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Extra info for X-15 Advanced Research Airplane [NA-55-221] -

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1 ... ~. ::;::::: :::::::::::::::::: ::: :::::::::: ",cm... :::::::: . m ........................ FIT :: ::::: :::::::::::: ::: :::: :::::::::::::::::: :::: WIND TUNNEL TESTING HYPERSONIC SUPERSONIC LOW SPEED SPIN MANUFACTURING 5 0 0 1 0\0 FUEL SYSTEM TEST STAND :::;:::::::::::::::::::::1:::::::::::::::::::::::::::::::::::::::::::::::::::::: ENGINEERING RELEASE GFAE ENGINE tlJAA I:::::;::::::)h::::::::::::::::j ENGINE FUEL TEST 1 0 0 1 0 1 0 1 0 MFG. TESTING :~:~:~:~:~:~:~:~:~;~:~:~:~:~:::~:~:J~:~;::~:::::::;;::::::~:::~:::~::::::::}:::::::::::::::::::;::::::::~::::::::::f::::;:::::::;:::::::::::: FLIGHT TEST :::::k::::::~:~:~:~:~:::~n:::::::::::::::::;:::::::::::::::::::::::~:~J:I STATIC TEST ;::::::::tm}~l}}}~:~:~:~:~:~:~:~:~:~:~:~:~:::~:~:~: AIRP LANE DOLLY 100100\1 ENGINE DOLLY 1 0 0 1\0 MISC.

33G).. . . . . .. 10,443 LB 46 . I... I NA-55-221 . DESIGN MISSION . . - 250 0 0 0 two place version DESIGN PROFILE PULL UP 200 1 POWERED CLIMB TO BURNOUT, 150 § I CL=O - HIGH TEMPERATURE PROFILE PULL UP CLIMB TO 75, 000 FT -2 G PUSHOVER POWEROFF CLIMB TO POWEROFF MAX. ALTITUDE, CL MAX. 75 ~ DESCENT TO la, 000 FT OPT. GLIDE DESCENT TO la, 000 FT. OPT. GLIDE - --- 100 --- LEVELFLIGHT 50 « 0 100 0 200 300 400 TIME 7000 ~ 6000 ~~ 5000 ~ 4000 Q 3000 2000 ~ P4 U) " - 1000 o ,/ o I I I '" , - , 500 FROM I 600 - LAUNCH 800 900 T !

9, 631 LB. . 18,053 LB. . 16,410 LB. . 27,684LB. POWER PLANT REACTION MOTORS INC. THRUST, 40,000FT. . . . . . . . . . . . . . . .. XLR-30RM2 57,000 LBS. 44 . NA-55-221 GENERAL ARRANGEMENT . . two place version The proposed X-15 research airplane is well adapted for conversion to a two-place research vehicle. Flight test instrumentation is removed from the airplane, and the instrumentation compartment and canopy are replaced by a rear cockpit and revised canopy.

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