Re: Force instead of lift
"Bill Galbraith" <[email protected]> Sat, 1 Oct 2011 08:27:49 -0400
| Newsgroups | gmane.games.flightgear.flightmodel |
|---|---|
| Message-ID | <D47BAAD90C154A94B1F7CA1757517CFE@Dell755> |
This is a multi-part message in MIME format. ------=_NextPart_000_001F_01CC8014.01A4CAA0 Content-Type: text/plain; charset="us-ascii" Content-Transfer-Encoding: 7bit In this case, the Cl is roll moment coefficient, not CL, the lift coefficient The attached file shows a new format for JSBSim files that I came up with. It works just as well as the older format, but the formulation of the coefficients more closely matches classical aerodynamic textbook equation buildup. Feel free to use this, or the older format. They are both equally valid. Bill > -----Original Message----- > From: Oleksiy Frolov [mailto:[email protected]] > Sent: Saturday, October 01, 2011 12:03 AM > To: Flight dynamics model discussions > Subject: Re: [Flightgear-flightmodel] Force instead of lift > > Hello Bill > > This is a good suggestion, thank you. > > I understand about calculating 2(4) different CL-s. > > Do I also understand correctly we will than have use > something you guys did to the flaps once: > > <axis name="ROLL"> > ................. > <function name="aero/coefficient/CldF3"> > <description> > Roll Moment Coefficient due to Asymetrical > Fowler Flaps Deflection > calculated as difference between left and > right flap lift coef, > times distance from centerline to MAC of surface. > </description> > <product> > <value> 21.28</value> > <difference> > <property>aero/coefficient/CLdF3R</property> > <property>aero/coefficient/CLdF3L</property> > </difference> > </product> > </function> > > > in order to calculate the moments due to difference in > individual CLs ? > > With best regards, > Oleksiy Frolov > > > > > > >> -----Original Message----- > >> From: Oleksiy Frolov [mailto:[email protected]] > >> Sent: Friday, September 30, 2011 3:43 PM > >> To: [email protected] > >> Subject: [Flightgear-flightmodel] Force instead of lift > >> > >> Hello > >> > >> I am trying to simulate the effects of the differential > wing lift. > >> Such as single wing stall due to the propwash loss at a low speed, > >> and the effect of the icing on a single wing (which can > happen during > >> a deicing failure on that wing). All of these are important > >> aerodynamic effects. > >> > >> Now, we know we only have one wing in jsbsim currently, not 2. My > >> idea is therefor to try using 2 <force> records to > simulate the wings > >> separately, instead of the usual CL record. > >> This however would require some kind of algorithm to > define how the > >> force origin moves to overlay with center of lift for each wing, > >> which is probably not an easy task > >> > >> I was wondering if anyone have tried a similar approach > before, and > >> if this problem pechaps has an easier solution ? > >> > >> Thank you > >> > >> regards, > >> Oleksiy Frolov > >> > > > > > > No reason that you couldn't build this inside of the > existing JSBSim > > format without using the external forces. Divide your wing into > > panels, maybe (on each side) one that is influenced by the > propeller > > slipstream, one not. > > Sum > > all of your lifts to apply them at the aero reference > point. So with a > > two engine aircraft, you might have a total of four panels, two per > > wing half, one inboard in the slipstream, one outboard in > clean air. A > > mismatch of forces left/right would normally shift the aero > reference > > point left or right, but that can be resolved with a moment. > > > > You have a couple advantages doing this. A force at a distance is a > > moment, so if the outer panels are experiencing different > lift forces, > > that lift times its arm creates a moment. If the aircraft > is rolling, > > each wing sees a