Embraer E190-E2 as Modern Aircraft compatible with Sustainable Development Goals

Embraer E190-E2 as Modern Aircraft compatible with Sustainable Development Goals


Embraer’s E-Jet E2 series is a mid-range aircraft developed in the aftermath of the first E-Jet. The show made its premiere during the 2013 Paris Air Show. The first exception, the E190-E2, took to the skies for the first time on May 23, 2016, and was validated on February 28, 2018, before entering Widere service on April 24, 2018. Three twinjet variants share four abreast fossils of varying lengths and three new wings, as well as a two-sized Pratt & Whitney PW1000G turbofan, two-dimensional aircraft controls, and an upgraded cabinet. Embraer is the product of the efforts of hundreds of individuals who, over the course of 47 years, overcame the task of establishing a Brazilian firm as a key player in the global aerospace industry. The corporation was founded in 1969 in So José dos Campos, Brazil, and its headquarters are still situated in 10 Brazilian towns and 17 other places throughout the world. In addition, the corporation holds 51% of Visiona Tecnologia Espacial Telebras, a joint venture with Telebras, and 65% of the Portuguese company OGMA, which specialises in aviation repair and production. ELEB, Embraer Aero Seating Technologies (EAST), Atech, Savis, and Bradhar are among the firms that use the hosting facility. The company designs, develops, manufactures, and sells aircraft, systems, and solutions for the Commercial Aviation, Executive Aviation, and Defense & Security industries, with customer support and services accessible in over 100 countries. Embraer finished the fiscal year with 18,506 employees worldwide and 240 airlines, a US $ 6.2 billion surplus, and a US $ 19.6 billion order backlog.


Following the receipt of the type certificate, the first E190-E2 was delivered in April 2018 for the opening of operator Widere, refurbished with 114 seats in one category, and was followed by the delivery of Air Astana and Chinese GX Airlines. Embraer said that due to the limited combustor life of their Pratt & Whitney PW1900G engines, some of the first E-Jet E2s may need to be reinstalled before the aircraft can be delivered. The business class, which will be available in mid-2019, is designed using a 2 + 2 moveable seat construction that allows for a seat height of up to 54 (137 cm).

Embraer has mandated 99 percent shipping dependability after 12 months and 99.5 percent reliability after four years, but E1 requires ten years to attain its desired reliability. Widere delivered their first E190-E2 to Sao Jose dos Campos on April 4, 2018. On April 24, 2018, a ferry service between Bergen and Tromso, Norway, was inaugurated. In June 2018, the first three E190-E2s delivered to Wideroe accumulated 413 flying hours and 332 cycles, an average of 6.57 cycles per day and an average stage length of -1.28, with a delivery reliability of 99.35 percent and a schedule reliability of 97.74 percent. After its first year of operation, Widere achieved a shipment dependability of 98.5 percent.

Boeing and Embraer were exploring a prospective merger in December 2017. On July 5, 2018, Boeing and Embraer announced a Partnership Agreement to form a joint venture in which Boeing would hold 80% of Embraer commercial aircraft manufacture, production, and service, including the E-Jet E2. According to aviation industry analysts, the acquisition will help both firms since Boeing requires smaller aircraft, such as the E-Jet and E-Jet E2 families, and Embraer requires the marketing strength of a larger corporation as the E-Jet E2 family sells. a little bit

Embraer shareholders approved the deal on February 26, 2019, and the new joint venture was pending legal clearance. Boeing cancelled the deal on April 24, 2020, citing Embraer’s failure to meet the requirements of the agreement. Embraer criticised Boeing’s justifications, claiming the business was attempting to avoid its commitments, and stated that it will pursue “all remedies to Boeing’for losses caused,” which industry analysts believe may include the loss of lost orders while clients wait for the deal to finish.


The following aerodynamic design characteristics contribute to this performance:

• A negative lifting strut at the wing-strut junction that is locally rectified by the wing to preserve an elliptical overall spanwise lift distribution.

•An outwards normal force distribution inside the wing-strut junction to lessen differences in local pressure between surrounding surfaces; this is accomplished in part through an outwards directed twist distribution.

•New air foil shapes surrounding the wing-strut junction to reduce the flow’s fast acceleration, which would otherwise result in a significant fall in local pressure, resulting in shock development and boundary-layer separation.

•A positive lifting strut close to the strut-fuselage joint. The following aerodynamic design characteristics contribute to this performance:

•A negative lifting strut near the wing-strut junction, which is corrected locally by the wing to preserve an elliptical overall spanwise lift distribution.

•An outwards normal force distribution inside the wing-strut junction to eliminate differences in local pressure between adjacent surfaces; this is accomplished in part by an outwardly directed twist distribution.

