RANDOM RANTS XLVI: Slightly More Than a Month-ly Edition #1

[aimeeandbeatles]

Anytime. If you do not have an active subscription for your antivirus, I suggest buying one. Absent that you can get Microsoft Security Essentials - a free full antivirus from MS. It doesn't have the bells and whistles of a paid subscription but it's free, effective and always up-to-date. That should stop further malware attacks.

I used to recommend AVG; it's become something of a pain in the last while though, so my recommendation has switched to Microsoft Security Essentials. For a secondary or on-demand, you still can't beat MalwareBytes Anti-Malware.

 

[Mathalamus]

I used to recommend AVG; it's become something of a pain in the last while though, so my recommendation has switched to Microsoft Security Essentials. For a secondary or on-demand, you still can't beat MalwareBytes Anti-Malware.

i recommend MSSE as well, but avast is good as well. i dont use any anti virus since it became clear i only catch viruses or malware from stupid actions only.

 

[cardgame]

Malwarebytes is the bomb.

 

[hobbsyoyo]

Wife: Why aren't you home yet?
Me:

Spoiler :

APPENDIX B
EQUATIONS 




(i) Thrust Equation T= c_1+ c_2 V+c_3 V^2+c_4 V^3 Example:
T =(0.4672) + (-0.0036)*(19.0889)+(-0.0002)*(19.0889)2+(0.0000001)*(19.0889)3 ; T = 0.3263 lb
Where V=Takeoff Velocity and c_1, etc. are the values listed in the equation. The same format is used in the following equations.
(ii) Fuselage Equation D_f=d_1+d_2 V+d_3 V^2 Example:
Df = (-0.0033) +(-0.0001)*(19.0889)+(0.0002)*(19.0889)2;Df =0.06768 lb

(iii) Wheel Tractive Force WT= F_max (V<2) Example:
WT = 0.5 lb
WT= P/V (V>=2)
Example:
WT = (1)/(19.0889) = 0.05239 lb

(iv) Taylor Series &#8721;_(n=0)^&#8734;&#9618;&#12310;(f^((n) ) (a))/n!(x-a)^n &#12311;

(v) Wing Drag D_w=1/2 &#961;V^2 S(C_do+&#8709;(C_L^2)/&#960;eAR) Example:
Dw = (1/2)*(.0023081)*(19.0889)2*(4.1667)(.015+(.777)*(.5742/&#960;*(.879)*(6))); Dw = 0.05336 lb
Where phi (&#8709 is the ground effect force, AR is the Aspect Ratio and C_L^2 is the lift coefficient.

(vi) Rolling Resistance S_g= W/(&#963;SC_L )(T/W )^(-1) 1/(g&#961;_0 ) Example:
Sg = (10)*(0.05)-1*(1/(32.2*.0023081))
Sg = 0.014571

(vii) Normal Force R= &#956;(W-1/2 &#961;V^2 SC_Lo) Example:
R = (.01)(1 &#8211; (.5)*(.0023081)*(19.0889)2*(4.1667)*(.574)); R =-0.000057512 lb
Where S is planform wing area (b*c) and C_Lo is the section lift coefficient.

(viii) Wing Loading WL=W/S
Example:
WL = (1)/(4.1667); WL = .239998







APPENDIX C
SOURCE CODE
&#8195;
#include <cmath>
#include <iostream>

using namespace std;

int main()
{
float weight=1.00, span=5.00, chord=.83333, clalpha=.082, oswald=.879, mu=.01, parasitedrag=.015, zerolift=-5, takeoffangle=2;
float density=.0023081, gravity=32.2, wingheight=.583333, forcemax=.5, velocity=0.0, position=0.0, time=0.0;
float timestep, c1=.4672, c2=-.0036, c3=-.0002, c4=.0000001, d1=-.0033, d2=-.0001, d3=.0002, power=1.00, reactionforce;
float tractiveforce, thrust, fuselagedrag, aspectratio, surfacearea, phi, clnaught, wingdrag, derivative;
char crepeat;

do
{

cout << "This program will compute the estimated take-off distance of your vehicle with following assumptions and parameters\n";
cout << "Vehicle weight =" <<weight <<" lb, Wing span =" <<span<<" ft, Chord =" <<chord<<" ft\n";
cout << "Finite lift slope = " <<clalpha<<" per degree, Oswald efficiency factor "<<oswald<<", Friction coefficient, mu = "<<mu<<" \n";
cout << "Parasite drag coefficient = "<<parasitedrag<<", Zero lift AoA = "<<zerolift<<" degrees, Take-off AoA = "<<takeoffangle<<" \n";
cout << "Enter the time step you wish to use for this calculation.\n";
cin >> timestep;


