Airfoil: PT-40 (B) Builder: T. Lampe Comment: clean; open bay Number of Reynolds #'s: 4 Average Reynolds #: 99700 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -2.84 -0.109 0.0396 0.0437 0.0417 0.0366 0.0373 -1.71 0.062 0.0275 0.0302 0.0287 0.0264 0.0253 -0.85 0.174 0.0235 0.0250 0.0234 0.0241 0.0229 0.35 0.297 0.0197 0.0200 0.0185 0.0207 0.0180 1.34 0.384 0.0179 0.0191 0.0185 0.0182 0.0165 2.35 0.475 0.0171 0.0178 0.0172 0.0177 0.0158 3.36 0.567 0.0158 0.0171 0.0156 0.0149 0.0146 4.43 0.659 0.0168 0.0179 0.0167 0.0162 0.0155 5.45 0.746 0.0195 0.0207 0.0182 0.0191 0.0163 6.48 0.831 0.0215 0.0255 0.0214 0.0200 0.0172 7.48 0.920 0.0245 0.0286 0.0249 0.0233 0.0208 8.51 0.995 0.0268 0.0285 0.0263 0.0282 0.0284 9.50 1.066 0.0326 0.0374 0.0323 0.0333 0.0309 10.46 1.126 0.0378 0.0405 0.0345 0.0403 0.0373 11.51 1.183 0.0458 0.0536 0.0467 0.0429 0.0417 Tabulated from data in file CL01066.DAT & reduced using program Q05.01D Average Reynolds #: 200100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -2.67 0.006 0.0253 0.0293 0.0252 0.0239 0.0229 -1.46 0.115 0.0188 0.0193 0.0196 0.0177 0.0182 -0.85 0.172 0.0168 0.0159 0.0176 0.0161 0.0165 0.47 0.310 0.0146 0.0150 0.0146 0.0134 0.0132 1.49 0.414 0.0140 0.0146 0.0137 0.0131 0.0135 2.48 0.512 0.0140 0.0134 0.0142 0.0136 0.0129 3.50 0.618 0.0134 0.0133 0.0130 0.0138 0.0121 4.54 0.711 0.0145 0.0147 0.0140 0.0141 0.0134 5.54 0.799 0.0162 0.0162 0.0162 0.0156 0.0154 6.53 0.886 0.0181 0.0185 0.0176 0.0178 0.0177 7.52 0.973 0.0190 0.0183 0.0193 0.0193 0.0200 8.45 1.047 0.0209 0.0203 0.0205 0.0207 0.0213 9.53 1.125 0.0250 0.0236 0.0243 0.0250 0.0263 10.48 1.189 0.0285 0.0268 0.0279 0.0293 0.0296 11.54 1.245 0.0332 0.0303 0.0324 0.0341 0.0335 Tabulated from data in file CL01068.DAT & reduced using program Q05.01D Average Reynolds #: 299800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -2.81 0.004 0.0226 0.0270 0.0232 0.0204 0.0193 -1.76 0.090 0.0169 0.0193 0.0173 0.0152 0.0148 -0.69 0.201 0.0142 0.0139 0.0150 0.0137 0.0131 0.32 0.322 0.0134 0.0132 0.0134 0.0128 0.0129 1.36 0.428 0.0132 0.0126 0.0131 0.0130 0.0130 2.35 0.521 0.0140 0.0132 0.0136 0.0140 0.0137 3.48 0.626 0.0147 0.0140 0.0143 0.0152 0.0142 4.59 0.727 0.0141 0.0142 0.0143 0.0138 0.0129 5.65 0.826 0.0154 0.0156 0.0147 0.0150 0.0150 6.64 0.908 0.0164 0.0165 0.0156 0.0160 0.0163 7.65 0.994 0.0184 0.0184 0.0177 0.0181 0.0187 8.65 1.073 0.0206 0.0198 0.0193 0.0210 0.0216 9.59 1.145 0.0229 0.0215 0.0218 0.0238 0.0236 10.59 1.206 0.0267 0.0246 0.0252 0.0276 0.0279 11.49 1.255 0.0305 0.0271 0.0278 0.0319 0.0318 12.50 1.293 0.0364 0.0312 0.0320 0.0396 0.0419 Tabulated from data in file CL01070.DAT & reduced using program Q05.01D Average Reynolds #: 399100 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -2.90 0.019 0.0199 0.0209 0.0207 0.0188 0.0178 -1.62 0.145 0.0142 0.0136 0.0150 0.0139 0.0135 -0.72 0.233 0.0130 0.0123 0.0136 0.0130 0.0126 0.29 0.336 0.0126 0.0120 0.0129 0.0127 0.0123 1.34 0.444 0.0131 0.0121 0.0130 0.0131 0.0129 2.28 0.532 0.0141 0.0131 0.0135 0.0139 0.0140 3.34 0.637 0.0143 0.0137 0.0143 0.0138 0.0141 4.43 0.743 0.0132 0.0133 0.0130 0.0122 0.0124 5.47 0.845 0.0139 0.0136 0.0134 0.0139 0.0139 6.60 0.942 0.0153 0.0155 0.0147 0.0149 0.0147 7.36 1.007 0.0169 0.0173 0.0163 0.0158 0.0172 8.75 1.120 0.0197 0.0190 0.0187 0.0195 0.0208 9.46 1.166 0.0214 0.0205 0.0199 0.0217 0.0224 10.48 1.233 0.0242 0.0221 0.0222 0.0252 0.0243 11.55 1.296 0.0286 0.0245 0.0251 0.0305 0.0298 12.59 1.336 0.0332 0.0286 0.0287 0.0343 0.0384 Tabulated from data in file CL01072.DAT & reduced using program Q05.01D File PT40B.DRG created on 09-12-1997 at 13:39:49 using program FORMAT