8/3/2023 0 Comments Supercritical airfoil![]() ![]() Since then, adaptations of supercritical wing technology have been built into nearly every transport category aircraft. The modern supercritical wing was first flown on a modified F-8 Crusader during a NASA research project in the early 1970s. This eventually led to the development of the supercritical wing. In the early ‘70s, when the economic demand for cheap high-speed air travel became greater, research began into a new type of wing which would perform more efficiently at near supersonic speeds. These challenges were eventually compensated for in the designs of supersonic military aircraft, but transport category aircraft were left orphaned with wing designs from the days Wilbur and Orville. Two of the most notable of these effects are the sharp increase in drag caused by the formation of a shockwave, and the rearward shift of the center of lift generated by the wing. It was quickly noted that when an aircraft approaches and passes the speed of sound, many unfavorable things begin to happen. In essence, the supercritical wing has revolutionized modern air transportation.ĭuring early testing in the 1940s and 1950s into supersonic flight, it became apparent that flight into the supersonic regime presented some serious engineering problems. This mid 1970s invention, though seldom discussed, has allowed airliners to fly faster and farther, while burning less fuel. In this post, I am going to shed a little light on the supercritical wing and discuss how it works, and how it compares to a conventional wing. In fact, the CRJ series of aircraft incorporates one of the most pronounced examples in the entire fleet of transport aircraft of a specially designed wing type called the supercritical wing. The reason for my astonishment was because the wing of the CRJ was designed significantly differently than any other plane I had flown before. Furthermore, it enables the cruise performance and drag divergence Mach number to be predicted with only one simulation of the cruise point, which will greatly save the computational cost of optimizations.“Wow, it really is curved on the bottom!” I still remember how surprised I was when I took my first look at the wing of the CRJ. ![]() It indicates that the drag divergence Mach number can be increased by obtaining a shock wave that is further upstream in the detailed design. Compared with Korn's equation, the discovered correlation reduces the maximum prediction error by approximately 40%. A new linear correlation is discovered and validated by existed airfoil databases. Correlation screening and multivariate regression are carried out to discover knowledge about the airfoil drag divergence Mach number and pressure distribution features. This paper designs a supercritical airfoil database that covers the typical free stream Mach number, angle of attack, lift coefficient, and geometry of modern transonic commercial aircraft. However, it neither reveals the key factors of fluid features on the drag divergence nor contributes to the detailed design. It is very helpful in the aircraft initial design. ![]() For example, Korn's equation predicts the airfoil drag divergence Mach number using the airfoil maximum thickness and the lift coefficient. Aerodynamic rules and knowledge are often obtained through theoretical research and experiments, which have contributed greatly to aircraft design. ![]()
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