16x8E (16x8E.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 0.3750 0.0000 0.3750 0.0000 0.2350 0.0000 0.0000 0.1400 0.9536 8.0000 0.0181 -0.2483 0.4930 0.0151 0.3715 1.1790 0.3542 0.3066 0.2436 0.0184 0.0467 0.2800 0.9032 8.0000 0.1422 -0.4705 0.4862 0.0562 0.3610 4.6224 0.3261 0.3028 0.2665 0.0384 0.0587 0.4200 0.8586 8.0000 0.4714 -0.5097 0.4803 0.1168 0.3435 10.1289 0.2949 0.2855 0.2988 0.0611 0.0799 0.5600 0.8296 8.0000 1.0914 -0.2086 0.4758 0.1908 0.3202 17.2333 0.2657 0.2590 0.3379 0.0848 0.1089 0.7000 0.8234 8.0000 2.0560 0.5509 0.4730 0.2723 0.2979 25.0543 0.2453 0.2288 0.3818 0.1075 0.1436 0.8400 0.8415 8.0000 3.3538 1.8083 0.4725 0.3553 0.2773 32.4341 0.2334 0.1993 0.4288 0.1279 0.1821 0.9800 0.8789 8.0000 4.8692 3.4076 0.4746 0.4337 0.2585 38.3360 0.2272 0.1736 0.4769 0.1442 0.2223 1.1200 0.9272 8.0000 6.3625 5.0542 0.4799 0.5016 0.2412 42.1177 0.2236 0.1537 0.5235 0.1553 0.2619 1.2600 0.9779 8.0000 7.5078 6.3828 0.4888 0.5530 0.2254 43.4811 0.2204 0.1409 0.5638 0.1596 0.2978 1.4000 1.0256 8.0000 7.9957 7.0213 0.5018 0.5820 0.2111 42.2699 0.2165 0.1371 0.5899 0.1551 0.3257 1.5436 1.0711 8.0000 8.0000 7.1224 0.5170 0.5934 0.1979 39.5176 0.2120 0.1393 0.6034 0.1439 0.3452 1.7490 1.1312 8.0000 8.0000 7.2428 0.5354 0.6019 0.1814 36.0545 0.2052 0.1418 0.6152 0.1273 0.3654 1.9579 1.1865 8.0000 8.0000 7.3447 0.5503 0.6012 0.1672 33.0359 0.1984 0.1444 0.6181 0.1092 0.3759 2.1669 1.2341 8.0000 8.0000 7.4244 0.5615 0.5912 0.1555 30.4379 0.1919 0.1466 0.6118 0.0916 0.3771 2.3759 1.2716 8.0000 8.0000 7.4816 0.5691 0.5730 0.1460 28.1871 0.1856 0.1484 0.5974 0.0748 0.3698 2.5848 1.2995 8.0000 8.0000 7.5235 0.5733 0.5533 0.1384 26.2240 0.1798 0.1496 0.5815 0.0589 0.3610 2.7938 1.3185 8.0000 8.0000 7.5526 0.5743 0.5337 0.1325 24.5006 0.1747 0.1503 0.5656 0.0437 0.3520 3.0028 1.3289 8.0000 8.0000 7.5698 0.5722 0.5143 0.1281 22.9781 0.1702 0.1505 0.5497 0.0295 0.3429 3.2117 1.3314 8.0000 8.0000 7.5762 0.5673 0.4950 0.1248 21.6251 0.1662 0.1502 0.5338 0.0162 0.3337 3.4207 1.3265 8.0000 8.0000 7.5790 0.5596 0.4761 0.1222 20.4161 0.1621 0.1487 0.5178 0.0038 0.3247 3.6297 1.3146 8.0000 8.0000 7.5825 0.5493 0.4578 0.1197 19.3303 0.1573 0.1458 0.5019 -0.0076 0.3159 3.8386 1.2965 8.0000 8.0000 7.5829 0.5367 0.4400 0.1173 18.3503 0.1521 0.1416 0.4859 -0.0180 0.3074 4.0476 1.2725 8.0000 8.0000 7.5752 0.5219 0.4227 0.1150 17.4619 0.1464 0.1360 0.4698 -0.0273 0.2991 4.2566 1.2432 8.0000 8.0000 7.5528 0.5049 0.4059 0.1130 16.6532 0.1404 0.1294 0.4537 -0.0357 0.2911 4.4655 1.2091 8.0000 8.0000 7.5293 0.4861 0.3895 0.1110 15.9143 0.1342 0.1218 0.4375 -0.0430 0.2834 4.6745 1.1709 8.0000 8.0000 7.5066 0.4656 0.3735 0.1092 15.2366 0.1279 0.1136 0.4213 -0.0494 0.2759 4.8834 1.1289 8.0000 8.0000 7.4853 0.4436 0.3578 0.1076 14.6131 0.1214 0.1048 0.4050 -0.0549 0.2685 5.0924 1.0838 8.0000 8.0000 7.4670 0.4201 