different angle of attack, and therefore different > > lift. This is usually handled other ways, but your method has the > > advantage of spinning properly. > > There are disadvantages, though. > > > > If you are going to that trouble, you might consider > keeping the flaps > > and ailerons seperate as well, unless the actuator mechanism is > > guaranteed to never give you different flap or aileron angles. > > > > Bill > > > > > > > ---------------------------------------------------------------------- > > -------- All of the data generated in your IT infrastructure is > > seriously valuable. > > Why? It contains a definitive record of application performance, > > security threats, fraudulent activity, and more. Splunk takes this > > data and makes sense of it. IT sense. And common sense. > > http://p.sf.net/sfu/splunk-d2dcopy2 > > _______________________________________________ > > Flightgear-flightmodel mailing list > > [email protected] > > https://lists.sourceforge.net/lists/listinfo/flightgear-flightmodel > > > > > > -------------------------------------------------------------- > ---------------- > All of the data generated in your IT infrastructure is > seriously valuable. > Why? It contains a definitive record of application > performance, security threats, fraudulent activity, and more. > Splunk takes this data and makes sense of it. IT sense. And > common sense. > http://p.sf.net/sfu/splunk-d2dcopy2 > _______________________________________________ > Flightgear-flightmodel mailing list > [email protected] > https://lists.sourceforge.net/lists/listinfo/flightgear-flightmodel ------=_NextPart_000_001F_01CC8014.01A4CAA0 Content-Type: text/xml; name="Citation_aero.xml" Content-Transfer-Encoding: quoted-printable Content-Disposition: attachment; filename="Citation_aero.xml" <?xml version=3D"1.0"?> <!-- ****************** IMPORTANT NOTICES ********************** This file was generated by Datcom+ Pro, a superset of=20 the USAF Digital DATCOM program. This file is considered an intermediary file in the=20 DATCOM/JSBSim process. This file may be overwritten without warning, so any changes that you make in here may be lost. If you intend to use this file as it is and modify it, make sure that you take the necessary precautions to prevent it=20 from being overwritten, like renaming it. *********************************************************** DISCLAIMER REQUIRED BY HQ USAF FOR PUBLIC RELEASE APPROVAL THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION IS RELEASED "AS IS". THE U.S. GOVERNMENT MAKES NO WARRANTY OF ANY KIND, EXPRESS OR IMPLIED, CONCERNING THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION, INCLUDING, WITHOUT LIMITATION, ANY WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE. IN NO EVENT WILL THE U.S. GOVERNMENT BE LIABLE FOR ANY DAMAGES, INCLUDING LOST PROFITS, LOST SAVINGS OR OTHER INCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING OUT OF THE=20 USE, OR INABILITY TO USE, THIS SOFTWARE OR ANY ACCOMPANYING DOCUMENTATION, EVEN IF INFORMED IN ADVANCE OF THE POSSIBILITY OF SUCH DAMAGES. *********************************************************** --> <!-- = ********************************************************************** AERODYNAMICS = *******************************************************************--> <aerodynamics> <!-- *************************=20 Sign Conventions =20 *************************=20 Control displacements Stick FWD + / Aft - Stick Left + / Right - Wheel CCW + / CW - Pedal Left + / Right - Elevator trim Nose Up + / Nose down - Surfaces Elevator TED + / TEU - R Ail TED + / TEU - L Ail TED + / TEU - Rudder TEL + / TER - F&M, Accel, Rates, Displacements Pitch Up + / Down - Roll Rgt + / Left - Yaw Rgt + / Left - Other Alpha Up + / Down - Beta Wind in right ear + / Wind in left ear - Slip Ball right of center + / left of center - --> <!