aspectratio = (span*span)/(span*chord);
clnaught = (clalpha)*(takeoffangle-zerolift);
surfacearea = span*chord;
phi = (((16*wingheight)/span)*((16*wingheight)/span))/(1+((16*wingheight)/span)*((16*wingheight)/span));

float takeoffvelocity;

takeoffvelocity = sqrt((2*weight)/(density*surfacearea*clnaught));
do
{
thrust=(c1+c2*velocity+c3*velocity*velocity+c4*velocity*velocity*velocity);
fuselagedrag=(d1+d2*velocity+d3*velocity*velocity);
wingdrag=.5*density*velocity*velocity*surfacearea*(parasitedrag+phi*(clnaught*clnaught/(3.14159265*oswald*aspectratio)));
reactionforce=mu*(weight-(.5*density*velocity*velocity*surfacearea*clnaught));

if(velocity>=2.00)
{
tractiveforce=(power/velocity);
}
else
{
tractiveforce=forcemax;
}
if(velocity<=2.00)
{
derivative=c2+2*c3*velocity+3*c4*velocity*velocity-(d2+2*d3*velocity)-(density*surfacearea*velocity)*(parasitedrag+phi*((clnaught*clnaught)/(3.14159265*oswald*aspectratio)))+(mu*density*surfacearea*clnaught*velocity);
}
else
{
derivative=c2+2*c3*velocity+3*c4*velocity*velocity-(d2+2*d3*velocity)-(density*surfacearea*velocity)*(parasitedrag+phi*((clnaught*clnaught)/(3.14159265*oswald*aspectratio)))+(mu*density*surfacearea*clnaught*velocity)-(1/(velocity*velocity));
}
position=position+(timestep*velocity)+(timestep*timestep/2.0)*(gravity/weight)*(thrust - fuselagedrag - wingdrag - reactionforce + tractiveforce) + (timestep*timestep*timestep/6.0)*(gravity/weight)*derivative*(gravity/weight)*(thrust - fuselagedrag - wingdrag - reactionforce + tractiveforce);
velocity=velocity + (gravity/weight)*timestep*(thrust + tractiveforce - fuselagedrag - wingdrag - reactionforce) + (gravity/weight)*derivative*(timestep*timestep)/2.00*(gravity/weight)*(thrust+tractiveforce-fuselagedrag-wingdrag-reactionforce);
time=time+timestep;
cout << "Velocity, take off time and runway distance required equals " << velocity <<", "<< time <<", " << position<<"\n";

}while(velocity<=takeoffvelocity);

cout << "Again? (Enter Y or y)";
cin >> crepeat;
position=0.0;
time=0.0;
velocity=0.0;
}while(crepeat=='Y'||crepeat=='y');

return 0;
}
&#8195;




APPENDIX D
PROGRAM RESULTS&#8195;




VELOCITY TIME GROUND ROLL
2.96442 .1 0.152643
5.17401 .2 0.563687
7.05352 .3 1.17692
8.75058 .4 1.96839
10.3119 .5 2.92254
11.7586 .6 4.02696
13.1022 .7 5.27082
14.3503 .8 6.64422
15.6197 .9 8.29354
16.6847 1.0 9.90945
17.5745 1.1 11.4516
18.4907 1.2 13.2555
19.0889 1.27 14.571

FML

Edit: But I am one step closer to world domination. My drone flies dagnabit.

 

[Takhisis]

City got flash flooded yesterday (150-175mm in 2-3 hours) and a large part of our neighbourhood was turned into a gigantic lake of about 1m. depth. We were a full day without power (or water, because the pumps don't work) and most of the shops and every single ground floor in the area is ruined, I hope they all have insurance.
The stream river lake stopped about one block down the street. Huzzah!
Still, communications are cracked up, most shops around are still taking out wrecked stuff to dry, most basements are still flooded, the local library has lost most of their books, etc. etc. etc.

But, hey, I'm alive! Thank God.

On a completely unrelated note, Larisa Riquelme says she won't do any more nude photoshoots.
What's Quackers doing in this pic?

With your new avatar, I keep thinking you are CivGeneral.

Well that is amusing. Perhaps I should change it to something else.

I want to see that avatar!!

Wife: Why aren't you home yet?
Me: <incredibly long meaningless jargon>

Sound like what any husband does.

 

[hobbsyoyo]

I am glad you are safe, sound and capable of belittling weeks of hard work on the interwebs.

 

[Takhisis]

Check the pics:
http://www.lanacion.com.ar//1568990-furioso-temporal-6-muertos-miles-de-evacuados-y-450000-afectados

(scroll a bit down the page, I'll check to see if the Beeb has something).

