Northrop M2-F2
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{{infobox Aircraft
|name = M2-F2
|type = Lifting body
|national origin=United States
|manufacturer = [[Northrop Corporation|Northrop]]
|image = Image:Northrop_M2-F2.jpg
|caption =
|designer =
|first flight = [[12 July]] [[1966 in aviation|1966]]
|introduced =
|retired = [[10 May]] [[1967 in aviation|1967]]
|produced =
|number built = 1
|status = Rebuilt as M2-F3
|unit cost =
|primary user = [[NASA]]
|more users =
|developed from = [[NASA M2-F1]]
|variants with their own articles = [[Northrop M2-F3]]
}}
The '''[[Northrop Corporation|Northrop]] M2-F2''' was a heavyweight [[lifting body]] based on studies at [[NASA]]'s Ames and Langley research centers. Built by the Northrop Corporation in [[1966]]. The "M" refers to "manned" and "F" refers to "flight" version.
==Development==
The success of Dryden's [[NASA M2-F1|M2-F1]] program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers -- the M2-F2 and the [[Northrop HL-10|HL-10]], both built by the Northrop Corporation. The "M" refers to "manned" and "F" refers to "flight" version. "HL" comes from "horizontal landing" and 10 is for the tenth lifting body model to be investigated by [[Langley Research Center|Langley]]. (See also [[NASA Ames Research Center]]).
The M2-F2 made its first captive flight (attached to the [[B-52 Stratofortress|B-52]] carrier aircraft throughout the flight) on [[March 23]], [[1966]].
The first flight of the M2-F2 - which looked much like the [[NASA M2-F1|"M2-F1"]] - was on [[July 12]], 1966. [[Milton O. Thompson]] was the pilot.
By then, the same B-52 used to air launch the famed [[X-15]] rocket research aircraft was modified to also carry the lifting bodies. Thompson was dropped from the B-52's wing pylon mount at an altitude of 45,000 feet (13,700 m) on that maiden glide flight. He reached a [[gliding]] speed of about 450 miles per hour (720 km/h).
==Operational history==
[[Image:M2-F2 crash.jpg|thumb|right|The crash site of the M2-F2]]
Before powered flights were undertaken, a series of glide flights were conducted. On [[May 10]], [[1967]], the sixteenth and last glide flight ended in disaster as the vehicle slammed into the lake bed on landing. With test pilot [[Bruce Peterson]] at the controls, the M2-F2 suffered a [[Pilot-induced oscillation|pilot induced oscillation]] (PIO) as it neared the lake bed. The vehicle rolled from side to side in flight as he tried to bring it under control. Peterson recovered, but then observed a rescue helicopter that seemed to pose a collision threat. Distracted, Peterson drifted in a cross-wind to an unmarked area of the lake bed where it was very difficult to judge the height over the ground because of a lack of guidance the markers provided on the lake bed runway.
Peterson fired the landing rockets to provide additional lift, but he hit the lake bed before the [[Undercarriage|landing gear]] was fully down and locked. The M2-F2 rolled over six times, coming to rest upside down. Pulled from the vehicle by Jay King and Joseph Huxman, Peterson was rushed to the base hospital, transferred to [[March Air Force Base]] and then the [[University of California, Los Angeles|UCLA]] Hospital. He recovered but lost vision in his right [[eye]] due to a [[Staphylococcus|staphyloccocal]] infection.
Portions of M2-F2 footage including Peterson's spectacular crash landing were used for the 1973 [[television|TV]] [[Film|movie]] [[The Six Million Dollar Man]] and subsequently during the [[opening credits]] of every [[episode]] of the [[television]] series.
Four pilots flew the M2-F2 on its 16 glide flights. They were [[Milton O. Thompson]] (5 flights), [[Bruce Peterson]] (3 flights), [[Don Sorlie]] (3 flights) and [[Jerry Gentry]] (5 flights).
