15x8E (15x8E.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) 0.0000 1.0000 8.0000 0.0000 0.0000 0.5000 0.0000 0.3450 0.0000 0.3450 0.0000 0.2050 0.0000 0.0000 0.1200 0.9560 8.0000 0.0152 -0.2124 0.4926 0.0152 0.3440 1.1576 0.3289 0.2843 0.2145 0.0163 0.0339 0.2400 0.9019 8.0000 0.1202 -0.4125 0.4831 0.0566 0.3411 4.5578 0.3076 0.2844 0.2402 0.0354 0.0470 0.3600 0.8483 8.0000 0.4028 -0.4776 0.4727 0.1176 0.3362 10.0978 0.2852 0.2725 0.2769 0.0577 0.0702 0.4800 0.8069 8.0000 0.9490 -0.2582 0.4623 0.1922 0.3293 17.4676 0.2657 0.2498 0.3210 0.0814 0.1019 0.6000 0.7869 8.0000 1.8307 0.3748 0.4531 0.2744 0.3204 25.9011 0.2522 0.2221 0.3702 0.1046 0.1396 0.7200 0.7921 8.0000 3.0730 1.5018 0.4459 0.3581 0.3096 34.1878 0.2453 0.1941 0.4221 0.1257 0.1810 0.8400 0.8187 8.0000 4.6008 3.0160 0.4417 0.4375 0.2968 41.0793 0.2430 0.1694 0.4745 0.1429 0.2236 0.9600 0.8577 8.0000 6.1841 4.6709 0.4415 0.5065 0.2821 45.7142 0.2420 0.1503 0.5246 0.1548 0.2648 1.0800 0.8996 8.0000 7.4469 6.0677 0.4463 0.5592 0.2654 47.6592 0.2388 0.1382 0.5674 0.1601 0.3013 1.2000 0.9381 8.0000 7.9952 6.7558 0.4571 0.5896 0.2481 46.6790 0.2328 0.1340 0.5953 0.1573 0.3295 1.3242 0.9747 8.0000 8.0000 6.8766 0.4717 0.6031 0.2318 43.8764 0.2259 0.1347 0.6103 0.1485 0.3501 1.5202 1.0296 8.0000 8.0000 7.0428 0.4916 0.6168 0.2090 39.9483 0.2152 0.1352 0.6269 0.1341 0.3754 1.7203 1.0827 8.0000 8.0000 7.1882 0.5081 0.6217 0.1894 36.5054 0.2050 0.1355 0.6349 0.1182 0.3917 1.9205 1.1326 8.0000 8.0000 7.3082 0.5209 0.6176 0.1730 33.5431 0.1959 0.1363 0.6340 0.1007 0.3981 2.1207 1.1738 8.0000 8.0000 7.4027 0.5300 0.6045 0.1595 30.9802 0.1872 0.1369 0.6241 0.0830 0.3952 2.3209 1.2053 8.0000 8.0000 7.4746 0.5358 0.5861 0.1486 28.7494 0.1792 0.1368 0.6090 0.0667 0.3873 2.5210 1.2278 8.0000 8.0000 7.5308 0.5383 0.5677 0.1400 26.7959 0.1719 0.1362 0.5938 0.0513 0.3795 2.7212 1.2416 8.0000 8.0000 7.5725 0.5377 0.5494 0.1333 25.0747 0.1655 0.1351 0.5785 0.0369 0.3717 2.9214 1.2475 8.0000 8.0000 7.6014 0.5342 0.5312 0.1281 23.5493 0.1598 0.1337 0.5632 0.0235 0.3638 3.1216 1.2458 8.0000 8.0000 7.6197 0.5280 0.5132 0.1241 22.1899 0.1546 0.1317 0.5479 0.0111 0.3560 3.3217 1.2372 8.0000 8.0000 7.6303 0.5192 0.4955 0.1210 20.9722 0.1497 0.1290 0.5327 -0.0004 0.3482 3.5219 1.2221 8.0000 8.0000 7.6369 0.5080 0.4782 0.1184 19.8760 0.1447 0.1255 0.5174 -0.0110 0.3405 3.7221 1.2012 8.0000 8.0000 7.6404 0.4946 0.4613 0.1160 18.8847 0.1394 0.1208 0.5020 -0.0206 0.3330 3.9222 1.1748 8.0000 8.0000 7.6313 0.4790 0.4449 0.1138 17.9845 0.1336 0.1152 0.4866 -0.0293 0.3256 4.1224 1.1437 8.0000 8.0000 7.6124 0.4616 0.4288 0.1117 17.1637 0.1277 0.1088 0.4711 -0.0371 0.3183 4.3226 1.1082 8.0000 8.0000 7.5929 0.4425 0.4132 0.1097 16.4126 0.1216 0.1018 0.4556 -0.0440 0.3112 4.5228 1.0690 8.0000 8.0000 7.5734 0.4217 0.3979 0.1079 15.7229 0.1154 0.0942 0.4400 -0.0503 0.3041 4.7229 1.0265 8.0000 8.0000 7.5556 0.3996 0.3828 