Edit: Unacceptable personal attack removed by moderator.

Beautiful air combat:

Everybody say a big thankyou to flateric for discovering the official patent application for the PAK-FA, no less. Legible google trans due to length & time constraints:

12) ABSTRACT OF INVENTION
Status: As of 08.11.2010 – is valid

(21), (22) Application: 2009133611/11, 09.09.2009

(24) Date of the origin of the term of the patent:
09.09.2009

(46) Published: 09/27/2010

(72) Author (s):
Mikhail Pogosyan Aslanovich (RU),
Davidenko Aleksandr Nikolaevich (RU),
Strelets Mikhail (RU),
Runishev Vladimir Aleksandrovich (RU),
Tarasov Alexey Z. (RU)

(73) patent (s):
Open Joint Stock Company “Sukhoi” (RU)

(54) MULTIMODE highly-integrated aerodynamic AIRCRAFT LAYOUT

(57) Abstract:
The aircraft has a fuselage, in which the middle part (2) seamlessly paired with swept wing (3), warhead (1) and tail (6), where the all-moving vertical tail (4) and all-moving horizontal tail (5). The head part (1) the fuselage is light (10). The fuselage has increased the width of the cross section and recruited from airfoils whose height allows you to place the main cargo compartment in the fuselage between the air intakes. The invention is directed to a uniform distribution of air loads and increase load-bearing properties of the fuselage. 10 ill.

Спойлер: Скрыть
The invention relates to multi-mode aircraft operated in supersonic and subsonic flight speeds in a wide range of altitudes. Preferred scope of the invention are multi-mode super-maneuverable aircraft with a cruising flight at supersonic speeds and low level of visibility in the radar (radar) range.

Known in the art aircraft integral aerodynamic layout containing one carrying the fuselage, in which the middle part of the fuselage smoothly paired with swept wing, head of the fuselage and its tail part (RU 2140376 C1).

As a well-known shortcomings of the aircraft should indicate the following. In a plane distribution of goods to the external load does not allow to achieve a low degree of visibility of the radar, and high aerodynamic characteristics at supersonic flight regimes.

Due to the complex technical solutions applied in the layout and, above all, the integrated aerodynamic configuration of the fuselage, the plane is characterized by high value of the aerodynamic qualities at subsonic flight conditions.

The technical result on the aim of the invention is to create an aircraft has a low level of radar visibility, maneuverability at high angles of attack, high aerodynamic efficiency at supersonic speeds and at the same time preserving a high aerodynamic quality at subsonic regimes.

The technical result is achieved by a multi-mode highly maneuverable aircraft integral aerodynamic layout containing the fuselage, the middle part of which is smoothly conjugate with swept wing, head of the fuselage and tail, all-moving vertical and all-moving horizontal tail located in the rear fuselage, the average integrated with the fuselage center-wing and made flattened in the vertical direction, and its outer surface in the longitudinal direction is formed by a set of airfoils with high building heights, providing accommodation within the fuselage, built-in cargo compartments, with the upper surface of the fuselage, paired with the outer surface of the lamp and the expanding at the site from the lantern to the tail section of fuselage with decreasing curvature.

The invention is illustrated by drawings, where Figure 1 shows the plane in plan view, in Figure 2 – section A-A Figure 1; in Figure 3 – section B-B Figure 1; in Figure 4 – section B In Figure 2, in Figure 5 – section F-F Figure 2, Figure 6 – Rotation of least resistance (the body Siirsa-Haack) on Figure 7 – position of transverse sections of fuselage in Figure 8 – transverse section 7 shows, in Figure 9 – Schedule of cross-sections of the aircraft fuselage; Figure 10 – The enlarged part of the graphic cross-sectional areas of the fuselage of a lantern.

The aircraft has a fuselage, in which the average of the two seamlessly paired with swept wing 3, the head part 1 of the fuselage and the tail 6. In the rear part 6 of the fuselage are all-moving vertical 4 and all-moving horizontal tail 5. At the head of a fuselage is light 10.

In terms of aerodynamic layout aircraft has the following features: wide lifting fuselage and smoothed graph cross-sectional areas at the site of an airplane cockpit.

The fuselage has increased the width of the cross section (Fig. 1, 2) and recruited from the airfoils 11, 12, 13 (Figure 3, 4, 5), whose height can accommodate the main cargo compartment 9 in the fuselage of the aircraft (Figure 2, 3) between the air inlets 8 and also provides the necessary building height to accommodate the side cargo compartments 7 (Figure 2, 4).

In addition to space for cargo, resulting in a flattened layout an even distribution of air loads on airframe surface and an increase in load-bearing properties of the fuselage from the perspective of a lifting force that allows you to keep the aerodynamic characteristics of aircraft in general, smaller wing area,

In addition, a flattening of the fuselage reduces the effective area of the radar in the most likely areas of exposure: Side and front projection plane.

Smoothing schedule cross-sectional areas at the site of an airplane cockpit can improve the aerodynamic characteristics of aircraft by reducing drag.

Besides the general theoretical outline, the aerodynamics of the plane and drag affect the arrangement and mutual linkage aircraft parts. To estimate the drag on the mutual influence (interference), the design rule is used areas (Figure 6), which is as follows: in order to reduce the resistance, curve 14 cross-sectional areas of all elements of Sj plane along the length of the aircraft shall comply with the diagrams of the equivalent body of revolution least resistance (cigar-shaped body of high aspect ratio, the so-called body Siirsa-Haack).

According to the state of the art in the design of aircraft used the scheme to link canopy and fuselage, shown in Figure 8 (A – a common scheme), which is characterized by the fact that cross-sectional area decreases in the area of the canopy to the tail. The schedule of areas for this scheme has a marked departure from the body Siirsa-Haack in the canopy (Figure 9 and Figure 10, section A).

To improve the aerodynamic characteristics of a scheme for linking, which consists in the fact that the upper surface 15 of the fuselage expands on the section of the lamp 10 to the rear part 6 of the fuselage, compensating for the decrease in cross sectional area (Figure 8, B – invented by the scheme), resulting in smoother “failure “on the graph area of a lamp driver, which is characteristic for conventional aircraft integral aerodynamic layout. The curve on the chart area close to the optimal shape, which indicates an improvement in aerodynamic performance (Figure 10, section B) by reducing drag.

Claim
Multimode highly maneuverable aircraft integral aerodynamic layout containing the fuselage, the middle part of which is smoothly conjugate with swept wing, head of the fuselage and tail, all-moving vertical and all-moving horizontal tail located in the rear fuselage, wherein the middle part of the fuselage is integrated with center-wing and made flattened in the vertical direction, and its outer surface in the longitudinal direction is formed by a set of airfoils with high building heights, providing accommodation within the fuselage built cargo compartments, with the upper surface of the fuselage, paired with the outer surface of the lamp and extending the area from the lantern to the tail section of fuselage with decreasing curvature.