3/07/10)
1) For AeroWindTunnel 6.4.0.4 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 Files (x86)/AeroWindTunnel.

AeroWindTunnel 6.4.0.3 (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 VR.

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 6.4.0.1/6.4.0.2 (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 collection of 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 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.

AeroWindTunnel NOTES
NOTE-1:  For versions prior to 6.4.0.4 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 correct.

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