At subsonic speeds, blunt noses - both fuselage and airfoil - are good because of the need to maintain attached flow at varying angles of attack.

[![top:zero AoA/cruise, bottom: max AoA for landing/takeoff - 20-30deg][1]][1]


***TOP:** 0 AoA/Cruise
| **BOTTOM:** extreme AoA, 20-30degrees, takeoff/landing* 

If the airflow had to flow over a ridge/point in scenario 2, instead of the smooth curve, flow separation would be more likely. 

But it's not like most airplanes - particularly airliners - fly at AoA beyond 20-30 degrees. At least not without high-lift devices. Am I correct? But on the rounded nose, there are surfaces smoothly curving all the way from 90 degrees! This seems to me like a useless increase in cruise drag.

Would limiting the curvature to the max AoA limit for the aircraft, then terminating at a point, as in the image below, not keep the flow attached throughout the expected AoA range, while producing less drag? At the maximum AoA, the flow over the top of the shape encounters no "ridge" or "point", as it is parallel to the half-angle at the nose. 

[![the nose is now modified so that it comes to a point, with the maximum half-angle at nose limited to the maximum AoA expected for the aircraft(20-30deg?)][2]][2]

***TOP:** less drag is created at cruise
| **BOTTOM:** Flow remains attached at extreme AoA conditions.*


  [1]: https://i.sstatic.net/dzk11.png
  [2]: https://i.sstatic.net/rSkRk.png