-- **************************************=20 ASSUMPTIONS AND LIMITATIONS There is no interaction between deflected surfaces modeled so there is no change in elevator effects with the flaps deflected, for example. Terms known to be missing from DATCOM: Ground effects Cyr, dCY_Rud, dCY_Ail, dCl_Rud, dCN_Rud ************************************** --> <!-- The following functions provide properties in different units = than are native to JSBSim --> <function name=3D"attitude/pitch-deg"> <description>Pitch angle in degrees</description> <product> <property>attitude/pitch-rad</property> <value>57.29577951</value> </product> </function> <function name=3D"attitude/roll-deg"> <description>Roll angle in degrees</description> <product> <property>attitude/roll-rad</property> <value>57.29577951</value> </product> </function> <function name=3D"attitude/heading-true-deg"> <description>Roll angle in degrees</description> <product> <property>attitude/heading-true-rad</property> <value>57.29577951</value> </product> </function> <function name=3D"velocities/q-deg_sec"> <description>Pitch rate in degrees per sec</description> <product> <property>velocities/q-aero-rad_sec</property> <value>57.29577951</value> </product> </function> <function name=3D"velocities/p-deg_sec"> <description>Pitch rate in degrees per sec</description> <product> <property>velocities/p-aero-rad_sec</property> <value>57.29577951</value> </product> </function> <function name=3D"velocities/r-deg_sec"> <description>Pitch rate in degrees per sec</description> <product> <property>velocities/r-aero-rad_sec</property> <value>57.29577951</value> </product> </function> <!-- = **********************************************************************=20 LIFT FORCE = ********************************************************************** = --> <function name=3D"aero/coefficient/CL_wbh"> <description> Lift coefficient due to wing, body, and horizontal tail </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 -.0313 .0000 .1609 2.0000 .3557 4.0000 .5533 8.0000 .9495 9.0000 1.0380 10.0000 1.1171 11.0000 1.1898 12.0000 1.2555 13.0000 1.3124 14.0000 1.3632 15.0000 1.3922 16.0000 1.3403 </tableData> </table> </function> <function name=3D"aero/derivative/CLq-per_rad"> <description> Lift coefficient derivative due to pitch rate, per rad </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 9.2943 16.0000 9.2943 </tableData> </table> </function> <function name=3D"aero/derivative/CLadot-per_rad"> <description> Lift coefficient derivative due to AOA rate, per rad Important contributor to short period damping </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 2.4726 .0000 2.5178 2.0000 2.6025 4.0000 2.6508 8.0000 2.4940 9.0000 2.3980 10.0000 2.2089 11.0000 1.8322 12.0000 1.4917 13.0000 1.2549 14.0000 .7177 15.0000 -.2527 16.0000 -.8221 </tableData> </table> </function> <function name=3D"aero/coefficient/dCL_Flap"> <description> Lift coefficient increment due to flap deflection Positive surface deflection is trailing edge down. </description> <table> <independentVar lookup=3D"row"> fcs/flap-pos-deg = </independentVar> <tableData> .0000 .0000 15.0000 .2360 30.0000 .4337 40.0000 .5045 </tableData> </table> </function> <function name=3D"aero/coefficient/dCL_Elev"> <description> Lift coefficient increment due to elevator deflection. Positive surface deflection is trailing edge down. </description> <table> <independentVar lookup=3D"row"> fcs/elevator-pos-deg = </independentVar> <tableData> -20.0000 -.1583 -15.0000 -.1501 -10.0000 -.1059 -5.0000 -.0529 .0000 .0001 5.0000 .0529 10.0000 .1059 13.0000 .1349 16.0000 .1562 </tableData> </table> </function> <function name=3D"aero/coefficient/dCL_Power"> <description> Lift coefficient increment due to thrust effects </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <independentVar lookup=3D"column"> = propulsion/total-thrust-coefficient </independentVar> <tableData> .0000 .1000 .2000 .3000 -2.0000 .0014 .0014 .0014 .0014 .0000 .0097 .0167 .0237 .0306 2.0000 .0172 .0311 .0451 .0590 4.0000 .0230 .0439 .0648 .0857 8.0000 .0280 .0627 .0974 .1322 9.0000 .0276 .0658 .1039 .1421 10.0000 .0266 .0682 .1098 .1513 11.0000 .0250 .0699 .1149 .1599 12.0000 .0227 .0711 .1195 .1679 13.0000 .0200 .0718 .1235 .1753 14.0000 .0168 .0719 .1270 .1822 15.0000 .0132 .0716 .1301 .1886 16.0000 .0092 .0711 .1329 .1947 </tableData> </table> </function> <axis name=3D"LIFT"> <function name=3D"aero/force/lift-lbs"> <description> Lift force =3D ( CL_wbh + CLq*q*cbar/(2*V) + = CLadot*adot*cbar/(2*V) + dCL_Flap + dCL_Elev + dCL_Power ) * q_bar * wing area </description> <product> <sum> <property> aero/coefficient/CL_wbh </property> <product> <property> aero/derivative/CLq-per_rad </property> <property> velocities/q-rad_sec </property> <property> aero/ci2vel </property> </product> <product> <property> aero/derivative/CLadot-per_rad </property> <property> aero/alphadot-rad_sec </property> <property> aero/ci2vel </property> </product> <property> aero/coefficient/dCL_Flap </property> <property> aero/coefficient/dCL_Elev </property> <property> aero/coefficient/dCL_Power </property> </sum> <property> aero/qbar-psf </property> <property> metrics/Sw-sqft </property> </product> </function> </axis> <!-- = **********************************************************************=20 DRAG FORCE = ********************************************************************** = --> <function name=3D"aero/coefficient/CD_wbh"> <description> Drag coefficient due to wing, body, and horizontal tail Main contributor to Phugoid damping: greater Cd, better damping </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 .0154 .0000 .0165 2.0000 .0210 4.0000 .0295 8.0000 .0582 9.0000 .0668 10.0000 .0759 11.0000 .0856 12.0000 .0954 13.0000 .1052 14.0000 .1152 15.0000 .1232 16.0000 .1233 </tableData> </table> </function> <function name=3D"aero/coefficient/dCD_Flap"> <description> Drag coefficient increment due to flap deflection Positive surface deflection is trailing edge down. </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <independentVar lookup=3D"column"> fcs/flap-pos-deg = </independentVar> <tableData> .0000 15.0000 30.0000 40.0000 -2.0000 .0000 .0006 .0078 .0119 .0000 .0000 .0041 .0142 .0193 2.0000 .0000 .0076 .0206 .0268 4.0000 .0000 .0111 .0271 .0343 8.0000 .0000 .0181 .0399 .0492 9.0000 .0000 .0198 .0431 .0530 10.0000 .0000 .0216 .0463 .0567 11.0000 .0000 .0233 .0495 .0604 12.0000 .0000 .0251 .0527 .0642 13.0000 .0000 .0268 .0560 .0679 14.0000 .0000 .0286 .0592 .0716 15.0000 .0000 .0303 .0624 .0754 16.0000 .0000 .0321 .0656 .0791 </tableData> </table> </function> <function name=3D"aero/coefficient/dCD_Elev"> <description> Drag coefficient increment due to elevator deflection. Positive surface deflection is trailing edge down. </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <independentVar lookup=3D"column"> fcs/elevator-pos-deg = </independentVar> <tableData> -20.0000 -15.0000 -10.0000 -5.0000 = .0000 5.0000 10.0000 13.0000 16.0000 -2.0000 .0110 .0101 .0057 .0020 = .0000 -.0003 .0011 .0026 .0040 .0000 .0094 .0085 .0046 .0014 = .0000 .0003 .0022 .0040 .0056 2.0000 .0078 .0070 .0035 .0009 = .0000 .0008 .0033 .0053 .0072 4.0000 .0062 .0055 .0025 .0004 = .0000 .0013 .0043 .0066 .0087 8.0000 .0032 .0027 .0005 -.0006 = .0000 .0023 .0063 .0092 .0117 9.0000 .0024 .0019 -.0001 -.0009 = .0000 .0026 .0069 .0099 .0125 10.0000 .0015 .0011 -.0007 -.0012 = .0000 .0029 .0074 .0107 .0134 11.0000 .0006 .0002 -.0013 -.0015 = .0000 .0032 .0081 .0115 .0143 12.0000 -.0005 -.0008 -.0020 -.0018 = .0000 .0035 .0088 .0124 .0153 13.0000 -.0016 -.0019 -.0027 -.0022 = .0000 .0039 .0095 .0133 .0164 14.0000 -.0028 -.0030 -.0035 -.0026 = .0000 .0043 .0103 .0143 .0176 15.0000 -.0042 -.0043 -.0045 -.0031 = .0000 .0048 .0112 .0155 .0190 16.0000 -.0059 -.0059 -.0056 -.0036 = .0000 .0053 .0124 .0170 .0206 </tableData> </table> </function> <axis name=3D"DRAG"> <function name=3D"aero/force/drag-lbs"> <description> Drag force =3D ( CD_wbh + dCD_Flap + dCD_Elev ) * q_bar * wing area </description> <product> <sum> <property> aero/coefficient/CD_wbh </property> <property> aero/coefficient/dCD_Flap </property> <property> aero/coefficient/dCD_Elev </property> </sum> <property> aero/qbar-psf </property> <property> metrics/Sw-sqft </property> </product> </function> </axis> <!-- = **********************************************************************=20 SIDE FORCE = ********************************************************************** = --> <function name=3D"aero/derivative/CYbeta-per_rad"> <description> Side force coefficient derivative due to sideslip, per rad Contributes to damping of dutch roll mode </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 -.7503 16.0000 -.7503 </tableData> </table> </function> <function name=3D"aero/derivative/CYp-per_rad"> <description> Side Force coefficient derivative due to roll rate, per rad </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 -.0884 .0000 -.0965 2.0000 -.1050 4.0000 -.1137 8.0000 -.1312 9.0000 -.1341 10.0000 -.1365 11.0000 -.1382 12.0000 -.1392 13.0000 -.1391 14.0000 -.1405 15.0000 -.1862 16.0000 -.0434 </tableData> </table> </function> <function name=3D"aero/derivative/CYr-per_rad"> <description> Side Force coefficient derivative due to yaw rate DATCOM does not calculate this term Effect is small </description> <table> <independentVar lookup=3D"row"> velocities/r-rad_sec = </independentVar> <tableData> -2.0000 .0000 .0000 .0000 2.0000 .0000 </tableData> </table> </function> <function name=3D"aero/coefficient/dCY_Rud"> <description> Side Force coefficient increment due to rudder DATCOM does not calculate this term </description> <table> <independentVar lookup=3D"row"> fcs/rudder-pos-deg = </independentVar> <tableData> -30.0000 .0000 .0000 .0000 30.0000 .0000 </tableData> </table> </function> <function name=3D"aero/coefficient/dCY_Ail"> <description> Side Force coefficient increment due to plain flap aileron DATCOM does not calculate this term Usually neglected as small </description> <table> <independentVar lookup=3D"row"> fcs/total-aileron-pos-deg = </independentVar> <tableData> -64.0000 .0000 .0000 .0000 64.0000 .0000 </tableData> </table> </function> <axis name=3D"SIDE"> <function name=3D"aero/force/side-lbs"> <description> Side force =3D ( CYbeta*beta + CYp*p*b/(2*V) + CYr*r*b/(2*V) = + CYdRud + CYdAil ) * q_bar * wing area </description> <product> <sum> <product> <property> aero/derivative/CYbeta-per_rad </property> <property> aero/beta-rad </property> </product> <product> <property> aero/derivative/CYp-per_rad </property> <property> velocities/p-rad_sec </property> <property> aero/bi2vel </property> </product> <product> <property> aero/derivative/CYr-per_rad </property> <property> velocities/r-rad_sec </property> <property> aero/bi2vel </property> </product> <property> aero/coefficient/dCY_Rud </property> <property> aero/coefficient/dCY_Ail </property> </sum> <property> aero/qbar-psf </property> <property> metrics/Sw-sqft </property> </product> </function> </axis> <!