 

[Kaitzilla]

Wife: Why aren't you home yet?
Me:

Spoiler :

APPENDIX B
EQUATIONS&#8195;




(i) Thrust Equation T= c_1+ c_2 V+c_3 V^2+c_4 V^3 Example:
T =(0.4672) + (-0.0036)*(19.0889)+(-0.0002)*(19.0889)2+(0.0000001)*(19.0889)3 ; T = 0.3263 lb
Where V=Takeoff Velocity and c_1, etc. are the values listed in the equation. The same format is used in the following equations.
(ii) Fuselage Equation D_f=d_1+d_2 V+d_3 V^2 Example:
Df = (-0.0033) +(-0.0001)*(19.0889)+(0.0002)*(19.0889)2;Df =0.06768 lb

(iii) Wheel Tractive Force WT= F_max (V<2) Example:
WT = 0.5 lb
WT= P/V (V>=2)
Example:
WT = (1)/(19.0889) = 0.05239 lb

(iv) Taylor Series &#8721;_(n=0)^&#8734;&#9618;&#12310;(f^((n) ) (a))/n!(x-a)^n &#12311;

(v) Wing Drag D_w=1/2 &#961;V^2 S(C_do+&#8709;(C_L^2)/&#960;eAR) Example:
Dw = (1/2)*(.0023081)*(19.0889)2*(4.1667)(.015+(.777)*(.5742/&#960;*(.879)*(6))); Dw = 0.05336 lb
Where phi (&#8709 is the ground effect force, AR is the Aspect Ratio and C_L^2 is the lift coefficient.

(vi) Rolling Resistance S_g= W/(&#963;SC_L )(T/W )^(-1) 1/(g&#961;_0 ) Example:
Sg = (10)*(0.05)-1*(1/(32.2*.0023081))
Sg = 0.014571

(vii) Normal Force R= &#956;(W-1/2 &#961;V^2 SC_Lo) Example:
R = (.01)(1 – (.5)*(.0023081)*(19.0889)2*(4.1667)*(.574)); R =-0.000057512 lb
Where S is planform wing area (b*c) and C_Lo is the section lift coefficient.

(viii) Wing Loading WL=W/S
Example:
WL = (1)/(4.1667); WL = .239998







APPENDIX C
SOURCE CODE
&#8195;
#include <cmath>
#include <iostream>

using namespace std;

int main()
{
float weight=1.00, span=5.00, chord=.83333, clalpha=.082, oswald=.879, mu=.01, parasitedrag=.015, zerolift=-5, takeoffangle=2;
float density=.0023081, gravity=32.2, wingheight=.583333, forcemax=.5, velocity=0.0, position=0.0, time=0.0;
float timestep, c1=.4672, c2=-.0036, c3=-.0002, c4=.0000001, d1=-.0033, d2=-.0001, d3=.0002, power=1.00, reactionforce;
float tractiveforce, thrust, fuselagedrag, aspectratio, surfacearea, phi, clnaught, wingdrag, derivative;
char crepeat;

do
{

cout << "This program will compute the estimated take-off distance of your vehicle with following assumptions and parameters\n";
cout << "Vehicle weight =" <<weight <<" lb, Wing span =" <<span<<" ft, Chord =" <<chord<<" ft\n";
cout << "Finite lift slope = " <<clalpha<<" per degree, Oswald efficiency factor "<<oswald<<", Friction coefficient, mu = "<<mu<<" \n";
cout << "Parasite drag coefficient = "<<parasitedrag<<", Zero lift AoA = "<<zerolift<<" degrees, Take-off AoA = "<<takeoffangle<<" \n";
cout << "Enter the time step you wish to use for this calculation.\n";
cin >> timestep;


aspectratio = (span*span)/(span*chord);
clnaught = (clalpha)*(takeoffangle-zerolift);
surfacearea = span*chord;
phi = (((16*wingheight)/span)*((16*wingheight)/span))/(1+((16*wingheight)/span)*((16*wingheight)/span));

float takeoffvelocity;

takeoffvelocity = sqrt((2*weight)/(density*surfacearea*clnaught));
do
{
thrust=(c1+c2*velocity+c3*velocity*velocity+c4*velocity*velocity*velocity);
fuselagedrag=(d1+d2*velocity+d3*velocity*velocity);
wingdrag=.5*density*velocity*velocity*surfacearea*(parasitedrag+phi*(clnaught*clnaught/(3.14159265*oswald*aspectratio)));
reactionforce=mu*(weight-(.5*density*velocity*velocity*surfacearea*clnaught));

