Operation 'Grapple' : testing Britain's first H-bomb by K. Hubbard, M. Simmons

By K. Hubbard, M. Simmons

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The second X-1 was built with a NACA 65-11 0 airfoil wing section of 10% thickness (the 8% wing was significantly more difficult to manufacture than the 10%; the 8% wing, due to structural requirements, had wing skins that tapered from 1/2-in. thickness at the root to approximately 1/32-in. at the tip). The taper ratio for both wing types was 2:1. 2 in. 1 in. Incidence atthe root was + 2-1/2°; incidence at the tip was + 1° 30 minutes. Dihedral was 0° and leading edge sweepback was 5° 2 minutes and 52 seconds.

In. Additionally, the pilot was provided with a personalized oxygen system (this unit underwent several changes during the course of the X-l 's flight test program). A control yoke for aileron and elevator actuation was provided along with conventional rudder pedals. The pilot was not furnished an ejection seat (though studies for an ejection seat were undertaken, it was concluded that it would be of little use at high speeds and that the weight penalty would be too severe). In an emergency, he was expected to remove a pin from the hinged control column and displace it, remove the door panel located on the right side of the cockpit, and manually bailout.

7 in. and the tread was 51 in. The first and third X-1s were built with a NACA 65-108 airfoil wing section of 8% thickness/chord ratio. The second X-1 was built with a NACA 65-11 0 airfoil wing section of 10% thickness (the 8% wing was significantly more difficult to manufacture than the 10%; the 8% wing, due to structural requirements, had wing skins that tapered from 1/2-in. thickness at the root to approximately 1/32-in. at the tip). The taper ratio for both wing types was 2:1. 2 in. 1 in. Incidence atthe root was + 2-1/2°; incidence at the tip was + 1° 30 minutes.

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