-- = **********************************************************************=20 ROLL MOMENT = ********************************************************************** = --> <function name=3D"aero/derivative/Clbeta-per_rad"> <description> Roll moment coefficient derivative due to sideslip Decrease of Clb to small negative value improves dutch roll = damping High Positive value leads to excessive spiral instability </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 -.1362 .0000 -.1301 2.0000 -.1240 4.0000 -.1177 8.0000 -.1052 9.0000 -.1023 10.0000 -.0993 11.0000 -.0964 12.0000 -.0936 13.0000 -.0909 14.0000 -.0882 15.0000 -.0857 16.0000 -.0842 </tableData> </table> </function> <function name=3D"aero/derivative/Clp-per_rad"> <description> Roll moment coefficient derivative due to roll rate Clp alone determines damping-in-roll characteristics </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 -.4558 .0000 -.4649 2.0000 -.4725 4.0000 -.4696 8.0000 -.3796 9.0000 -.3396 10.0000 -.2962 11.0000 -.2478 12.0000 -.1947 13.0000 -.1484 14.0000 -.0469 15.0000 .3125 16.0000 .8656 </tableData> </table> </function> <function name=3D"aero/derivative/Clr-per_rad"> <description> Roll moment coefficient derivative due to yaw rate, per rad Considerable effect on spiral mode.=20 Large positive values leads to strong sprial instability </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 .0311 .0000 .0628 2.0000 .0951 4.0000 .1276 8.0000 .1897 9.0000 .2013 10.0000 .2114 11.0000 .2198 12.0000 .2261 13.0000 .2304 14.0000 .2332 15.0000 .2297 16.0000 .2051 </tableData> </table> </function> <function name=3D"aero/coefficient/dCl_Ail"> <description> Roll Moment coefficient increment due to aileron deflection Positive surface deflection is trailing edge down. Positive rolling moment is right wing down </description> <table> <independentVar lookup=3D"row"> fcs/total-aileron-pos-deg = </independentVar> <tableData> -64.0000 -.0687 -40.0000 -.0576 -20.0000 -.0369 -10.0000 -.0184 .0000 .0000 10.0000 .0184 20.0000 .0369 40.0000 .0576 64.0000 .0687 </tableData> </table> </function> <function name=3D"aero/coefficient/dCl_Rud"> <description> Roll moment coefficient increment due to rudder DATCOM does not calculate this term </description> <table> <independentVar lookup=3D"row"> fcs/rudder-pos-deg = </independentVar> <tableData> -30.0000 .0000 .0000 .0000 30.0000 .0000 </tableData> </table> </function> <axis name=3D"ROLL"> <function name=3D"aero/moment/roll-lbsft"> <description> Roll Moment =3D ( Clbeta*beta + Clp*p*b/(2*V) + = Clr*r*b/(2*V) + dCl_Ail + dCl_Rud ) * q_bar * wing area * wing span </description> <product> <sum> <product> <property> aero/derivative/Clbeta-per_rad </property> <property> aero/beta-rad </property> </product> <product> <property> aero/derivative/Clp-per_rad </property> <property> velocities/p-rad_sec </property> <property> aero/bi2vel </property> </product> <product> <property> aero/derivative/Clr-per_rad </property> <property> velocities/r-rad_sec </property> <property> aero/bi2vel </property> </product> <property> aero/coefficient/dCl_Ail </property> <property> aero/coefficient/dCl_Rud </property> </sum> <property> aero/qbar-psf </property> <property> metrics/Sw-sqft </property> <property> metrics/bw-ft </property> </product> </function> </axis> <!-- = **********************************************************************=20 PITCH MOMENT = ********************************************************************** = --> <function name=3D"aero/coefficient/CM_wbh"> <description> Pitch moment coefficient as a function of alpha CM0 is included in this term </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 .1134 .0000 .0487 2.0000 -.0155 4.0000 -.0791 8.0000 -.2067 9.0000 -.2388 10.0000 -.2702 11.0000 -.3030 12.0000 -.3385 13.0000 -.3745 </tableData> </table> </function> <function name=3D"aero/derivative/CMq-per_rad"> <description> Pitch moment coefficient derivative due to pitch rate, per rad Pitch damping derivative - Very important to short period = damping of oscillations </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 -18.4339 16.0000 -18.4339 </tableData> </table> </function> <function name=3D"aero/derivative/CMadot-per_rad"> <description> Pitch moment coefficient derivative due to AOA rate, per rad Negative CMadot increase short period damping </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 -7.3596 .0000 -7.4939 2.0000 -7.7462 4.0000 -7.8900 8.0000 -7.4230 9.0000 -7.1375 10.0000 -6.5746 11.0000 -5.4534 12.0000 -4.4398 13.0000 -3.7349 14.0000 -2.1362 15.0000 .7521 16.0000 2.4471 </tableData> </table> </function> <function name=3D"aero/coefficient/dCM_Elev"> <description> Pitch moment coefficient increment due to elevator deflection Positive surface deflection is trailing edge down </description> <table> <independentVar lookup=3D"row"> fcs/elevator-pos-deg = </independentVar> <tableData> -20.0000 .4592 -15.0000 .4367 -10.0000 .3081 -5.0000 .1540 .0000 -.0003 5.0000 -.1540 10.0000 -.3081 13.0000 -.3923 16.0000 -.4548 </tableData> </table> </function> <function name=3D"aero/coefficient/dCM_Flap"> <description> Pitch moment coefficient increment due to flap deflection Positive surface deflection is trailing edge down. </description> <table> <independentVar lookup=3D"row"> fcs/flap-pos-deg = </independentVar> <tableData> .0000 .0000 15.0000 -.0988 30.0000 -.1854 40.0000 -.2203 </tableData> </table> </function> <function name=3D"aero/coefficient/dCM_Power"> <description> Pitch moment coefficient increment due to thrust effects </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <independentVar lookup=3D"column"> = propulsion/total-thrust-coefficient </independentVar> <tableData> .0000 .1000 .2000 .3000 -2.0000 -.0010 -.0880 -.1749 -.2619 .0000 -.0072 -.0942 -.1811 -.2681 2.0000 -.0127 -.0997 -.1867 -.2736 4.0000 -.0171 -.1041 -.1910 -.2780 8.0000 -.0208 -.1077 -.1947 -.2817 9.0000 -.0205 -.1075 -.1944 -.2814 10.0000 -.0197 -.1067 -.1937 -.2806 11.0000 -.0185 -.1055 -.1925 -.2794 12.0000 -.0169 -.1038 -.1908 -.2778 13.0000 -.0148 -.1018 -.1888 -.2757 14.0000 -.0125 -.0994 -.1864 -.2733 15.0000 -.0098 -.0967 -.1837 -.2707 16.0000 -.0069 -.0938 -.1808 -.2678 </tableData> </table> </function> <axis name=3D"PITCH"> <function name=3D"aero/moment/pitch-lbsft"> <description> Pitch Moment =3D ( CM_wbh + CMq*q*MAC/(2*V) + = CMadot*adot*MAC/(2*V) + dCM_Elev + dCM_Flap + CM_Power ) * q_bar * wing area * wing MAC </description> <product> <sum> <property> aero/coefficient/CM_wbh </property> <product> <property> aero/derivative/CMq-per_rad </property> <property> velocities/q-rad_sec </property> <property> aero/ci2vel </property> </product> <product> <property> aero/derivative/CMadot-per_rad </property> <property> aero/alphadot-rad_sec </property> <property> aero/ci2vel </property> </product> <property> aero/coefficient/dCM_Elev </property> <property> aero/coefficient/dCM_Flap </property> <property> aero/coefficient/dCM_Power </property> </sum> <property> aero/qbar-psf </property> <property> metrics/Sw-sqft </property> <property> metrics/cbarw-ft </property> </product> </function> </axis> <!-- = **********************************************************************=20 YAW MOMENT = ********************************************************************** = --> <function name=3D"aero/derivative/CNbeta-per_rad"> <description> Yaw moment coefficient derivative due to sideslip, per rad Determines dutch roll and spiral characteristics Prevents side-slip and counters yawing moments </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 .0680 16.0000 .0680 </tableData> </table> </function> <function name=3D"aero/derivative/CNp-per_rad"> <description> Yaw moment coefficient derivative due to roll rate, per rad Reduces Dutch Roll damping. Positive value desireable </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 .0001 .0000 -.0154 2.0000 -.0314 4.0000 -.0479 8.0000 -.0839 9.0000 -.0925 10.0000 -.1011 11.0000 -.1093 12.0000 -.1171 13.0000 -.1238 14.0000 -.1322 15.0000 -.1374 16.0000 -.2479 </tableData> </table> </function> <function name=3D"aero/derivative/CNr-per_rad"> <description> Yaw moment coefficient derivative due to yaw rate, per rad Main contributor to damping of