11x10E (11x10E.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 0.8000 10.0000 0.0000 0.0000 0.4000 0.0000 0.3480 0.0000 0.2784 0.0000 0.0650 0.0000 0.0000 0.1150 0.7593 10.0000 0.0179 -0.4370 0.3946 0.0135 0.3274 1.4197 0.2486 0.1997 0.0767 0.0113 -0.0726 0.2300 0.7120 10.0000 0.1428 -0.8614 0.3902 0.0502 0.3078 5.6417 0.2191 0.2014 0.1084 0.0323 -0.0557 0.3450 0.6689 10.0000 0.4835 -1.0972 0.3870 0.1037 0.2891 12.5728 0.1934 0.1936 0.1521 0.0575 -0.0279 0.4600 0.6425 10.0000 1.1518 -0.9074 0.3852 0.1681 0.2713 21.7269 0.1743 0.1762 0.2038 0.0845 0.0083 0.5750 0.6419 10.0000 2.2465 -0.0781 0.3850 0.2377 0.2546 31.8740 0.1634 0.1546 0.2611 0.1113 0.0491 0.6900 0.6683 10.0000 3.8089 1.5337 0.3866 0.3070 0.2388 41.3011 0.1596 0.1328 0.3207 0.1358 0.0909 0.8050 0.7149 10.0000 5.7444 3.8525 0.3902 0.3703 0.2239 48.6358 0.1601 0.1138 0.3777 0.1558 0.1299 0.9200 0.7705 10.0000 7.7472 6.3109 0.3959 0.4219 0.2100 53.2716 0.1618 0.0994 0.4260 0.1696 0.1627 1.0350 0.8245 10.0000 9.3242 8.2954 0.4040 0.4560 0.1971 55.1064 0.1625 0.0906 0.4588 0.1755 0.1854 1.1500 0.8699 10.0000 9.9942 9.1868 0.4146 0.4672 0.1852 54.1337 0.1611 0.0879 0.4698 0.1719 0.1937 1.2661 0.9090 10.0000 10.0000 9.2553 0.4262 0.4617 0.1741 51.4967 0.1582 0.0894 0.4648 0.1612 0.1904 1.4016 0.9531 10.0000 10.0000 9.3421 0.4375 0.4538 0.1624 48.6322 0.1547 0.0913 0.4577 0.1467 0.1852 1.5381 0.9909 10.0000 10.0000 9.4300 0.4466 0.4444 0.1519 45.9784 0.1505 0.0921 0.4492 0.1323 0.1805 1.6747 1.0209 10.0000 10.0000 9.5079 0.4535 0.4337 0.1428 43.5425 0.1458 0.0923 0.4396 0.1184 0.1760 1.8112 1.0437 10.0000 10.0000 9.5723 0.4583 0.4218 0.1351 41.3065 0.1410 0.0919 0.4289 0.1050 0.1712 1.9478 1.0595 10.0000 10.0000 9.6207 0.4610 0.4086 0.1287 39.2529 0.1363 0.0915 0.4172 0.0923 0.1657 2.0843 1.0688 10.0000 10.0000 9.6533 0.4617 0.3942 0.1237 37.3648 0.1322 0.0911 0.4045 0.0802 0.1596 2.2209 1.0720 10.0000 10.0000 9.6752 0.4606 0.3788 0.1200 35.6267 0.1286 0.0905 0.3909 0.0688 0.1529 2.3574 1.0694 10.0000 10.0000 9.6855 0.4577 0.3625 0.1177 34.0243 0.1258 0.0898 0.3765 0.0584 0.1457 2.4940 1.0615 10.0000 10.0000 9.6915 0.4531 0.3455 0.1158 32.5444 0.1229 0.0886 0.3615 0.0489 0.1383 2.6305 1.0486 10.0000 10.0000 9.6969 0.4469 0.3281 0.1141 31.1753 0.1196 0.0867 0.3457 0.0403 0.1306 2.7671 1.0313 10.0000 10.0000 9.7006 0.4392 0.3103 0.1124 29.9064 0.1159 0.0842 0.3295 0.0327 0.1227 2.9036 1.0097 10.0000 10.0000 9.7010 0.4300 0.2923 0.1109 28.7283 0.1120 0.0810 0.3128 0.0259 0.1148 3.0402 0.9845 10.0000 10.0000 9.6934 0.4196 0.2741 0.1094 27.6323 0.1077 0.0773 0.2957 0.0200 0.1067 3.1767 0.9558 10.0000 10.0000 9.6840 0.4078 0.2559 0.1081 26.6110 0.1033 0.0731 0.2782 0.0149 0.0986 3.3133 0.9243 10.0000 10.0000 9.6747 0.3949 0.2377 0.1068 25.6575 0.0987 0.0685 0.2606 0.0106 0.0905 3.4498 0.8902 10.0000 10.0000 9.6659 0.3809 0.2195 0.1057 24.7658 0.0941 0.0637 0.2427 0.0070 0.0823 3.5864 0.8539 10.0000 10.0000 9.6585 0.3660 0.2015 0.1046 23.9305 0.0893 0.0587 0.2248 0.0040 0.0741 