Improvement of MiG 17 over MiG 15

十月 28, 2007 at 11:28 | 張貼於jet, MiG | 發表留言






chr3_1-17.jpg chr3_1-18.jpg




chr3_1-19.jpg chr3_1-21.jpg



However, in 1949 on basis MiG-15bis was developed for the purpose of further increase in the velocity the design of a similar aircraft I -330 (“SI"). but with the sweep angle of wing in 45° by a somewhat elongated aft fuselage section and the sharper on top form of vertical tail assembly. This was done on the basis of studies, experiences and those considerations, that MiG-15 with the wing into 35° it began already to eliminate itself. Aircraft “SI -2″ there was vypushen at the end of 1949. and on 1 February, 1950, test pilot I. t. ivashenko during the plant tests on his first copy on the combat aircraft it for the first time reached at a height 5000 m of the speed of 1161 km/h. Thus far there are the speeds to M=0.92. But during March I. t. ivashenko perished with the crash of this aircraft, which detained tests. The second and third copies (“SI -02″ and “SI 03″) underwent tests (on 20 June, 1951), they proved to be successful and obtained designation MiG-17 with the starting into the series, and then into the mass production in 1951 for the change MiG-15 – as its direct continuation and development. Engine – the same VK -1, but speed grew ia 40 – 50 km/h, was improved maneuverability at high (but not on the small) altitudes, it grew rate of climb, everything with the same engine. In the report it was noted that, in spite of a certain worsening in takeoff data, aircraft can take off from the same airfields as MiG-15. By the exterior forms and the construction MiG-17 (Fig. 203) it had many elements of similarity MiG-15. Differences were in essence following. The sweepback of wing on the leading edge was 450 in the root of the half span) and 42° in the end part, wing area was increased to 22.6 m2. Dihedral is equal to –3°, ia each console – on three boundary layer fences with height to y00mm. wing profile only is thinner, joining wing with the fuselage improved due to the section of trailing edge it is onboard. Fuselage is elongated, with respect to larger sweepback, the tail assembly is a little increased, especially vertical, its sweepback – 56°, horizontal – 45. Under the end part of the fuselage


發表迴響 »

RSS feed for comments on this post. TrackBack URI


在下方填入你的資料或按右方圖示以社群網站登入: Logo

您的留言將使用 帳號。 登出 / 變更 )

Twitter picture

您的留言將使用 Twitter 帳號。 登出 / 變更 )


您的留言將使用 Facebook 帳號。 登出 / 變更 )

Google+ photo

您的留言將使用 Google+ 帳號。 登出 / 變更 )

連結到 %s

Entries留言 feeds.

%d 位部落客按了讚: