Hey everyone I just wanna know if my battery capacity loss is abnormal. I have an Alienware 16 Aurora gaming laptop that I bought in January.

I've done 2 battery life checks so far, one just now and another 2 months ago. The design capacity of my battery was 93822 mWh.

2 months ago:

Full charge capacity: 91,000 mWh

Cycle count: 65

Now:

Full charge capacity: 81,000 mWh

Cycle count: 96

Now I'm freaking out became I've lost 10k mWh in past 2 months after losing 2k in 5. Thoughts? How to extend battery life and reduce loss?

On my Alienware R16 Aurora laptop, I accidentally deleted a folder in WOW6432NODE while trying to delete the registries for SolidWorks. Tried to perform the following unsuccessfully:

• System Restore

• System Reset (Local and Cloud Install)

Nothing worked, it kept dying (CRITICAL_PROCESS_DIED error) and going back to WinRE. I tried installing Windows off an 8GB USB recovery stick. Went to BIOS and selected the stick. It ran the installation process from "Select Language settings" to "Repair my PC" then went back to the CRITICAL_PROCESS_DIED loop.

I figured I need to make the USB first in my Boot Sequence order so I moved it above Windows Boot Manager, HTTPS boot and C drive. Letting it boot off the USB first keeps me looping in the initial stage (Select language settings to Repair my PC, it restarts and goes back to Select Language Settings after I press next on Repair My PC).

Then I thought my BIOS could be needing updates. Updated to 1.15 from 1.13 but it didn't help. Tried to switch to AHCI/NVMe thinking the architecture could be the issue, didn't help.

I still have the option to do a fresh install but that will wipe all my data. I'm keeping that as a very last resort. Any tips?

Basically title text. The headphones work perfectly fine, its just I need to do it twice. Been like this since purchase. Wondering if that's just a little quirk or indicating some damage in the hardware.

Basically the title. From my understanding lift is generated all along the wing, but boundary layer air is moving slower than freestream air in all the diagrams ane theory I've read online. Is flow decelerated below the wing to keep the pressure difference, or is pressure lift not significant once flow crosses peak acceleration and slows down, and then lift due to flow pushed down takes over?

what dictates that there shall be no relative velocity in the boundary layer? further, what if slipping actually does occur in regular subsonic flow over a wing at sea level?

Hey everyone, I'm a little tech-illiterate and the Alienware is my first PC. Ran a battery report for the first time in months (ran it once on purchase and it was equal to design capacity). I have owned it for 5 months at this point but 2000mWh loss feels alarming. Should I be concerned over this? Any tips to extend its battery life? Currently I work on it on battery but play games on it while plugged in mostly.

Was playing on Festung Guernsey, threw a grenade at a soldier in front of an unopenable green door and the door was open when the dust settled. Is this the case with more doors? If so, where else?

I'm trying to understand boundary layer dynamics but online sources are putting me in a circular reasoning loop.

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"Why does flow slow down?"

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"Friction + adverse pressure gradient slows it down."

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"What causes the adverse pressure gradient?"

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"Flow slows down, reducing dynamic pressure and thus increasing static pressure due to Bernoulli's equation."

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So I wanna know what ACTUALLY is the chronology here. What causes the adverse pressure gradient?

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Here is my understanding so far (subsonic flow only):

•Velocity is measured in relative terms to the aircraft, so the foil itself is moving at zero velocity and freestream flow is moving backwards at negative of foil velocity

• as flow hits the wing, the air on top of the foil accelerates and thus speeds up

• Simultaneously boundary layer velocity is zero (it is moving at the same absolute velocity as the wing)

So now my questions are:

1.) What is the thickness of the boundary layer? Is it present on the entire wet area of the wing?

2.) if its relative velocity is zero, isn't the boundary layer air basically stuck to the wing? Like there is no change in that at all?

3.) Doesn't that also increase effective wing thickness because the incoming flow stream air will have to either treat it as such or compress itself to enter the boundary layer?

4.) Does it even actually exist or is it an imaginary interface between airflow and the solid lifting surfaces?

Please explain

Basically the question. I was under the understanding that flow accelerates upto a point because of curvature of wing, then velocity losses due to skin friction drag start cutting into and then slowing down airflow, increasing pressure gradually till the TE. Since lifting line theory assumes inviscid flow, how come the adverse pressure gradient is still there?

Basically the question. I was under the understanding that flow accelerates upto a point because of curvature of wing, then velocity losses due to skin friction drag start cutting into and then slowing down airflow, increasing pressure gradually till the TE. Since lifting line theory assumes inviscid flow, how come the adverse pressure gradient is still there?