12x7E-3 (12x7E-3.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.1990 0.6894 -1.3581 0.0000 -0.9033 0.3447 0.0000 0.4400 0.0000 0.3033 0.0000 0.1100 0.0000 0.0000 0.2771 0.6230 -0.3847 0.1674 -1.2224 0.3156 0.0323 0.4305 5.4909 0.2682 0.1680 0.1165 0.0089 -0.0534 0.3552 0.5976 0.5284 0.4716 -1.4219 0.3113 0.0710 0.4180 11.9322 0.2498 0.1610 0.1340 0.0185 -0.0430 0.4333 0.5944 1.3813 0.9208 -1.3620 0.3128 0.1136 0.4024 18.6861 0.2392 0.1545 0.1589 0.0290 -0.0253 0.5114 0.6081 2.1739 1.5082 -0.9820 0.3158 0.1578 0.3836 25.1443 0.2333 0.1470 0.1888 0.0387 -0.0021 0.5895 0.6358 2.9063 2.2055 -0.2878 0.3202 0.2017 0.3618 30.7718 0.2301 0.1393 0.2225 0.0474 0.0240 0.6676 0.6741 3.5785 2.9667 0.6519 0.3261 0.2430 0.3372 35.2702 0.2273 0.1321 0.2575 0.0550 0.0504 0.7457 0.7175 4.1904 3.7469 1.7352 0.3333 0.2795 0.3133 38.6496 0.2248 0.1255 0.2910 0.0619 0.0748 0.8238 0.7625 4.7421 4.4942 2.8245 0.3418 0.3093 0.2912 40.9667 0.2221 0.1204 0.3193 0.0676 0.0942 0.9019 0.8067 5.2336 5.1508 3.7461 0.3514 0.3301 0.2709 42.2689 0.2186 0.1172 0.3396 0.0718 0.1070 0.9800 0.8483 5.6648 5.6625 4.3945 0.3622 0.3398 0.2523 42.6019 0.2140 0.1175 0.3492 0.0726 0.1090 1.0624 0.8888 6.0543 6.0543 4.8326 0.3741 0.3418 0.2344 42.2079 0.2084 0.1203 0.3513 0.0696 0.1029 1.2182 0.9555 6.6078 6.6078 5.5157 0.3944 0.3437 0.2052 40.8045 0.1960 0.1227 0.3538 0.0615 0.0960 1.3782 1.0105 6.9268 6.9268 5.9948 0.4121 0.3433 0.1808 38.6559 0.1827 0.1221 0.3544 0.0508 0.0956 1.5383 1.0533 7.0000 7.0000 6.2245 0.4268 0.3407 0.1615 35.9133 0.1701 0.1196 0.3533 0.0382 0.1012 1.6984 1.0874 7.0000 7.0000 6.3513 0.4386 0.3361 0.1466 33.2639 0.1595 0.1169 0.3505 0.0260 0.1078 1.8584 1.1132 7.0000 7.0000 6.4445 0.4475 0.3297 0.1356 30.9417 0.1509 0.1144 0.3461 0.0156 0.1134 2.0185 1.1312 7.0000 7.0000 6.5078 0.4537 0.3216 0.1276 28.8960 0.1444 0.1123 0.3402 0.0067 0.1176 2.1786 1.1419 7.0000 7.0000 6.5462 0.4573 0.3121 0.1221 27.0846 0.1394 0.1106 0.3328 -0.0008 0.1205 2.3386 1.1457 7.0000 7.0000 6.5668 0.4585 0.3012 0.1184 25.4724 0.1356 0.1090 0.3242 -0.0071 0.1219 2.4987 1.1431 7.0000 7.0000 6.5792 0.4572 0.2891 0.1158 24.0305 0.1323 0.1071 0.3143 -0.0124 0.1218 2.6588 1.1344 7.0000 7.0000 6.5893 0.4536 0.2760 0.1136 22.7349 0.1289 0.1044 0.3033 -0.0170 0.1203 2.8188 1.1203 7.0000 7.0000 6.5986 0.4479 0.2621 0.1116 21.5655 0.1251 0.1010 0.2914 -0.0210 0.1177 2.9789 1.1010 7.0000 7.0000 6.6051 0.4401 0.2475 0.1098 20.5055 0.1209 0.0968 0.2785 -0.0246 0.1139 3.1390 1.0770 7.0000 7.0000 6.6060 0.4303 0.2324 0.1080 19.5409 0.1164 0.0922 0.2648 -0.0278 0.1091 3.2990 1.0489 7.0000 7.0000 6.6033 0.4187 0.2169 0.1065 18.6599 0.1117 0.0870 0.2503 -0.0306 0.1034 3.4591 1.0169 7.0000 7.0000 6.5994 0.4053 0.2011 0.1050 17.8525 0.1068 0.0814 0.2352 -0.0331 0.0969 3.6191 0.9817 7.0000 7.0000 6.5941 0.3903 0.1851 0.1037 17.1100 0.1018 0.0756 0.2196 -0.0354 0.0897 3.7792 0.9436 7.0000 7.0000 6.5878 0.3738 0.1690 0.1025 16.4251 0.0967 0.0696 0.2035 -0.0375 0.0819 