UAV-ARDA mk 9
Advanced Reduced Drag Aircraft
By Jean-Louis Naudin
created on March
3, 2002 - JLN Labs - Last
update March 29, 2002
On March 24, 2002 the UAV-ARDA mk9 has done successfully its first test flight.
| " The
flying wing airplane is the most evocative shape in
aviation : a pure wing, unencumbered by tail surfaces or
a fuselage, producing lift over every square meter of its
surface. ". Richard P. Hallion (PhD), the US
Air Force historian. " L'aile volante repr�sente la configuration a�ronautique la plus aboutie : une aile dont la puret� n'est pas alt�r�e par des empennages ou un fuselage, et dont chaque m�tre carr� de sa surface g�n�re de la portance ". Richard P. Hallion (PhD), directeur du service historique de l'US Air Force. |
This was a great moment, the 4 m wingspan flying wing is very impressive in the sky and its flight is really magic for the eyes of the observers...
The UAV-ARDA mk9 is a big model ( 4 m wingspan and 8 kg weight ) it is fully propelled by Electric Power.
See the VIDEO of the First flight of the UAV-ARDA mk9
Click on the picture to see the video ( 955 kb )
This
only the beginning of the tests, stay tuned...
The ARDA
Mk 9 "XB-35",
Tests
flights in progress on April, 2002
See also :
The
Northrop Shock Wave Reduction experiment
ARDA mk8
"N9-M"
- Flights Tests successful on August 25th, 2001
Additional notes :
For
those are interested to know more about the air drag reduction
researches conducted by Northrop, I suggest to read :
- AIAA 6th Aerospace Sciences Meeting " Electroaerodynamics
in supersonic flow" by M.S.Cahn and G.M.Andrew from Northrop
Coporation - N�68-24 January
22-24, 1968
- AIAA 3rd Fluid and Plasma Dynamics conference" Recent
experiments in supersonic regime with electrostatic charges"
by M.S.Cahn and G.M.Andrew
from Northrop Coporation - N�70-759 June 29-July, 1970
You will find also some interesting informations about some
projects on Hypersonic experiments at Mach numbers from 8 to 25
don by the RPI (
Reensselaer Polytechnic Institute ) at : http://lightcraft.meche.rpi.edu/Facilities/hypersonic_shock_tunnel.html
- AIAA 98-0991 "Pressure Investigation of the
Hypersonic "Directed-Energy Air Spike" Inlet at Mach
Number 10 With Arc Power Up to 70 kW", Toro, P.G.P,
Myrabo, L.N., Nagamatsu, H.T., January, 1998.
Email : [email protected]
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