0.3425 0.1060 14.0377 0.1149 0.0957 0.3886 -0.0597 0.2612 5.3014 1.0360 8.0000 8.0000 7.4500 0.3954 0.3273 0.1047 13.5050 0.1085 0.0866 0.3722 -0.0640 0.2538 5.5103 0.9861 8.0000 8.0000 7.4325 0.3697 0.3123 0.1035 13.0106 0.1020 0.0777 0.3558 -0.0683 0.2460 5.7193 0.9347 8.0000 8.0000 7.4143 0.3430 0.2974 0.1024 12.5506 0.0957 0.0693 0.3392 -0.0726 0.2378 5.9283 0.8823 8.0000 8.0000 7.3949 0.3157 0.2825 0.1015 12.1215 0.0895 0.0613 0.3226 -0.0771 0.2291 6.1372 0.8293 8.0000 8.0000 7.3739 0.2878 0.2677 0.1007 11.7204 0.0835 0.0538 0.3059 -0.0817 0.2200 6.3462 0.7764 8.0000 8.0000 7.3512 0.2595 0.2528 0.1000 11.3446 0.0777 0.0469 0.2892 -0.0865 0.2105 6.5552 0.7240 8.0000 8.0000 7.3266 0.2310 0.2379 0.0995 10.9919 0.0721 0.0406 0.2723 -0.0918 0.2004 6.7641 0.6727 8.0000 8.0000 7.2995 0.2025 0.2230 0.0992 10.6603 0.0667 0.0349 0.2554 -0.0974 0.1899 6.9731 0.6231 8.0000 8.0000 7.2688 0.1740 0.2079 0.0990 10.3478 0.0617 0.0299 0.2384 -0.1036 0.1788 7.1821 0.5756 8.0000 8.0000 7.2339 0.1459 0.1927 0.0989 10.0530 0.0569 0.0254 0.2213 -0.1104 0.1672 7.3910 0.5308 8.0000 8.0000 7.1940 0.1182 0.1773 0.0990 9.7743 0.0525 0.0216 0.2041 -0.1178 0.1550 7.5912 0.4909 8.0000 8.0000 7.1242 0.0922 0.1624 0.0992 9.5213 0.0487 0.0184 0.1871 -0.1256 0.1424 7.6404 0.4816 8.0000 8.0000 7.0749 0.0859 0.1587 0.0992 9.4611 0.0478 0.0177 0.1824 -0.1276 0.1387 7.6808 0.4738 8.0000 8.0000 7.0208 0.0805 0.1556 0.0993 9.4123 0.0471 0.0172 0.1784 -0.1295 0.1355 7.7212 0.4622 8.0000 8.0000 6.9522 0.0712 0.1518 0.0994 9.3639 0.0459 0.0163 0.1734 -0.1336 0.1315 7.7616 0.4450 8.0000 8.0000 6.8353 0.0563 0.1471 0.0995 9.3160 0.0443 0.0151 0.1671 -0.1408 0.1268 7.8020 0.4214 8.0000 8.0000 6.5193 0.0349 0.1414 0.0995 9.2686 0.0419 0.0136 0.1595 -0.1516 0.1213 7.8424 0.3898 8.0000 8.0000 6.1617 0.0055 0.1344 0.0996 9.2217 0.0388 0.0116 0.1502 -0.1670 0.1148 7.8828 0.3469 8.0000 8.0000 5.7672 -0.0353 0.1255 0.0997 9.1752 0.0346 0.0092 0.1388 -0.1888 0.1071 7.9232 0.2836 8.0000 8.0000 5.3536 -0.0962 0.1135 0.0998 9.1292 0.0283 0.0062 0.1236 -0.2218 0.0975 7.9636 0.1596 8.0000 8.0000 5.0886 -0.2173 0.0919 0.0999 9.0837 0.0159 0.0020 0.0972 -0.2883 0.0823 8.0000 0.0210 8.0000 8.0040 8.0040 -0.3530 0.0686 0.1000 9.0476 0.0021 0.0000 0.0686 0.0000 0.0000 RADIUS: 8.00 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.40 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.117377 TOTAL WEIGHT (Kg) = 0.053232 TOTAL VOLUME (IN**3) = 1.912213 TOTAL PROJECTED AREA (IN**2) = 14.6421 MOMENT OF INERTIA (SNAIL-IN**2) = 0.003407 MOMENT OF INERTIA (Kg-M**2) = 0.000385 STATIC MOMENT, ONE SIDE (IN-LB) = 0.159284 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 = 73.610 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 7353.05 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.40, 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