CODE = 1 ' Data Type Code RUN = 2 ' Current Run Number TP = 3 ' Number of this test point SCAN = 4 ' Pressure Scan Position TEST = 5 ' Test Number (no UW!) QNOM = 6 ' Nominal Dynamic Pressure (Qnom) ALPHAI = 7 ' Indicated Alpha (uses AlphaAcc if present, otherwise AlphaEnc) PSI = 8 ' Indicated Psi (yaw angle), deg LIFTR = 9 ' ----------------------------- DRAGR = 10 ' Raw Balance Data PMR = 11 ' Uncorrected YMR = 12 ' RMR = 13 ' SFR = 14 ' ----------------------------- TIME = 15 ' Time (seconds since midnight) FOULING = 16 ' Strut fouling flag PRESSTS = 17 ' Test section absolute static pressure, psi TEMPTS = 18 ' Test section static temperature, deg F LIFTCORR = 19 ' CLWA * QC * SW DRAGCORR = 20 ' CDWA * QC * SW PMCORR05 = 21 ' CMWA01 * QC * SW * MAC YMCORR05 = 22 ' CNWA01 * QC * SW * BREF RMCORR05 = 23 ' CRWA01 * QC * SW * BREF SFCORR = 24 ' CYWA * QC * SW WTARERUN = 25 ' Run number associated with the current 3pt tare. (End) LB = 26 ' Forces & Moments corrected for CI and Weight Tare & moment transfers DB = 27 ' PMB = 28 ' YMB = 29 ' RMB = 30 ' SFB = 31 ' QA = 32 ' Actual dynamic pressure for clean test section, psf QC = 33 ' Dynamic pressure corrected for Delta-q ESB = 34 ' Solid blockage (old UWAL method) EWB = 35 ' Wake blockage BCFACTOR = 36 ' Blockage effect = (1+et)**2 GPHEIGHT = 37 ' Ground plane height (inches) INVERTED = 38 ' Whether model is inverted (0 = upright, 1 = inverted) TAILON = 39 ' Whether tail is on (0 = off, 1 = on) IS3DTEST = 40 ' 3-D or 2-D corrections applied (0 = 2D, 1 = 3D) DALPHAWC = 41 ' Wall correction to angle of attack DCD_WC = 42 ' Wall correction effect for CD DCM_WC = 43 ' Wall correction effect for CM UPFLOW = 44 ' Tunnel upflow angle (also stored in the DRConst) DCD_ANG = 45 ' Change in CD due to upflow ALPHAENC = 46 ' Angle of attack based on UWAL encoder ALPHAACC = 47 ' Angle of attack based on UWAL accelerometer (blank if not used) ALPHAC = 48 ' Alpha, corrected for everything BETA = 49 ' = -Psi CLSA2 = 50 ' CLSA * CLSA CLWA = 51 ' Coefficients about the wind axis CDWA = 52 ' CDPWA = 53 ' CMWA05 = 54 ' CMWA15 = 55 ' CMWA25 = 56 ' CMWA35 = 57 ' CMWA00 = 58 ' CNWA05 = 59 ' CNWA15 = 60 ' CNWA25 = 61 ' CNWA35 = 62 ' CNWA00 = 63 ' CRWA05 = 64 ' CRWA15 = 65 ' CRWA25 = 66 ' CRWA35 = 67 ' CRWA00 = 68 ' CYWA = 69 ' CLSA = 70 ' Coefficients about the stability axis CDSA = 71 ' CDPSA = 72 ' CMSA05 = 73 ' CMSA15 = 74 ' CMSA25 = 75 ' CMSA35 = 76 ' CMSA00 = 77 ' CNSA05 = 78 ' CNSA15 = 79 ' CNSA25 = 80 ' CNSA35 = 81 ' CNSA00 = 82 ' CRSA05 = 83 ' CRSA15 = 84 ' CRSA25 = 85 ' CRSA35 = 86 ' CRSA00 = 87 ' CYSA = 88 ' CLBA = 89 ' Coefficients about the body axis CDBA = 90 ' CDPBA = 91 ' CMBA05 = 92 ' CMBA15 = 93 ' CMBA25 = 94 ' CMBA35 = 95 ' CMBA00 = 96 ' CNBA05 = 97 ' CNBA15 = 98 ' CNBA25 = 99 ' CNBA35 = 100 ' CNBA00 = 101 ' CRBA05 = 102 ' CRBA15 = 103 ' CRBA25 = 104 ' CRBA35 = 105 ' CRBA00 = 106 ' CYBA = 107 ' CLT05 = 108 ' (Stability axis only) CLT15 = 109 ' (Stability axis only) CLT25 = 110 ' (Stability axis only) CLT35 = 111 ' (Stability axis only) CLT00 = 112 ' (Stability axis only) CDP05 = 113 ' (Stability axis only) CDP15 = 114 ' (Stability axis only) CDP25 = 115 ' (Stability axis only) CDP35 = 116 ' (Stability axis only) CDP00 = 117 ' (Stability axis only) CDI = 118 ' Ideal induced drag PMB05 = 119 ' PMB transferred to MMC1 PMB15 = 120 ' PMB transferred to MMC2 PMB25 = 121 ' PMB transferred to MMC3 PMB35 = 122 ' PMB transferred to MMC4 PMB00 = 123 ' PMB transferred to MMC5 RMB05 = 124 ' YMB transferred to MMC1 RMB15 = 125 ' YMB transferred to MMC2 RMB25 = 126 ' YMB transferred to MMC3 RMB35 = 127 ' YMB transferred to MMC4 RMB00 = 128 ' YMB transferred to MMC5 YMB05 = 129 ' RMB transferred to MMC1 YMB15 = 130 ' RMB transferred to MMC2 YMB25 = 131 ' RMB transferred to MMC3 YMB35 = 132 ' RMB transferred to MMC4 YMB00 = 133 ' RMB transferred to MMC5 PMWT = 134 ' Calculated weight tare value for Pitching Moment at the current angles (Alpha & Psi) RMWT = 135 ' Calculated weight tare value for Rolling Moment at the current angles (Alpha & Psi) CLUNCORR = 136 ' UNCORRECTED CL = LIFTR / QA * SW CDUNCORR = 137 ' UNCORRECTED CD = DRAGR / QA * SW CMUNCORR = 138 ' UNCORRECTED CM = PMR / QA * SW * MAC CNUNCORR = 139 ' UNCORRECTED CN = YMR / QA * SW * BREF CRUNCORR = 140 ' UNCORRECTED CR = RMR / QA * SW * BREF CYUNCORR = 141 ' UNCORRECTED CY = SFR / QA * SW MACH = 142 ' Mach number SPEEDMPH = 143 ' Airspeed in MPH RE_MAC = 144 ' Reynolds No. based on MAC (InitialCoeffs) RE_B = 145 ' Reynolds No. based on MAC (InitialCoeffs) RE_FT = 146 ' Reynolds No. based on MAC (InitialCoeffs) LOD = 147 ' LIFT OVER DRAG (CLWA/CDWA) TRAV_X = 148 ' X location of traverse rig TRAV_Y = 149 ' Y location of traverse rig TRAV_Z = 150 ' Z location of traverse rig MVACC = 151 ' TACC = 152 ' CDPSA = 153 ' CLSA2 = 154 ' BLANK = 155 ' BLANK = 156 ' BLANK = 157 ' BLANK = 158 ' BLANK = 159 ' BLANK = 160 ' BLANK = 161 ' BLANK = 162 ' BLANK = 163 ' BLANK = 164 ' BLANK = 165 ' BLANK = 166 ' BLANK = 167 ' BLANK = 168 ' BLANK = 169 ' BLANK = 170 ' BLANK = 171 ' BLANK = 172 ' BLANK = 173 ' BLANK = 174 ' BLANK = 175 ' BLANK = 176 ' BLANK = 177 ' BLANK = 178 ' BLANK = 179 ' BLANK = 180 ' BLANK = 181 ' BLANK = 182 ' BLANK = 183 ' BLANK = 184 ' BLANK = 185 ' BLANK = 186 ' BLANK = 187 ' BLANK = 188 ' BLANK = 189 ' BLANK = 190 ' BLANK = 191 ' BLANK = 192 ' BLANK = 193 ' BLANK = 194 ' BLANK = 195 ' BLANK = 196 ' BLANK = 197 ' BLANK = 198 ' BLANK = 199 ' BLANK = 200 ' End of user-defined variables. Hopefully you'll never need more...