3.7229 0.8159 10.0000 10.0000 9.6530 0.3501 0.1837 0.1036 23.1467 0.0846 0.0536 0.2068 0.0014 0.0659 3.8595 0.7765 10.0000 10.0000 9.6503 0.3335 0.1661 0.1028 22.4100 0.0798 0.0485 0.1889 -0.0008 0.0578 3.9960 0.7362 10.0000 10.0000 9.6503 0.3161 0.1489 0.1020 21.7165 0.0751 0.0435 0.1711 -0.0028 0.0496 4.1326 0.6953 10.0000 10.0000 9.6533 0.2981 0.1321 0.1013 21.0628 0.0705 0.0387 0.1536 -0.0048 0.0415 4.2691 0.6543 10.0000 10.0000 9.6577 0.2795 0.1156 0.1008 20.4456 0.0659 0.0342 0.1363 -0.0070 0.0331 4.4057 0.6134 10.0000 10.0000 9.6631 0.2605 0.0995 0.1003 19.8622 0.0615 0.0300 0.1193 -0.0096 0.0247 4.5422 0.5733 10.0000 10.0000 9.6699 0.2411 0.0839 0.0999 19.3099 0.0573 0.0262 0.1028 -0.0126 0.0162 4.6788 0.5341 10.0000 10.0000 9.6775 0.2215 0.0689 0.0996 18.7864 0.0532 0.0228 0.0868 -0.0161 0.0076 4.8153 0.4964 10.0000 10.0000 9.6851 0.2016 0.0544 0.0995 18.2896 0.0494 0.0197 0.0714 -0.0202 -0.0009 4.9519 0.4605 10.0000 10.0000 9.6941 0.1817 0.0406 0.0994 17.8175 0.0458 0.0170 0.0567 -0.0251 -0.0092 5.0884 0.4268 10.0000 10.0000 9.6890 0.1618 0.0274 0.0994 17.3685 0.0424 0.0147 0.0424 -0.0308 -0.0178 5.2193 0.3970 10.0000 10.0000 9.6085 0.1427 0.0156 0.0995 16.9582 0.0395 0.0128 0.0285 -0.0372 -0.0272 5.2528 0.3893 10.0000 10.0000 9.5716 0.1374 0.0125 0.0995 16.8564 0.0388 0.0123 0.0248 -0.0393 -0.0299 5.2806 0.3800 10.0000 10.0000 9.5344 0.1300 0.0091 0.0996 16.7727 0.0378 0.0117 0.0208 -0.0425 -0.0327 5.3083 0.3674 10.0000 10.0000 9.4374 0.1194 0.0048 0.0996 16.6898 0.0366 0.0110 0.0157 -0.0476 -0.0361 5.3361 0.3509 10.0000 10.0000 9.2727 0.1049 -0.0006 0.0997 16.6077 0.0350 0.0100 0.0095 -0.0547 -0.0402 5.3639 0.3299 10.0000 10.0000 9.1228 0.0860 -0.0073 0.0997 16.5264 0.0329 0.0089 0.0018 -0.0644 -0.0452 5.3917 0.3028 10.0000 10.0000 8.9817 0.0611 -0.0157 0.0998 16.4459 0.0302 0.0075 -0.0077 -0.0773 -0.0510 5.4194 0.2668 10.0000 10.0000 8.8743 0.0275 -0.0265 0.0998 16.3661 0.0266 0.0059 -0.0198 -0.0950 -0.0583 5.4472 0.2135 10.0000 10.0000 8.8927 -0.0229 -0.0421 0.0999 16.2871 0.0213 0.0038 -0.0370 -0.1216 -0.0682 5.4750 0.1147 10.0000 10.0000 9.7963 -0.1171 -0.0702 0.1000 16.2088 0.0115 0.0011 -0.0677 -0.1717 -0.0850 5.5000 0.0171 10.0000 10.0051 10.0050 -0.2104 -0.0978 0.1000 16.1467 0.0017 0.0000 -0.0978 0.0000 0.0000 RADIUS: 5.50 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.15 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.053044 TOTAL WEIGHT (Kg) = 0.024056 TOTAL VOLUME (IN**3) = 0.864162 TOTAL PROJECTED AREA (IN**2) = 7.2952 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000712 MOMENT OF INERTIA (Kg-M**2) = 0.000080 STATIC MOMENT, ONE SIDE (IN-LB) = 0.048375 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 = 86.469 INNER LIMIT (NORMALIZED BY RADIUS) = 0.073 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 12673.67 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.15, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.03, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412