Airfoil: PT-40 (A) Builder: T. Lampe Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 100600 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.91 -0.353 0.0957 0.0988 0.0907 0.0964 0.0969 -3.70 -0.261 0.0608 0.0650 0.0583 0.0564 0.0634 -3.07 -0.170 0.0435 0.0484 0.0467 0.0393 0.0396 -1.68 0.038 0.0314 0.0308 0.0362 0.0283 0.0303 -1.04 0.144 0.0300 0.0284 0.0345 0.0285 0.0288 0.34 0.349 0.0237 0.0241 0.0232 0.0236 0.0242 1.33 0.445 0.0213 0.0221 0.0221 0.0207 0.0204 2.27 0.535 0.0179 0.0187 0.0170 0.0182 0.0179 3.28 0.631 0.0167 0.0184 0.0156 0.0164 0.0164 4.30 0.714 0.0176 0.0201 0.0170 0.0170 0.0165 5.31 0.799 0.0208 0.0232 0.0202 0.0191 0.0209 6.30 0.883 0.0229 0.0246 0.0214 0.0219 0.0239 7.27 0.964 0.0245 0.0251 0.0240 0.0245 0.0245 8.57 1.061 0.0284 0.0298 0.0263 0.0276 0.0300 9.16 1.100 0.0303 0.0320 0.0288 0.0310 0.0295 10.39 1.173 0.0388 0.0359 0.0393 0.0403 0.0398 Tabulated from data in file CL01021.DAT & reduced using program Q05.01D Average Reynolds #: 200200 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.28 -0.200 0.0602 0.0635 0.0600 0.0579 0.0595 -3.53 -0.084 0.0425 0.0447 0.0428 0.0402 0.0423 -2.50 0.049 0.0267 0.0292 0.0262 0.0247 0.0267 -1.50 0.149 0.0198 0.0211 0.0185 0.0204 0.0192 0.32 0.333 0.0147 0.0156 0.0138 0.0156 0.0141 0.63 0.361 0.0149 0.0154 0.0140 0.0159 0.0141 1.64 0.463 0.0139 0.0148 0.0130 0.0142 0.0135 2.71 0.567 0.0134 0.0133 0.0134 0.0135 0.0133 3.70 0.660 0.0119 0.0118 0.0121 0.0116 0.0121 4.72 0.751 0.0136 0.0133 0.0137 0.0135 0.0139 5.73 0.843 0.0158 0.0160 0.0150 0.0163 0.0157 7.24 0.976 0.0183 0.0188 0.0177 0.0185 0.0184 7.79 1.019 0.0192 0.0196 0.0186 0.0195 0.0193 8.88 1.096 0.0226 0.0218 0.0218 0.0235 0.0232 9.87 1.157 0.0259 0.0241 0.0255 0.0286 0.0255 10.88 1.208 0.0313 0.0278 0.0309 0.0335 0.0331 Tabulated from data in file CL01023.DAT & reduced using program Q05.01D Average Reynolds #: 299800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.28 -0.025 0.0348 0.0372 0.0349 0.0329 0.0342 -2.38 0.065 0.0240 0.0252 0.0245 0.0236 0.0229 -1.35 0.166 0.0173 0.0177 0.0172 0.0171 0.0172 -0.32 0.271 0.0141 0.0141 0.0137 0.0140 0.0146 0.71 0.379 0.0130 0.0130 0.0121 0.0133 0.0135 1.73 0.483 0.0127 0.0126 0.0116 0.0133 0.0133 3.25 0.629 0.0121 0.0116 0.0126 0.0120 0.0121 3.78 0.680 0.0113 0.0108 0.0121 0.0111 0.0113 4.81 0.777 0.0125 0.0124 0.0126 0.0125 0.0126 5.85 0.873 0.0138 0.0139 0.0135 0.0137 0.0143 6.78 0.952 0.0150 0.0151 0.0146 0.0149 0.0155 7.75 1.031 0.0167 0.0166 0.0163 0.0167 0.0173 8.90 1.119 0.0194 0.0182 0.0196 0.0195 0.0201 10.35 1.214 0.0246 0.0223 0.0254 0.0257 0.0249 10.86 1.239 0.0268 0.0236 0.0273 0.0288 0.0275 11.89 1.284 0.0326 0.0269 0.0338 0.0371 0.0327 Tabulated from data in file CL01025.DAT & reduced using program Q05.01D Average Reynolds #: 399500 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.37 -0.037 0.0353 0.0373 0.0354 0.0338 0.0349 -2.42 0.056 0.0246 0.0251 0.0253 0.0239 0.0240 -1.35 0.169 0.0166 0.0164 0.0166 0.0166 0.0169 -0.31 0.276 0.0134 0.0130 0.0134 0.0133 0.0140 0.57 0.368 0.0122 0.0119 0.0119 0.0120 0.0130 1.73 0.489 0.0119 0.0116 0.0118 0.0116 0.0124 2.76 0.591 0.0120 0.0115 0.0119 0.0121 0.0124 3.49 0.656 0.0122 0.0113 0.0125 0.0124 0.0125 4.81 0.788 0.0117 0.0112 0.0119 0.0118 0.0120 5.58 0.857 0.0126 0.0120 0.0127 0.0127 0.0130 6.64 0.953 0.0136 0.0133 0.0136 0.0133 0.0143 7.90 1.062 0.0159 0.0154 0.0155 0.0161 0.0166 8.91 1.140 0.0182 0.0170 0.0186 0.0185 0.0187 9.93 1.206 0.0215 0.0194 0.0222 0.0222 0.0222 10.95 1.258 0.0257 0.0224 0.0269 0.0272 0.0263 11.93 1.295 0.0312 0.0259 0.0321 0.0358 0.0311 Tabulated from data in file AB01027.DAT & reduced using program Q05.01D File PT40A.DRG created on 09-12-1997 at 13:39:49 using program FORMAT