Northrop X-4 Bantam

Northrop X-4 Bantam
Državi	Zda
Vlogo	Prototip letala brez repa
Prvi let	15. december 1948
Zgrajena	2

V Northrop X-4 Bantam je bil prototip majhnega twinjet letala, ki ga je leta 1948 proizvajala korporacija Northrop. Ni imel vodoravnih repnih površin, odvisno od kombiniranih dvigal in aileronskih nadzornih površin (imenovanih dvigala) za nadzor v odnosih z metom in rolo, skoraj točno na način podobnega formata, raketni pogon Messerschmitt Me 163 nacistične nemčije Luftwaffe. Nekateri aerodinamiki so predlagali, da bi odprava vodoravnega repa prav tako odpravila težave s stabilnostjo pri hitrih hitrostih (imenovanih šok stall), ki so posledica interakcije nadzvočnih udarnih valov s kril in horizontalnih stabilizatorjev. Ideja je bila utemeljena, vendar so sistemi za nadzor letenja tega časa preprečili uspeh X-4.

Vir: Northrop X-4 Bantam na Wikipediji

Northrop X-4 Bantam Walk Aroundd
Photographers	John Heck, Randy Ray
Localisation	National Museum of the USAF
Photos	50

Northrop X-4 Bantam 01

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Northrop X-4 Bantam 09

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General Characteristics and Role

The Northrop X-4 Bantam was an experimental jet aircraft developed for the U.S. Air Force and the National Advisory Committee for Aeronautics (NACA, the precursor to NASA) in the late 1940s. Its primary role was to investigate the aerodynamic properties of a tailless aircraft design at transonic speeds (speeds approaching the speed of sound, or Mach 1). It utilized a semi-tailless configuration, meaning it lacked a horizontal tail stabilizer but retained small vertical fins. The tailless design was believed to reduce the shock waves and control issues experienced by conventional aircraft as they approached the sound barrier. The Bantam was built as a small, swept-wing jet to minimize costs and complexity during the high-risk transonic research phase.

Property	Typical Value (X-4)
Vlogo	Experimental Aircraft (Transonic Stability Research)
National Origin	Združene države Amerike
proizvajalec	Northrop Corporation
First Flight	15. december 1948
Posadke	1 Pilot
Wing Sweep	35 degrees
Dolžina	7.01 m (23 ft 0 in)
Peruti	8.23 m (27 ft 0 in)
Višina	4.52 m (14 ft 10 in)	Gross Weight	3,524 kg (7,770 lb)

Powerplant and Flight Controls

Engine: 2 x Westinghouse J30 turbojet engines.
Thrust (Total): Approximately 1,600 lbf (7.1 kN).
Maximum Speed: 1,032 km/h (641 mph, or approx. Mach 0.85).
Control Surfaces: All control was handled by elevons (control surfaces that combine the functions of elevators and ailerons) on the trailing edge of the wing, and twin vertical rudders.
Stability Issue: Testing confirmed that while the X-4 was stable at low speeds, it experienced severe longitudinal stability issues when flying faster than Mach 0.88, leading to a tendency to pitch up and lose control.

Program Outcome and Legacy

Test Program: The X-4 completed 81 research flights at the NACA Muroc Flight Test Unit (later Edwards AFB).
Discovery: The program proved that a simple tailless design was unsuitable for sustained transonic flight due to the poor stability characteristics encountered.
Influence: This finding was crucial, convincing designers to use a conventional horizontal stabilizer (tailplane) or the all-moving stabilator on high-speed jets, which became the standard design for supersonic aircraft.
Preservation: Both prototypes built are preserved: one (46-676) is at the U.S. Air Force Museum in Ohio, and the other (46-677) is at the National Museum of Nuclear Science & History in New Mexico.