You're sure that's the 2707-200? From what I remember the 2707-200 had the double-jointed nose -- the B-2707-300 had the single-joined nose like the L-2000

KJ Lesnick
 
Some nice L-2000 mockup photos
 

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Now, in higher resolution
 

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Flateric! Many thanks for these really surprising pictures. I will try to find new unknown facts for me.
 
Here we are again, with this very popular thread.. 1963 was a pivot year for the original US SST competition. JFK announced it in June, just days after Juan Trippe revealed his exploratory order for Concord(e)s. NASA was working with a Boeing and Lockheed on refining (really, commercializing) some SCAT configuration. Almost everyone else was looking at the SST concept, even if someone denied this then and later. One of the hopeful was NAA, that had been excluded from the NASA contract on SCAT but had re-entered the fray (this a really poorly known episode) thanks to a work-sharing agreement with Boeing, by which they did the tasks contracted by NASA on two configurations (or, half the tasks contracted by NASA on all configurations, that seems nearer the truth). In parallel, they did work on their own concepts, derived or not from the B-70. Lttle is known on those activities (the documents are buried in the Boeing archives), BUT NAA used Le Bourget 1963 to go public. Unfortunately, what I've been able to find of their technical and PR activities in Paris amount to little more than model photos. I post them here to stimulate research.
First is a panoramic of five configuration they were studying in early 1963. Four were SCAT derived (you can recognize a SCAT 15-3 and a plain SCAT 15, both VG, and what seems a less-radical-version-than-NASA-one SCAT 4). The internally studied configuration is the one in the highest part of the photo.
Second is what is described as NAC-2000 concept (clearly related to the NAC-60 tendered a few months later in the FAA competition). Third is, above, another view of NAC-2000, and below, another view of the SCAT-15 derivative.
Fourth, is another configuration, could be a variation of the SCAT 15-3, but I'm not so sure.
Sorry for the low quality of the images, I'm working from poor originals...
 

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Adding to the score of concepts for SST dating from 1963, I think this will be a surprise for many. In 1962-63 Northrop was studying Laminar Flow Control using, among other things, a modified B-66 (aka X-21). The program was headed by Welko A. Gasich, one of the leading technical persons in Northrop. He presented some of the results of the LFC work to one of the last "Institute for Aeronautical Sciences" congresses (in the same 1963 they became AIAA) in early 1963. One of the possible uses cited for LFC was.. you bet, an SST. A model was displayed at the congress, and this is the sole photo I've been able to find. Note the suction slits on the wings, the canard and the vertical tail. They are exaggerated in size to make them visible at the model scale. Model number of the LFC SST is unknown, and how far Northrop went, the same. I'm trying and find the Gasich paper in the Politecnico di Milano library. I'll keep you updated.
 

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Oh! :eek: Forced laminar flow concept. I wonder it need frequent cleaning of small holes or filter
exchange. Also manufacturing is problem.
 
Hi! I made a chart of Lockheed SST design evolution. Sorry for low quality. Enjoy.
 

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Hi! Lockheed L2000 mock up pictures.
(Source : Japanese AIREVIEW magazine in January 1967)
 

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Lockheed L2000 mock up cabin and window cooling system pictures. Enjoy!
(Source : Japanese AIREVIEW magazine in January 1967)
 

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B2707 VG model mock up cockpit and cabin pictures.(not B2707-300 mock up)
 

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Hi,

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19710069968_1971069968.pdf
 

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Why did so many swing-wing SST's have a lower sweep angle on the glove than on the wing? I figure it would be more advantageous to have the same sweep as the wing (fully swept)?


KJ Lesnick
 
Hi! I get "SUPERSONIC TRANSPORT VOLUME A-V AERODYNAMIC REPORT 1964 January Lockheed California" from NTRS.(255pages). (But it removed now.) This document is a part of series of document for Lockheed CL823 Mach 3 Supersonic transport. CL823 was designed in accordance with the Federal Aviation Agency Request for Proposals dated 15 August 1963.
 

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Specification of CL823 is as follows.
1.Cruising Speed : Mach 3
2.Cruising Altitude : 70,000ft to 77,000ft
3.Design Range : 3,470n.m.
4.passengers : 125 to 192
5.Ramp Weight : 453,000lbs
6.Maximum Take off Weight : 450,000lbs
7.Maximum Landing Weight : 280,000lbs
8.Maximum Zero Fuel Weight : 240,000lbs
9.L/D @Mach 3 : 7.25
In this document, I found interesting information about high performance Curtiss Wright TJ70A4 turbojet engine which skybolt used to taught us. And I realized that at first GE4 was turbofan engine.
 

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This report also include loading condition of 125 passengers and 192 passengers.
I want to see especially Volume A-Ⅵ Propulsion Report.
FAA! Please release all reports for American SST.
I will not speak ill of FAA any more.
 

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nothing disappears without a trace...full text pdf goes here
http://handle.dtic.mil/100.2/AD377973

Thanks for discovery!
 
Thanks Flateric :)
 

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Already posted by Skybolt in this topic....

http://www.secretprojects.co.uk/forum/index.php/topic,483.msg34387.html#msg34387

;D
 
Dear Skybolt! Recently I feel I must study grammar. I usually made mistake.
I surprise that you are in Italy now. Two weeks later 9/11 2001 terrorism in N.Y, I travelled Milan,Venice,Pisa,Florence,Rome and Pompei with my wife. We fascinated by Italy very much.
Very excellent country!
 
Nice photo print on sale at eBay, but $39.00 is rather out of my planning expences nearest time
 

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Lockheed take on the SCAT-16: the CL-788. More drawings at my blog...
scat16a.gif


http://up-ship.com/blog/?p=1548
 
Oh! Shoulder mounted VG wing and T-tail. Engines location are very interesting. This configuration can avoid interaction between engine exhaust gas and horizontal tail stabilizer. Passengers visibility is excellent. Wing aspect ratio seems to be small. But VG SST was still heavy weight?
 
That was the primary problem for large VG configurations for transportation. Since you have to make room for passengers, you have to move the hinges of the VG mechanism outward, exacerbating the flexing moment of the hing box, that had to be reinforced, and so the weight went up. In turn, locating the engines added to the problem, look at where the hinges are in the Lockheed SCAT-16 NASA configuration are.
 
Dear Skybolt! I realize the hinges of this design. Many thanks again.
 
...
 

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AFRL's Total In-Flight Simulator (TIFS) proposed modification for SST tests (1986)
Note also bits of AMSA mod appearing.

source
The Total In-Flight Simulator (TIFS) design and capabilities.

PRUNER, J. R., USAF, SYSTEMS COMMAND, RESEARCH AND TECHNOLOGY DIV., FLIGHT DYNAMICS LAB., WRIGHT-PATTERSON AFB, OHIO; REYNOLDS, P. A., CORNELL AERONAUTICAL LAB., INC., BUFFALO, N.Y.
AIAA-1968-258
AMERICAN INST OF AERONAUTICS AND ASTRONAUTICS, FLIGHT TEST, SIMULATION AND SUPPORT CONFERENCE, 2ND, LOS ANGELES, CALIF., Mar 25-27, 1968.
 

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Hi flateric! Thank you very much again. This is the best B2707-300 mock up picture I ever saw.
It a really beautiful plane!
 
http://www.youtube.com/watch?v=eDGk3qCq630&feature=related
 
http://cgi.ebay.com/Boeing-SST-sales-brochure-material-literature-with-box_W0QQitemZ230326873444QQcmdZViewItemQQptZLH_DefaultDomain_0?hash=item230326873444&_trksid=p3286.c0.m14&_trkparms=72%3A1205%7C66%3A2%7C65%3A12%7C39%3A1%7C240%3A1318%7C301%3A1%7C293%3A1%7C294%3A50

Hell of a long link...

!BND3((!BWk~$(KGrHgoOKicEjlLmYvG8BJnvgDw)I!~~_1.JPG
 
I don't know this SST aircraft (artist drawing).
 

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I hope, this picture wasn't posted before in this thread (which has
become a little bit confusing over the years ... :-\ ): North American
concept with canards (from AviationWeek 6/63 ) :
 

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