[[NASA]] [[Aviator|pilot]]s and [[research]]ers realized the M2-F2 had lateral control problems, even though it had a stability augmentation control system. When the M2-F2 was rebuilt at Dryden and redesignated the [[Northrop M2-F3|M2-F3]], it was modified with an additional third vertical [[fin]] -- centered between the tip fins to improve control characteristics.
The M2-F2/F3 was the first of the heavy-weight, entry-configuration lifting bodies. Its successful development as a research test vehicle answered many of the generic questions about these vehicles.
==M2-F2 flights==
*'''NASA M2-F2''' - NASA 803, 16 unpowered flights
{| class="wikitable"
|-
! Vehicle<br>Flight #
! width=125| Date
! Pilot
! Mach
! Velocity<br> (km/h)
! Altitude<br> (meters)
! Duration
! Comments
|-
| '''M2-F2 #1'''
| [[July 12]], [[1966]]
| Thompson
| 0.646
| 727
| 13,716
| 00:03:37
| First M2-F2 Flight. Unpowered glide. 320 km/h landing.
|-
| '''M2-F2 #2'''
| [[July 19]], 1966
| Thompson
| 0.598
| 634
| 13,716
| 00:04:05
| Unpowered glide. Determination of lateral stability control, longitudinal trim, vehicle performance and landing characteristics.
|-
| '''M2-F2 #3'''
| [[August 12]], 1966
| Thompson
| 0.619
| 692
| 13,716
| 00:04:38
| Unpowered glide. Determine effect of increasing Mach number, minimum damper requirements, testing of longitudinal and lateral stability and control.
|-
| '''M2-F2 #4'''
| [[August 24]], 1966
| Thompson
| 0.676
| 718
| 13,716
| 00:04:01
| Unpowered glide. Determine control damper requirements, lift-drag ratio, elevon response, flap effectiveness and longitudinal stability and control.
|-
| '''M2-F2 #5'''
| [[September 2]], 1966
| Thompson
| 0.707
| 750
| 13,716
| 00:03:46
| Unpowered glide. Evaluate 360 degree overhead approach, determine control damper-off handling qualities.
|-
| '''M2-F2 #6'''
| [[September 15]], 1966
| Peterson
| 0.705
| 750
| 13,716
| 00:03:30
| Unpowered glide. Pilot checkout.
|-
| '''M2-F2 #7'''
| [[September 20]], 1966
| Sorlie
| 0.635
| 678
| 13,716
| 00:03:31
| Unpowered glide. Pilot checkout.
|-
| '''M2-F2 #8'''
| [[September 22]], 1966
| Peterson
| 0.661
| 702
| 13,716
| 00:03:53
| Unpowered glide. Longitudinal and lateral stability and control with dampers.
|-
| '''M2-F2 #9'''
| [[September 28]], 1966
| Sorlie
| 0.672
| 713
| 13,716
| 00:03:53
| Unpowered glide. Complete pilot checkout and extend flight envelope.
|-
| '''M2-F2 #10'''
| [[October 5]], 1966
| Sorlie
| 0.615
| 692
| 13,716
| 00:03:45
| Unpowered glide. Explore lateral and longitudinal stability and control characteristics with dampers on and off.
|-
| '''M2-F2 #11'''
| [[October 12]], 1966
| Gentry
| 0.662
| 702
| 13,716
| 00:03:54
| Unpowered glide. Pilot checkout.
|-
| '''M2-F2 #12'''
| [[October 26]], 1966
| Gentry
| 0.605
| 642
| 13,716
| 00:03:47
| Unpowered glide. Obtain stability and control data at 7 and 11 degree attack angles and upper flap effectiveness.
|-
| '''M2-F2 #13'''
| [[November 14]], 1966
| Gentry
| 0.681
| 716
| 13,716
| 00:04:21
| Unpowered glide. Test stability and control, determine vehicle performance characteristics.
|-
| '''M2-F2 #14'''
| [[November 21]], 1966
| Gentry
| 0.695
| 735
| 13,716
| 00:03:50
| Unpowered glide. Test stability and control, determine vehicle performance characteristics.