if(velocity>=2.00)
{
tractiveforce=(power/velocity);
}
else
{
tractiveforce=forcemax;
}
if(velocity<=2.00)
{
derivative=c2+2*c3*velocity+3*c4*velocity*velocity-(d2+2*d3*velocity)-(density*surfacearea*velocity)*(parasitedrag+phi*((clnaught*clnaught)/(3.14159265*oswald*aspectratio)))+(mu*density*surfacearea*clnaught*velocity);
}
else
{
derivative=c2+2*c3*velocity+3*c4*velocity*velocity-(d2+2*d3*velocity)-(density*surfacearea*velocity)*(parasitedrag+phi*((clnaught*clnaught)/(3.14159265*oswald*aspectratio)))+(mu*density*surfacearea*clnaught*velocity)-(1/(velocity*velocity));
}
position=position+(timestep*velocity)+(timestep*timestep/2.0)*(gravity/weight)*(thrust - fuselagedrag - wingdrag - reactionforce + tractiveforce) + (timestep*timestep*timestep/6.0)*(gravity/weight)*derivative*(gravity/weight)*(thrust - fuselagedrag - wingdrag - reactionforce + tractiveforce);
velocity=velocity + (gravity/weight)*timestep*(thrust + tractiveforce - fuselagedrag - wingdrag - reactionforce) + (gravity/weight)*derivative*(timestep*timestep)/2.00*(gravity/weight)*(thrust+tractiveforce-fuselagedrag-wingdrag-reactionforce);
time=time+timestep;
cout << "Velocity, take off time and runway distance required equals " << velocity <<", "<< time <<", " << position<<"\n";

}while(velocity<=takeoffvelocity);

cout << "Again? (Enter Y or y)";
cin >> crepeat;
position=0.0;
time=0.0;
velocity=0.0;
}while(crepeat=='Y'||crepeat=='y');

return 0;
}
&#8195;




APPENDIX D
PROGRAM RESULTS&#8195;




VELOCITY TIME GROUND ROLL
2.96442 .1 0.152643
5.17401 .2 0.563687
7.05352 .3 1.17692
8.75058 .4 1.96839
10.3119 .5 2.92254
11.7586 .6 4.02696
13.1022 .7 5.27082
14.3503 .8 6.64422
15.6197 .9 8.29354
16.6847 1.0 9.90945
17.5745 1.1 11.4516
18.4907 1.2 13.2555
19.0889 1.27 14.571

FML

Edit: But I am one step closer to world domination. My drone flies dagnabit.

Holy moly. I will pray for you!

I'd say check for errors by comparing an estimate of what's reasonable to the results, but look at all that stuff. Where'd even start?


Maybe simplify the problem. Tear off the wings, upgrade the engine to a rocket, point it vertical, horizontal takeoff distance now = 0.

 

[Takhisis]

It's on the Beeb, but only a small note.

 

[hobbsyoyo]

@Kaitzilla -

It runs fine, I was actually done with coding a couple of weeks back but out TA decided in a moment of brilliance to not explicitly state project goals in the required deliverables memo he sent out (and in some cases didn't even imply them) leaving us to discover them on our own god knows how. And part of this course is to focus on how to write good memos!

Tl;dr
I wrote the code, it works but I had to go back and run it under different conditions he hadn't told us about and then write up the report. I went to bed at 4am and was up at 7.

 

[aimeeandbeatles]

Ran out of money again. My mother's looking for stuff to sell.

My stuff, to be more precise.

WITHOUT ASKING ME.

Seriously, how about all that cooking equipment crap she bought and never even took out of the box? Oh, of course not, it's hers, after all.....

 

[Takhisis]

That's theft.

 

[aimeeandbeatles]

I know.

This morning I caught her digging through my games to sell online.

"But you can just buy them on the Steam thing again!"

"NO."

 

[Takhisis]

But then you'd be at 0 again. Sell something, buy it again&#8230; wait, used games might fetch even less. Really, get a safe with a strong lock.

 

[aimeeandbeatles]

But then you'd be at 0 again. Sell something, buy it again… wait, used games might fetch even less. Really, get a safe with a strong lock.

She fails at financial management

 

[Takhisis]

Alternatively -or, more likely, complementarily- she doesn't give a damn about your rights.

 

[PlutonianEmpire]

Can't someone just call the cops or something?

 

[ace99]

If you're 18+ move out. Less awkward than calling the cops on your mother.

 

[W|M]

Aimee is disabled and unemployed, it's not exactly easy for her to move out.

 

[Takhisis]

If you're 18+ move out. Less awkward than calling the cops on your mother.

Aimee is disabled and unemployed, it's not exactly easy for her to move out.

You see? You answer yourself.