Dutch Roll </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <tableData> -2.0000 -.1099 .0000 -.1111 2.0000 -.1118 4.0000 -.1121 8.0000 -.1115 9.0000 -.1113 10.0000 -.1110 11.0000 -.1107 12.0000 -.1104 13.0000 -.1102 14.0000 -.1100 15.0000 -.1101 16.0000 -.1111 </tableData> </table> </function> <function name=3D"aero/coefficient/dCN_Ail"> <description> Yaw Moment coefficient increment due to aileron deflection Positive surface deflection is trailing edge down. Positive yawing moment is nose right </description> <table> <independentVar lookup=3D"row"> aero/alpha-deg = </independentVar> <independentVar lookup=3D"column"> fcs/total-aileron-pos-deg = </independentVar> <tableData> -64.0000 -40.0000 -20.0000 -10.0000 = .0000 10.0000 20.0000 40.0000 64.0000 -2.0000 .0002 .0002 .0001 .0001 = .0000 -.0001 -.0001 -.0002 -.0002 .0000 .0013 .0011 .0007 .0003 = .0000 -.0003 -.0007 -.0011 -.0013 2.0000 .0023 .0020 .0013 .0006 = .0000 -.0006 -.0013 -.0020 -.0023 4.0000 .0034 .0029 .0018 .0009 = .0000 -.0009 -.0018 -.0029 -.0034 8.0000 .0056 .0047 .0030 .0015 = .0000 -.0015 -.0030 -.0047 -.0056 9.0000 .0060 .0050 .0032 .0016 = .0000 -.0016 -.0032 -.0050 -.0060 10.0000 .0063 .0053 .0034 .0017 = .0000 -.0017 -.0034 -.0053 -.0063 11.0000 .0067 .0056 .0036 .0018 = .0000 -.0018 -.0036 -.0056 -.0067 12.0000 .0069 .0058 .0037 .0019 = .0000 -.0019 -.0037 -.0058 -.0069 13.0000 .0071 .0060 .0038 .0019 = .0000 -.0019 -.0038 -.0060 -.0071 14.0000 .0072 .0061 .0039 .0019 = .0000 -.0019 -.0039 -.0061 -.0072 15.0000 .0072 .0060 .0039 .0019 = .0000 -.0019 -.0039 -.0060 -.0072 16.0000 .0065 .0054 .0035 .0017 = .0000 -.0017 -.0035 -.0054 -.0065 </tableData> </table> </function> <function name=3D"aero/coefficient/dCN_Rud"> <description> Yaw coefficient increment due to rudder DATCOM does not calculate this, but a default value is supplied </description> <table> <independentVar lookup=3D"row"> fcs/rudder-pos-deg = </independentVar> <tableData> -10.0000 -.0100 .0000 .0000 10.0000 .0100 </tableData> </table> </function> <axis name=3D"YAW"> <function name=3D"aero/moment/yaw-lbsft"> <description> Yaw Moment =3D ( CNbeta*beta + CNp*p*b/(2*V) + CNr*r*b/(2*V) = + dCN_Ail + dCN_Rud ) * q_bar * wing area * wing span </description> <product> <sum> <product> <property> aero/derivative/CNbeta-per_rad </property> <property> aero/beta-rad </property> </product> <product> <property> aero/derivative/CNp-per_rad </property> <property> velocities/p-rad_sec </property> <property> aero/bi2vel </property> </product> <product> <property> aero/derivative/CNr-per_rad </property> <property> velocities/r-rad_sec </property> <property> aero/bi2vel </property> </product> <property> aero/coefficient/dCN_Ail </property> <property> aero/coefficient/dCN_Rud </property> </sum> <property> aero/qbar-psf </property> <property> metrics/Sw-sqft </property> <property> metrics/bw-ft </property> </product> </function> </axis> </aerodynamics> ------=_NextPart_000_001F_01CC8014.01A4CAA0 Content-Type: text/plain; charset="us-ascii" MIME-Version: 1.0 Content-Transfer-Encoding: 7bit Content-Disposition: inline ------------------------------------------------------------------------------ All of the data generated in your IT infrastructure is seriously valuable. Why? It contains a definitive record of application performance, security threats, fraudulent activity, and more. Splunk takes this data and makes sense of it. IT sense. And common sense. http://p.sf.net/sfu/splunk-d2dcopy2 ------=_NextPart_000_001F_01CC8014.01A4CAA0 Content-Type: text/plain; charset="us-ascii" MIME-Version: 1.0 Content-Transfer-Encoding: 7bit Content-Disposition: inline _______________________________________________ Flightgear-flightmodel mailing list [email protected] https://lists.sourceforge.net/lists/listinfo/flightgear-flightmodel ------=_NextPart_000_001F_01CC8014.01A4CAA0--