The oblique flying wing (OFW) is a wing of elliptic planform having mininum wave drag at transonic and supersonic speeds up to M=1.4. For minimum wave drag due to lift the equivalent body of revolution must be a Karman Ogive; whereas for minimum wave drag due to volume of the equivalent body of revolution must be a Sears-Haack body.
The first to prove that such a wing has minimum wave drag was R.T. Jones (1951). More recently, inviscid CFD calculations proved that the best performances are obtained with a wing of aspect-ratio 10:1 with a cruise CL=0.068. The best yaw angle would be 68 degrees, and the wing would have the flying operation shown in Fig. 1 below.
Figure 1: Oblique flying wing, AR = 10:1, yaw = 68 deg
The use of the OFW would be limited to transonic and low supersonic speeds, since the increasing sweep reduces the effective wing span, which on turns increases the induced drag. Fig. 2 below shows a qualitative behavior of the CD of the OFW as compared with the swept-back wing (SBW).
Figure 2: Oblique flying wing vs Swept-back wing
There has been recent research devoted to the computational aerodynamics, to the optimization of the wing, and to preliminary sizing/design. The data reported below are those relative to a McDonnell- Douglas study for a commercial transport oblique wing:
From the above data we find that the optimal oblique flying wing is a huge body, with a span more than twice as big as the Boeing 747-400 ! Such an aircraft is unlikely to be able to land on any airport, although the wing is the best theoretical compromise for weight, flutter, flexibility, and other aeroelastic problems.