|-
| '''M2-F2 #15'''
| [[May 2]], [[1967]]
| Gentry
| 0.623
| 661
| 13,716
| 00:03:51
| Unpowered glide.
|-
| '''M2-F2 #16'''
| [[May 10]], 1967
| Peterson
| 0.612
| 649
| 13,716
| 00:03:43
| Unpowered glide<br>Crash landing
|}
==Specifications (M2-F2)==
[[Image:Northrop M2-F2 diagram.png|right|350px|NASA M2-F2 Lifting body diagram]]
{{aero-specs}}
{{aircraft specifications
<!-- if you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] -->
|plane or copter?=<!-- options: plane/copter --> plane
|jet or prop?=<!-- options: jet/prop/both/neither --> jet
<!-- Now, fill out the specs. Please include units where appropriate (main comes first, alt in parentheses). If an item doesn't apply leave it blank. For instructions on using |more general=, |more performance=, |power original=, and |thrust original= see [[Template talk:Aircraft specifications]]. -->
|ref=
|crew= one, pilot
|capacity=
|length main= 22 ft 2 in
|length alt= 6.76 m
|span main= 9 ft 8 in
|span alt= 2.94 m
|height main= 9 ft 6 in
|height alt= 2.89 m
|area main= 160 ft²
|area alt= 14.9 m²
|airfoil=
|empty weight main= 4,620 lb
|empty weight alt= 2,095 kg
|loaded weight main= 6,000 lb
|loaded weight alt= 2,722 kg
|useful load main= <!--lb-->
|useful load alt= <!--kg-->
|max takeoff weight main= 7,485 lb
|max takeoff weight alt= 3,395 kg
|more general=
|engine (jet)= [[Reaction Motors XLR-11|Reaction Motors Upgraded XLR-11]]
|type of jet=four-chamber [[rocket engine]]
|number of jets=1
|thrust main= 8,000 lbf
|thrust alt= 36 kN
|thrust original=
|afterburning thrust main= <!--lbf-->
|afterburning thrust alt= <!--kN-->
|max speed main=Mach 0.707
|max speed alt= 466 mph, 750 km/h
|cruise speed main= <!--knots-->
|cruise speed alt= <!--mph,km/h-->
|never exceed speed main= <!--knots-->
|never exceed speed alt= <!--mph,km/h-->
|stall speed main= <!--knots-->
|stall speed alt= <!--mph,km/h-->
|range main= 8.6 nm
|range alt= 10 mi, 16 km
|ceiling main= 45,000 ft
|ceiling alt= 13,700 m
|climb rate main= <!--ft/min-->
|climb rate alt= <!--m/s-->
|loading main= 43.2 lb/ft²
|loading alt= 196 kg/m²
|thrust/weight= 1.3
|power/mass main= <!--hp/lb-->
|power/mass alt= <!--W/kg-->
|more performance=
|armament=
|avionics=
}}
==See also==
{{aircontent|
|related=
|similar aircraft=
*[[Martin-Marietta X-24|X-24]] -
*[[NASA M2-F1|M2-F1]] -
*[[Northrop M2-F3|M2-F3]] -
*[[Northrop HL-10|HL-10]]
|sequence=
|lists=
|see also=
}}
==External links==
*[http://www.dfrc.nasa.gov/Gallery/Photo/M2-F2/HTML/index.html Most of text taken from NASA Dryden webpage.]
*[http://www.dfrc.nasa.gov/gallery/photo/M2-F2/ NASA Dryden M2-F2 Photo Collection]
*[http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19980169231_1998082126.pdf Wingless Flight: The Lifting Body Story. NASA History Series SP-4220 1997 PDF]
{{Northrop aircraft}}
{{X-planes}}
{{aviation lists}}
[[Category:Lifting body aircraft]]
[[Category:Parasite aircraft]]
[[Category:United States experimental aircraft 1960-1969|M2-F2, Northrop]]
[[Category:Gliding in the United States|M2-F2, Northrop]]
[[Category:Rocket-powered aircraft|M2-F2, Northrop]]
[[de:Northrop M2-F2]]
[[ja:M2-F2]]