The following
AeroDRAG & Flight Simulation
validation analysis uses widely available V2 rocket
physical characteristics and flight performance information
to compare range, apogee of trajectory, velocity at burnout,
velocity at impact, burnout altitude, acceleration at burn
out and acceleration at liftoff to actual V2 rocket flight
performance information.

INPUT DATA: Table1 to Table4 display the required
V2 airframe dimensions, fin dimensions and flight input
data required for flight analysis. Please refer to Figure3
for a screen shot of the drag analysis screen and a
summation of the input dimensional data and Figure4 for a
screen shot of the flight results. Finally, please refer to
Figure8 and Figure9 for screen shots of altitude verses
time, Mach number verses time and acceleration (G) verses
time plots. Please note: This analysis is an approximation
based on the best information available for the A4/V2
rocket.

Table 4: Launch Conditions & 2D Flight
Data Input 
Stage1 
Source 
Temperature at launch location [deg F] 
80.0 
N/A 
Elevation of launch location [ft] 
0.0 
N/A 
Flight path angle at insertion [deg] 
49.0 
A4/V2 Resource Site 
Time from liftoff to roll initiation [sec] 
5.0 
A4/V2 Resource Site 
Time from liftoff to Flight path angle insertion [sec] 
54.0 
A4/V2 Resource Site 
Lift to drag ratio [1] 
0.0 
N/A 
Table5, AeroDRAG Flight Results Compared to V2 Flight Data
Flight Data 
AeroDRAG 
V2 Flight Data 
% Difference 
Range (miles) 
189.5 
199 
4.8% 
Apogee of trajectory (miles) 
59.8 
56.0 
+6.8% 
Velocity at burnout (ft/sec) 
5,290.6 
5,249.3 
+0.8% 
Velocity at impact (ft/sec) 
2,927.8 
3,608.9 
18.9% 
Burnout altitude (miles) 
18.3 
17.4 
+5.2% 
Maximum Acceleration at burnout (G's) 
6.6 
7.0 (a)(b)(c) 
5.7% 
Acceleration at liftoff (G's) 
0.95 
0.90 
+5.6% 
Apogee, 90 degree liftoff
(miles) 
120.0 (d) 
114.0 
+5.3% 
a) G modified using: G = F/W  1,
That is, V2 published values have been reduce by 1G.
b) When coasting vertically in space in a gravitational field, G
= 1 when F ~ 0 and W = SS1 final weight.
c) Acceleration due to gravity of a particle in space is G =
 g0 * R^2 / r^2, where r is the distance from the center of
the earth to the particle, R is the radius of the Earth and g0
is the acceleration due to gravity at the surface of the Earth.
d) This AeroDRAG apogee result is compared to the approximate maximum
altitude achieved by the V2 rocket for vertical
flight when used as a sounding rocket. This result is achieved by performing a onedimensional
flight analysis with the flight path angle set to 90 degrees
from the horizontal. Burn time was increased to 70 seconds
corresponding to the maximum burn time of the V2 rocket
motor. 
PROPELLANT WEIGHT: The V2 rocket used 3,710 kg of Ethyl Alcohol
(75%) and 4,900 kg of Liquidoxygen for a total of 8,610 kg
or 18,982 lb of propellant consumed during the 65 second
burn of the rocket motor for this example.

THRUSTTIME PROFILE:
The V2 rocket motor developed 25,000 kg (55,100 lb) of
thrust at sea level where the atmospheric pressure is
approximately 14.7 psia. Also, when the ambient pressure is
reduced to the near vacuum of space a V2
rocket motor developed 31,800 kg (70,107 lb)
of thrust because the low pressure of high altitude flight
allows the nozzle to
expand more efficiently from the nozzle exit to low
ambient pressure. The thrust curve is constructed using
these design conditions to define the thrusttime
plot in the ThrustCurve Generation screen. The
thrusttime curve (saved
as an FVT file) is used in this analysis to
approximate the thrust profile of the V2 rocket. Please see Figure1 (below) for the input screen used to
generate the thrusttime curve for this example.

FLIGHT
RESULTS (AeroDRAG 7.0):
Comparison between AeroDRAG & Flight Simulation
results and actual V2 flight data compare well for range,
apogee, velocity at burn out, impact velocity, burn out
altitude, acceleration at liftoff and finally the maximum
altitude achieved by the V2 rocket for vertical flight.
Please refer to Table5 where these results are compared.
For example, the range predicted by the simulation for the
V2 rocket was 189.5 miles compared to 199 miles for the
published V2 range data for a difference of 4.8 percent.
These results include the effects of Cd verses Mach number, air density verses altitude,
propellant weight as a function of time and Cd verses rocket shape and
Mach number. However, wind velocity, Earth curvature and other perturbations are not included
in the 2D analysis at present. Please note, the effects of Earth
curvature may be neglected for ranges less than 500 km
(310.7 miles). Finally, please refer to Figure2, Figure3,
Figure4 and Figure5 for more information concerning the
procedure required to generate program output.

Figure1, ThrustTime Profile  Manual Input screen and FreeForm
Input screen
AeroDRAG & Flight Simulation Input Data and Results Screen Shots
Figure2, Drag Screen and Summation of
Input Data
Figure3, Flight Screen and Results
Figure4, Launch Point Specification
Screen
Figure5, Altitude and Axial
Acceleration Plot Screen

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