PLEASE somebody look at these equations
and tell me where I am going wrong. There must be a mistake in here
somewhere.


*********************************************************************


  CLS
  Weight = 1900       'pounds
  statthrust = 2000   'pounds
  distance = 0        'feet
  FlatPlate = 4       'square feet
  PropEff = .8
  HP = 300         '1 HP = 550 pound foot per second
  FPS = .001
  distance = .001

PRINT "Time     Drag      HP     NetThrust     G's    FPS    MPH   Feet"
PRINT

FOR time = .1 TO 4.6 STEP .1

PRINT USING "###.#"; time;

Drag = FlatPlate * MPH ^ 2 * .0026

PRINT USING "#######.##"; Drag;

HP = HP * (1 - .000003 * distance) 'adjust HP for altitude.

PRINT USING "   #####"; HP;

Thrust = (HP * 550 * PropEff) / FPS

IF Thrust > 2000 THEN Thrust = 2000 'lower limit for  thrust

NetThrust = Thrust - Drag

PRINT USING "#########"; NetThrust;

Gs = NetThrust / Weight
PRINT USING "     ##.##"; Gs;
velincFPS = Gs * 32 * .1

VEL = VEL + velincFPS
PRINT USING "#########"; VEL;
MPH = 60 / 88 * VEL
PRINT USING "######"; MPH;
distance = (VEL * time) + distance
PRINT USING "########"; distance
NEXT

You can only climb straight up for a few seconds so you better
start pitching over right away or its going to hang on the
prop. This program assumes you are going to pitch over right
away. If you don't the velocity will drop to near zero and the
the airplane will stop climbing vertically. It also assumes the prop
pitch is adjusted for maximum thrust at all times.

Top speed will be limited by the rotor tips going supersonic.

Paul Lamar ...No rotor no motor.

The Rotary Engine NewsLetter. Powered by Linux.
ACRE NL web site. http://www.rotaryeng.net
Copyright 1998-2006 All world wide rights reserved.