Airfoil: SD7037 (C) Builder: D. Brengman Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -5.31 -0.153 0.0385 0.0373 0.0373 0.0367 0.0426 -3.77 -0.033 0.0264 0.0256 0.0244 0.0267 0.0289 -2.25 0.087 0.0176 0.0143 0.0170 0.0191 0.0198 -0.73 0.235 0.0174 0.0178 0.0189 0.0157 0.0170 0.80 0.392 0.0267 0.0247 0.0273 0.0281 0.0269 2.38 0.589 0.0327 0.0322 0.0296 0.0369 0.0322 3.92 0.778 0.0285 0.0317 0.0320 0.0256 0.0246 5.45 0.947 0.0240 0.0252 0.0270 0.0204 0.0236 6.99 1.077 0.0257 0.0230 0.0271 0.0273 0.0255 8.49 1.176 0.0287 0.0324 0.0270 0.0299 0.0254 Tabulated from data in file CN00901.DAT & reduced using program Q02.00D Average Reynolds #: 100000 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -5.28 -0.198 0.0342 0.0366 0.0334 0.0335 0.0332 -4.18 -0.050 0.0220 0.0221 0.0215 0.0225 0.0219 -2.22 0.100 0.0161 0.0159 0.0157 0.0144 0.0184 -0.70 0.249 0.0169 0.0180 0.0151 0.0180 0.0165 0.84 0.499 0.0183 0.0174 0.0174 0.0212 0.0173 2.39 0.666 0.0191 0.0186 0.0199 0.0188 0.0190 3.92 0.813 0.0176 0.0170 0.0171 0.0177 0.0186 5.46 0.960 0.0180 0.0168 0.0175 0.0194 0.0185 7.00 1.092 0.0219 0.0223 0.0214 0.0225 0.0216 8.52 1.202 0.0283 0.0296 0.0257 0.0287 0.0292 Tabulated from data in file CN00903.DAT & reduced using program Q02.00D Average Reynolds #: 199700 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -5.31 -0.178 0.0248 0.0259 0.0254 0.0244 0.0236 -3.78 -0.022 0.0166 0.0167 0.0184 0.0159 0.0155 -2.26 0.180 0.0128 0.0130 0.0130 0.0112 0.0142 -0.72 0.338 0.0123 0.0130 0.0135 0.0109 0.0119 0.85 0.475 0.0111 0.0105 0.0114 0.0097 0.0128 2.37 0.645 0.0111 0.0108 0.0114 0.0103 0.0119 3.93 0.812 0.0123 0.0117 0.0123 0.0126 0.0126 5.44 0.964 0.0143 0.0138 0.0139 0.0152 0.0144 7.00 1.108 0.0178 0.0185 0.0174 0.0176 0.0179 8.53 1.228 0.0226 0.0219 0.0220 0.0234 0.0229 Tabulated from data in file CN00905.DAT & reduced using program Q02.00D Average Reynolds #: 299300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.29 -0.154 0.0205 0.0216 0.0221 0.0180 0.0201 -3.76 0.029 0.0126 0.0138 0.0153 0.0093 0.0119 -2.25 0.218 0.0102 0.0095 0.0117 0.0095 0.0100 -0.70 0.365 0.0086 0.0084 0.0091 0.0078 0.0088 0.79 0.477 0.0081 0.0081 0.0083 0.0075 0.0086 2.38 0.658 0.0092 0.0090 0.0091 0.0089 0.0097 4.02 0.836 0.0107 0.0105 0.0104 0.0110 0.0109 5.45 0.980 0.0126 0.0124 0.0125 0.0125 0.0128 6.95 1.119 0.0160 0.0161 0.0154 0.0161 0.0163 8.52 1.250 0.0199 0.0196 0.0189 0.0212 0.0202 10.04 1.352 0.0245 0.0248 0.0240 0.0245 0.0249 Tabulated from data in file AG00907.DAT & reduced using program Q02.00D File 7037cbf4.drg created on 09-12-1997 at 13:46:25 using program FORMAT