• •A positive lifting strut at the strut-fuselage junction to alleviate the fast acceleration of the flow, which would otherwise produce a significant fall in local pressure, resulting in shock development and boundary-layer separation

Three primary goals:

1) Determining if the strut-braced drag low wing design can be reached at Mach 0.78 when computing wave drag, viscosity and pulse pulses, as well as the impacts of transonic disturbances in and around the wing-strut junction.

2) Examine features of aerodynamic design and trade-offs related with such strut-braced structures.

3) Provide a dependable estimate of the corresponding fuel savings offered by strut-braced-wing preparation at the jet circuit.

In terms of the third aim, the basic tube-and-wing circuit jet will be improved as well, acting as a working platform for new, cutting-edge aircraft like the Embraer E190-E2. The 2020 technological standards will be examined on the strut-braced wing to avoid the uncertainties around the advantages of advanced technology and to focus on the prospective fuel systems for self-configuration. As a result, current study will seek to shed light on how well the strut-braced-wing configuration can perform at a regional jet level with known technology when compared to the typical competitive tube-and-wing layout in service.


The fact that Embraer survived despite Brazil’s political and economic upheaval is astounding. This is only possible because Embraer produces high-quality, competitive goods. The company’s basic business planes are the best in class. Its regional jets are now the sole Western-produced aircraft in that market. Embraer has also begun an aggressive campaign to modernise a battleship that will compete for the famous Lockheed Martin C130 contract. The KC-390, a new aircraft for the Brazilian Skies Force, has lately pushed forward to fill the air. That’s something Boeing’s KC-46, based on the 767, had some issues with.      

The E2 series is Embraer’s high-end models on the commercial sector. These planes are significant improvements over prior versions, and many people now refer to them as “E1.” The three variants in the series range in size from 80 to 146 in a two-stage setup.

Embraer was the latest to modify its E1 planes, which were just seven years old when the initiative was revealed. The evaluation was imposed upon them when Bombardier created the C Series, which increased market pressure on Airbus to modernise its A320neo family and give birth to the Boeing 737 MAX.

Bombardier’s big earthquake finally forced the business to fly on a commercial airliner. Despite the outbreak, the C Series evolved into the Airbus A220 and sold successfully. Airbus’ A320neo family has sold better than predicted, while the MAX has seen over 1,000 cancellations but remains popular with numerous current 737 operators.

Unfortunately, Boeing ended aircraft terminating its deal with Embraer, and more viewers would attribute this to the MAX squabble than to anything Embraer did or did not do. With the exception of Boeing, practically everyone in the business thought that having E2 accessible in marketing efforts during the violence would tremendously help Boeing. Interest in the A220 has been consistent, if not growing, according to Airbus. These low-seat variants are the greatest ever for reducing traffic flow time (“the correct size,” as the name implies).

Given that background, let’s look into Embraer in more detail. First, let’s take a look at the E1 family, which will serve as Embraer’s cornerstone. Its E2 family orders will most likely follow the original industrial attitude rather than the previous models.

The table depicts the key issues that Embraer is experiencing with the E190. The most well-known model is the only newly established Western airline that is subject to the US Scope Clause. Embraer is under minimal pressure to push the E175-E2 into the market due to its great success. This is fortunate because the E190-E2 has piqued the market’s interest. The table also compares the E190 to the E195 in terms of power. Looking at the market reaction to E2, we can see that E195-E2 has become highly popular in the two primary models.

This is significant since Airbus saw greater demand in the A220-300 than the -100. In the seating of fewer than 150 seats, Airbus and Embraer offer something fresh and quite pleasant. Boeing, with the exception of the recent Southwest MAX7 election, does not do this.

It is undeniable that the E2 sequence is slower than the E1. Embraer confronts the same problem as Airbus with its A330ceo and A330neo models: the replacement model arrives quicker than the original older model.

The following are the most serious dangers to the Embraer E2 family’s hopes:

1. The US Scope Clause will not be amended to let E175-E2 to service US regional airlines.

2. Because of Boeing’s collapsed deal, Embraer is forced to compete directly with Airbus.

3. The pandemic has stifled progress in aviation and recycling. This sword has two edges, because the E2 jets equal the right to return after the outbreak.

Embraer has limited options with these three factors. They are all overwhelming, yet each one requires a unique response.