3.9393 0.9031 7.0000 7.0000 6.5806 0.3558 0.1529 0.1014 15.7917 0.0916 0.0636 0.1870 -0.0396 0.0736 4.0993 0.8606 7.0000 7.0000 6.5725 0.3365 0.1369 0.1005 15.2041 0.0865 0.0576 0.1704 -0.0417 0.0650 4.2594 0.8166 7.0000 7.0000 6.5636 0.3161 0.1209 0.0997 14.6578 0.0815 0.0517 0.1536 -0.0441 0.0560 4.4195 0.7716 7.0000 7.0000 6.5544 0.2945 0.1052 0.0991 14.1486 0.0765 0.0460 0.1367 -0.0468 0.0467 4.5795 0.7259 7.0000 7.0000 6.5449 0.2719 0.0897 0.0986 13.6730 0.0716 0.0406 0.1198 -0.0499 0.0371 4.7396 0.6800 7.0000 7.0000 6.5356 0.2485 0.0743 0.0982 13.2277 0.0668 0.0356 0.1032 -0.0538 0.0273 4.8997 0.6344 7.0000 7.0000 6.5267 0.2243 0.0593 0.0980 12.8101 0.0621 0.0309 0.0867 -0.0584 0.0174 5.0597 0.5895 7.0000 7.0000 6.5184 0.1994 0.0447 0.0978 12.4176 0.0577 0.0267 0.0706 -0.0638 0.0074 5.2198 0.5457 7.0000 7.0000 6.5106 0.1740 0.0305 0.0979 12.0481 0.0534 0.0230 0.0549 -0.0703 -0.0026 5.3799 0.5036 7.0000 7.0000 6.4910 0.1481 0.0168 0.0980 11.6997 0.0494 0.0196 0.0394 -0.0778 -0.0128 5.5399 0.4635 7.0000 7.0000 6.4315 0.1218 0.0037 0.0983 11.3706 0.0456 0.0167 0.0239 -0.0865 -0.0236 5.6932 0.4274 7.0000 7.0000 6.3254 0.0965 -0.0083 0.0987 11.0721 0.0422 0.0143 0.0093 -0.0961 -0.0342 5.7303 0.4186 7.0000 7.0000 6.2890 0.0899 -0.0111 0.0989 11.0022 0.0414 0.0137 0.0057 -0.0988 -0.0369 5.7606 0.4084 7.0000 7.0000 6.1843 0.0814 -0.0140 0.0990 10.9457 0.0404 0.0131 0.0021 -0.1028 -0.0394 5.7909 0.3947 7.0000 7.0000 6.0722 0.0693 -0.0176 0.0991 10.8898 0.0391 0.0122 -0.0023 -0.1087 -0.0425 5.8212 0.3769 7.0000 7.0000 5.9664 0.0531 -0.0219 0.0992 10.8345 0.0374 0.0111 -0.0076 -0.1170 -0.0460 5.8515 0.3541 7.0000 7.0000 5.8636 0.0319 -0.0272 0.0993 10.7797 0.0352 0.0099 -0.0140 -0.1281 -0.0501 5.8818 0.3249 7.0000 7.0000 5.7687 0.0043 -0.0335 0.0994 10.7254 0.0323 0.0083 -0.0218 -0.1427 -0.0549 5.9121 0.2860 7.0000 7.0000 5.6836 -0.0330 -0.0417 0.0995 10.6717 0.0285 0.0065 -0.0316 -0.1626 -0.0608 5.9424 0.2282 7.0000 7.0000 5.6052 -0.0889 -0.0532 0.0997 10.6185 0.0227 0.0041 -0.0454 -0.1923 -0.0687 5.9727 0.1222 7.0000 7.0000 5.7624 -0.1925 -0.0735 0.0998 10.5659 0.0122 0.0012 -0.0694 -0.2481 -0.0820 6.0000 0.0182 7.0000 7.0036 7.0035 -0.2943 -0.0931 0.0999 10.5241 0.0018 0.0000 -0.0931 0.0000 0.0000 RADIUS: 6.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 0.98 HUB TRANSITION (IN) BLADES: 3 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.087914 TOTAL WEIGHT (Kg) = 0.039870 TOTAL VOLUME (IN**3) = 1.432229 TOTAL PROJECTED AREA (IN**2) = 13.3432 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001576 MOMENT OF INERTIA (Kg-M**2) = 0.000178 STATIC MOMENT, ONE SIDE (IN-LB) = 0.065482 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 85.009 INNER LIMIT (NORMALIZED BY RADIUS) = 0.067 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 11457.55 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.05, E66 (Transition Start, Airfoil 1) AIRFOIL2: 4.42, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412