AeroWindTunnel™
Collection of
Projects
|
MAIN PAGE |
PRODUCTS |
CONSULTING |
MISSION |
RESUME |
Copyright © 1999-2009 John Cipolla/AeroRocket. All rights
reserved
1)
X-30 SPACE PLANE (NASP)
Top
Screen shot from AeroWindTunnel's Fuselage Geometry screen for
the X-30 NASP
Screen shot from AeroWindTunnel's Coefficients Plots screen
for CD, CL and L/D for the
X-30
AeroWindTunnel results compared to test results from the
AeroRocket wind tunnel at U = 100 m/sec
2) HL-20 SPACE PLANE
Top
Screen shot from AeroWindTunnel's Fuselage Geometry screen for
the
HL-20
Screen shot from AeroWindTunnel's Coefficients Plots screen
for CD, CL and L/D for the HL-20
at M = 0.3 and Elevator Deflection set to 0.0 degrees compared
to NASA wind tunnel results
3) HTV-3X BLACKSWIFT SPACE PLANE
Top
Information derived from publicly available resources on the
Internet
Screen shot from AeroWindTunnel's Fuselage Geometry screen for
the
HTV-3X Blackswift.
Insert shows Cd vs. M and Cd @ M = 2.64 from the
new 1" Diameter Supersonic
Blow-Down Wind Tunnel
4) F-16 TYPE JET AIRPLANE
Top
Screen shot from AeroWindTunnel's Fuselage Geometry screen for
the
F-16 Type Jet Airplane
Screen shot from AeroWindTunnel's
Coefficients Plots screen for CD, CL and L/D for the F-16 Type
Jet Airplane.
5) XCOR'S LYNX MK.1
Top
|
Details for this analysis were derived from the March
31, 2008 issue of Aviation Week and Space Technology
magazine. The Space Hopper article on pages 24
and
25 stated the
Lynx Mk.1 is 27.9 feet long with a wing span of 24.2
feet. In addition, the article said the vehicle is
"conceptually similar in appearance to the Boeing
X-20 Dyna-Soar hypersonic vehicle canceled in 1963". From
start to finish the generation of the Lynx Mk.1
simulation took a total of one hour because only
plan-view and side-view shapes need specification. Time consuming CAD definitions and DXF file generation
are not required for
AeroWindTunnel
model generation greatly increasing ease of use and aerodynamic analysis
productivity. |
Screen shot from AeroWindTunnel's Fuselage Geometry screen for
the Lynx Mk.1
Screen shot from AeroWindTunnel's Coefficients Plots screen
for CD, CL and L/D for the Lynx Mk.1
Please note this information is a first cut approximation
based on incomplete data
6) Me-163 Rocket Plane
Top
|
 The
Me-163 rocket plane
was
developed during World War II by Germany as a last ditch effort to stop allied
bombing raids. Development of this revolutionary
rocket-powered interceptor started in 1938 under the
title Project X. AeroWindTunnel results for drag
coefficient (CD) and climb rate 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
rocket plane. In addition, Thrust Required for the climb angle computed using
climb rate and airplane velocity from Fluid Dynamic
Drag agree within 4% for the thrust of the Walter
HWK 109-509A-1 liquid fuel rocket motor which is
16,671 NT. The results screen shot below illustrates AeroWindTunnel's results for CD = 0.012, Climb Rate =
11,600 feet/min and Thrust Required = 16,008 NT. Please
request the new Me-163 analysis if you
already own AeroWindTunnel by contacting John
Cipolla. The project file and airframe geometry for the
Me-163 are not included in the Glider_Examples.zip
file at this time but will emailed upon request.
|
Me-163 rocket plane tested in the AeroRocket wind tunnel
to determine subsonic CD at 0.0 degrees AOA
Screen shot from AeroWindTunnel's Fuselage Geometry screen for
the Me-163 rocket plane
Screen shot from AeroWindTunnel's CD verses Mn plot for the
Me-163. Red dot is CD from
Fluid Dynamic Drag
AeroWindTunnel's results displaying CD, Thrust Required for
Climbing Flight, Climb Rate and Flight angle input for the
Me-163
MathCAD analysis to compute CD and Climb Angle
from Fluid Dynamic Drag data for the Me-163
7) AEROROCKET'S AEROEAGLE MODEL
AIRPLANE
Top
Screen shot from AeroWindTunnel's Fuselage Geometry screen for
the AeroEagle glider
|