Establishment of the Composition Problem

Strut-braced-wing and normal tube-and-wing aircraft designs are based on regional jets like the Embraer E190-E2, which has a maximum cargo of 104 PAX passengers, a design range of 3,100 nmi, and general operating conditions of Mach 0.78 and 37,000 ft. These planes are known as the SBW100 and CTW100 in this country. Each aircraft is powered by PW1919G engines with a maximum departure thrust of 20,860 lb, a dry weight of 4,800 lb, engine length and flow width of 187.0 to 81.0, and a TSFC of 0.587 lb / lb / hour. These constraints are maintained by the CTW100 since the aircraft is designed to mimic the Embraer E190-E2, although the SBW100 can be adjusted by the rubber engine model specified in Phase II.B. Using the measuring technique, each aircraft is constructed to match the design specification of the payload diagram displayed in Figure 4, which is based on the Embraer E190-E2 airport planning handbook. These payload distance points are the maximum pay point (R1), which is used to measure the maximum departure weight (MTOW) and the maximum fixed weight of each plane; the range of fuel range in the area of MTOW (R2), which determines the maximum mass of fuel (MFW); and a nominal point (NR) point, which represents the general flight policy of regional jets of this type. Each MDO level of concept aims to minimise block fuel consumption over the NR function, which entails conveying the paid load of 104 PAX design across a distance of 500 nmi. Because the CTW100 is meant to replicate the Embraer E190-E2 as a performance baseline in comparison to the SBW100, the aircraft and engines are represented as drawings, with all operating conditions provided based on the reference aircraft. This is sans the unit’s thickness, which is not known to the public. Thus, size-to-chord scale design factors are contained in the centre line, root, crank, and tip, and are translated by a line on each portion of the wing. These degrees of freedom are constrained by the minimal quantity of gasoline volume to guarantee that there is enough fuel for a good grade fuel to be utilised. According to Andrews, Perez, and Wowk, the wing root is assumed to be constrained by the weight of the wing, and the major structures are thought to be made of 7075-T6 aerospace grade aluminium alloy. A number of design factors are incorporated in the SBW100 conceptual design to enable the measurement and efficiency of each design machine’s wing and tail systems, motion system, and beginning flight height. Table 1 lists these degrees of freedom. Wing extensions, wing sweep, and wing-strut junction are not considered design changes since they are predicted to surpass the capabilities of low-order models, necessitating high fidelity design. Instead, these constraints are imposed or constrained depending on the strut-braced wings discovered in the literature that have been examined for high fidelity, as will be detailed further below. Because departure and seating may not be precisely modelled after Faber, there are constraints on wing loading design and thrust-to-weight ratio to guarantee appropriate wing and thrust space is available under these situations. The wing load, in particular, is subject to a maximum bond of 110.2 lb / ft2, while the thrust-to-weight ratio must be more or equal to 0.336. T on the reference aircraft, which, although resulting in a robust structure, avoids the issue of developing high-altitude systems and estimating low-speed aerodynamic performance while assuring that the aircraft can fly within the same envelope. Furthermore, the weight of the second wing is estimated using the same size and kind of slats, flaps, spoilers, and ailerons as the reference plane. These concepts enable for the performance testing of first-generation flying aircraft without the effort of constructing new high-altitude equipment and control regions. With a focus on the design of the high-speed wing system, the strut-braced wing has an average look of around 16-20. This conclusion is based on the Boeing SUGAR High (765-095-RD-DF), which has 30% bigger wings than a typical single-plane aircraft, which is limited to code C gate gates at 118 ft, and the wing folding mechanism is used around 87 percent of the time.


Advanced designs for each regional aircraft are available at the MDO level of concept. Gradient-based designs have effectively altered the potential of machine precision, with acceptable reductions of 4 to 5 orders of magnitude, and preventing NR machine fuel from changing to an invisible value. The lowest volume of fuel capacity is applicable for the updated CTW100, which is common for conventional wing designs intended with little fuel combustion or high aerodynamic efficiency. The configured SBW100, on the other hand, is not subject to the same restriction. This is owing to reduced fuel consumption as well as the availability of surplus fuel storage inside the strut. The wing design in the SBW100 achieves its utmost limit, precisely balancing the aircraft wing. Locally, the minimum thrust-to-weight restriction does not apply. Instead, the propulsion system is assessed by the need for high-rise MFR equipment, which necessitates more concentration at higher altitudes, necessitating an increase in the maximum departure parameter. The buckling restrictions apply to the specified design as well. Part of the inner strands, in particular, are discovered to be confined to the folding condition during the layout with a balance of + 2.5g, and the main strut is measured in accordance with the buckling during the 1g diving condition. Buffet jeans, despite the coefficient of long-distance travel, are not a well-designed item. This might be attributed to the combination of big, fluffy, and thin-winged wings, which leads in improved wave gravity performance. Finally, it is discovered that both tail volume barriers work at greater altitudes. Table 3 shows the current state of each set of the updated SBW100’s indirect constraints. Table 4 shows the idea outcomes for the MDO concept. The CTW100’s design weight is similar to that of the Embraer E190-E2, with an MTOW of 124,340 lb, MZFW 102,514 lb, OEW 72,752 lb, and MFW 30,203 lb. The 6024 SBW’s main advantage over this reference aircraft is its low wing weight, which is achieved through a combination of excellent structural efficiency afforded by strut-braced wing topology and the use of lightweight composite materials. The SBW100 also includes a light rail system, which is achieved by a huge temporary T-tail configuration arm and the compact horizontal tail design. A bigger temporary arm, as well as fines connected to upper wing configurations, led in an 11.9 percent increase in fuselage weight, the first representing the flexible loads received by the fuselage in the power model. However, according to Torenbeek’s weight model, the weight of the fuselage is unaffected by the pressurisation loads of the high cabin during high altitude trips.

