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According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of

According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and about 0.45.

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1. A gas turbine engine assembly, comprising: a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge; andan inlet portion forward of the fan, a length of the inlet portion having a dim

1. A gas turbine engine assembly, comprising: a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge; andan inlet portion forward of the fan, a length of the inlet portion having a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion,wherein a dimensional relationship of L/D is between 0.2 and 0.45. 2. The assembly of claim 1, wherein the dimensional relationship of L/D is between 0.25 and 0.45. 3. The assembly of claim 2, wherein the dimensional relationship of L/D is between 0.30 and 0.40. 4. The assembly of claim 2, wherein the dimensional relationship of L/D is 0.35. 5. The assembly of claim 1, wherein the dimension L is different at a plurality of locations on the inlet portion;a greatest value of L corresponds to a value of L/D that is at most 0.45; anda smallest value of L corresponds to a value of L/D that is at least 0.20. 6. The assembly of claim 1, wherein the dimension L varies; andthe dimensional relationship of L/D is based on an average value of L. 7. The assembly of claim 1, wherein the dimension L varies between a top of the inlet portion and a bottom of the inlet portion; andthe dimensional relationship of L/D is based on a value of L near a midpoint between the top and the bottom of the inlet portion. 8. The assembly of claim 1, wherein the leading edges of the fan blades are in a reference plane; andthe dimension L extends along a direction that is perpendicular to the reference plane. 9. The assembly of claim 8, wherein the engine assembly has a central axis;the reference plane is perpendicular to the central axis; andthe dimension L extends along a direction that is parallel to the central axis. 10. The assembly of claim 1, wherein the engine assembly has a central axis;the forward edge on the inlet portion is in a first reference plane;the leading edges of the fan blades are in a second reference plane; andthe dimension L is measured between a first location where the central axis intersects the first reference plane and a second location where the central axis intersects the second reference plane. 11. The assembly of claim 1, wherein the fan is configured to deliver a portion of air into a compressor section and a portion of air into a bypass duct;a bypass ratio which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section being greater than or equal to 8; andthe fan is configured to have a pressure ratio between 1.20 and 1.50 when operating at sea level. 12. The assembly of claim 1, wherein each of the fan blades is a swept fan blade. 13. The assembly of claim 1, comprising a speed change device configured to drive the fan at a speed that is less than an input speed in the speed change device wherein the speed change device is a geared architecture that defines a gear reduction ratio greater than or equal to 2.3. 14. The assembly of claim 1, wherein a fan blade tip speed of each of the fan blades is less than 1150 ft/second. 15. A gas turbine engine assembly, comprising: a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge;a geared architecture configured to drive the fan at a speed that is less than an input speed in the geared architecture;a compressor section;a turbine section configured to drive the compressor section and the geared architecture;an inlet portion forward of the fan, a length of the inlet portion having a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion; andwherein a dimensional relationship of L/D is between 0.2 and 0.45. 16. The gas turbine engine assembly of claim 15, wherein the dimension L varies; andthe dimensional relationship of L/D is based on an average value of L. 17. The gas turbine engine assembly of claim 15, wherein the fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct;a bypass ratio between a volume of air passing to the bypass duct and a volume of air passing into the compressor section is greater than or equal to 8; andthe fan is configured to have a pressure ratio less than 1.50 when operating at sea level. 18. The gas turbine engine assembly of claim 15, wherein the geared architecture defines a gear reduction ratio greater than or equal to 2.3. 19. The gas turbine engine assembly of claim 15, wherein each of the fan blades is a swept fan blade.