0.1063 15.0875 0.1091 0.0864 0.4244 -0.0558 0.2972 4.9231 0.9813 8.0000 8.0000 7.5396 0.3762 0.3681 0.1048 14.5004 0.1029 0.0784 0.4087 -0.0608 0.2902 5.1233 0.9340 8.0000 8.0000 7.5269 0.3518 0.3536 0.1035 13.9564 0.0967 0.0705 0.3930 -0.0653 0.2831 5.3234 0.8850 8.0000 8.0000 7.5158 0.3264 0.3392 0.1024 13.4511 0.0906 0.0628 0.3771 -0.0696 0.2757 5.5236 0.8349 8.0000 8.0000 7.5042 0.3004 0.3248 0.1014 12.9804 0.0846 0.0555 0.3612 -0.0740 0.2679 5.7238 0.7842 8.0000 8.0000 7.4925 0.2737 0.3105 0.1005 12.5411 0.0788 0.0487 0.3453 -0.0786 0.2596 5.9240 0.7335 8.0000 8.0000 7.4805 0.2467 0.2962 0.0998 12.1301 0.0732 0.0424 0.3292 -0.0834 0.2508 6.1241 0.6833 8.0000 8.0000 7.4676 0.2194 0.2818 0.0993 11.7448 0.0679 0.0367 0.3131 -0.0886 0.2416 6.3243 0.6341 8.0000 8.0000 7.4536 0.1921 0.2674 0.0989 11.3829 0.0627 0.0315 0.2969 -0.0941 0.2318 6.5245 0.5864 8.0000 8.0000 7.4385 0.1649 0.2529 0.0987 11.0424 0.0579 0.0270 0.2806 -0.1001 0.2215 6.7247 0.5409 8.0000 8.0000 7.4216 0.1379 0.2383 0.0987 10.7214 0.0534 0.0229 0.2642 -0.1067 0.2106 6.9248 0.4979 8.0000 8.0000 7.4022 0.1114 0.2235 0.0988 10.4184 0.0492 0.0194 0.2477 -0.1140 0.1992 7.1165 0.4598 8.0000 8.0000 7.3404 0.0865 0.2091 0.0991 10.1436 0.0455 0.0166 0.2313 -0.1215 0.1870 7.1629 0.4510 8.0000 8.0000 7.2950 0.0806 0.2056 0.0991 10.0793 0.0447 0.0160 0.2268 -0.1235 0.1835 7.2008 0.4438 8.0000 8.0000 7.2460 0.0756 0.2027 0.0992 10.0274 0.0440 0.0155 0.2231 -0.1252 0.1805 7.2386 0.4330 8.0000 8.0000 7.1844 0.0669 0.1991 0.0993 9.9760 0.0430 0.0147 0.2184 -0.1290 0.1768 7.2765 0.4170 8.0000 8.0000 7.1103 0.0530 0.1946 0.0994 9.9251 0.0414 0.0137 0.2125 -0.1356 0.1725 7.3144 0.3950 8.0000 8.0000 6.8412 0.0331 0.1891 0.0995 9.8747 0.0393 0.0123 0.2052 -0.1457 0.1673 7.3523 0.3654 8.0000 8.0000 6.5473 0.0056 0.1823 0.0996 9.8248 0.0364 0.0105 0.1964 -0.1599 0.1612 7.3902 0.3252 8.0000 8.0000 6.2446 -0.0325 0.1736 0.0997 9.7754 0.0324 0.0084 0.1855 -0.1800 0.1539 7.4280 0.2660 8.0000 8.0000 5.9828 -0.0894 0.1618 0.0998 9.7265 0.0265 0.0056 0.1709 -0.2105 0.1448 7.4659 0.1498 8.0000 8.0000 6.2098 -0.2027 0.1404 0.0999 9.6781 0.0150 0.0018 0.1452 -0.2719 0.1302 7.5000 0.0197 8.0000 8.0040 8.0040 -0.3299 0.1172 0.1000 9.6397 0.0020 0.0000 0.1172 0.0000 0.0000 RADIUS: 7.50 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.099956 TOTAL WEIGHT (Kg) = 0.045331 TOTAL VOLUME (IN**3) = 1.628406 TOTAL PROJECTED AREA (IN**2) = 12.7713 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002495 MOMENT OF INERTIA (Kg-M**2) = 0.000282 STATIC MOMENT, ONE SIDE (IN-LB) = 0.125207 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 = 73.545 INNER LIMIT (NORMALIZED BY RADIUS) = 0.067 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 8326.93 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.20, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.12, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412