In terms of aerodynamic performance, the SBW100 wing’s high aspect ratio and low density produce a 16.0 percent high lift drag during the specified distance travel. This is despite the integrated wing system’s high humidity. While the combination of a high wing aspect ratio and sweeping can result in long altitude times if the wing stalls at low speeds, a 30-degree sweeping angle corresponds to a more modest 16-17 aspect ratio when compared to low sweeps. and the high aspect ratio of Boeing SUGAR High, which helps the SBW100 remain less affected by the trend. Given the rise in fuel prices, the SBW100 has an optimal start-up of 44,670 ft of boating, resulting in a CL design of 0.68 ft. Based on lower-order models, the SBW100 has 9.3 percent better block fuel over NR performance than the CTW100. Figure 6 depicts sophisticated designs created in Faber that serve as the foundation for building models utilised in the creation of aerodynamic sequence strength.

High-fidelity wing-fuselage-tail models of the CTW100 and SBW100 regional planes are constructed based on Faber’s initial drawings. The fuselage nose and tail designs for both aircraft are based on the Airbus A220-300, which is considered to feature a fuselage design indicative of current airliners ranging from big regional jets to small single-aisle planes. This fuselage design has been scaled down to the regional jet class, with an equivalent circular diameter compatible with Faber’s low-fidelity models. The wing-fuselage fairing for the CTW100 is likewise based on the Airbus A220-300, while the wing-fuselage and strut-fuselage fairings for the SBW100 are based on the PADRI strut-braced-wing geometry. To help the optimizer find the best design, the thickness distribution across each wing (and strut) is scaled to meet the linear distributions supplied by Faber. Furthermore, each optimization starts at an angle of attack that fulfils the CL objective. This guarantees that the optimization begins around the borders of the constant lift, minimal volume, and minimum (t/c) max constraints mentioned in Section IV.D, which we expect will be active for the best design.


The aerodynamic design and fuel economy of a strut-braced-braced-braced regional aircraft based on the Embraer E190-E2, with a maximum payload of 30,200 lb and a design distance of 3,100 nmi at maximum passenger loads, are investigated in this paper. This equals 104. PAX. The conceptual design of the strut-braced-wing aircraft is based on the MDO framework of the lower and middle dimensions, assuming that the 2020 technical standards, as well as the imaginative measurement of a standard tube-wing aircraft, are included and operated as an aircraft. Aerodynamic forms were then developed and employed in the building of each aircraft, with the goal of lowering drag on the 500 nmi machine trip by Mach 0.78. The results show that developing an aerodynamic shape based on RANS values, using a patch-based junction shift scheme, can reduce shock formation and border layer separation between wing-strut junctions while maintaining low travel drag, even when less than both lifting and cutting limits, the first with a relatively high CL design of 0.68.

The strut-braced wing gives a greater ride of 12.9 percent L / D when compared to a similar tube-and-wing regional aircraft produced in the same manner. Taking into account the weight and efficiency of the propellant, as well as the fuel required for departure, ascension, descent, and landing, this results in a 7.6 percent reduction in fuel consumption throughout a 500 nmi journey. Given that the strut-braced-wing regional aircraft must remove a major portion of the purpose of boarding and disembarking from the highest point of the boat route needed by design CL, the distance travelled is longer than in the fuel-efficient design. As a result, we may expect even more fuel savings while flying long distances, which is not unusual in regional planes of this sort. Working over extended distances results in a larger average wing load, allowing CL right to reach higher heights while simultaneously lowering fuel consumption. By example, we predict a 10.3 percent save on block fuel for pre-ordering the 1,000 nmi machines in the CL building. This also implies that strut-braced-wing layouts may yield higher fuel savings for long-distance aircraft, like as single-dimensional aircraft, where gasoline accounts for a major amount of overall fuel. Following the demonstration of the capability of creating a strong draught circuit aircraft at Mach 0.78, the next 37 steps would be to study if this functionality could be maintained across the required range of cruise circumstances utilising multiple locations. Other future work will include investigating the potential benefits of strut-braced-wing configuration for a single aircraft, carefully examining the trade-off between aerodynamics and architecture, and determining the suitability of truss-braced-wing configuration with one or more jury struts, using fidelity high aero structure, and dealing with concerns about the vulnerability of these flying wing systems.

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