20x10E (20x10E.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 1.2500 10.0000 0.0000 0.0000 0.6250 0.0000 0.3280 0.0000 0.4100 0.0000 0.1800 0.0000 0.0000 0.2600 1.1810 10.0000 0.0337 -0.6083 0.6153 0.0207 0.3248 1.1810 0.3836 0.4174 0.1958 0.0237 -0.0132 0.5200 1.1322 10.0000 0.2601 -1.0550 0.6115 0.0760 0.3154 4.5509 0.3571 0.4015 0.2360 0.0476 0.0149 0.7800 1.1092 10.0000 0.8315 -1.0366 0.6129 0.1567 0.2996 9.6293 0.3323 0.3771 0.2940 0.0698 0.0582 1.0400 1.1163 10.0000 1.8273 -0.3540 0.6186 0.2539 0.2774 15.6228 0.3097 0.3482 0.3649 0.0896 0.1126 1.3000 1.1537 10.0000 3.2302 1.0413 0.6278 0.3585 0.2493 21.5768 0.2876 0.3175 0.4430 0.1066 0.1740 1.5600 1.2160 10.0000 4.9221 3.0283 0.6396 0.4616 0.2220 26.6642 0.2699 0.2870 0.5222 0.1205 0.2381 1.8200 1.2937 10.0000 6.7010 5.2453 0.6532 0.5542 0.1983 30.3697 0.2565 0.2582 0.5956 0.1312 0.3003 2.0800 1.3759 10.0000 8.3136 7.2253 0.6677 0.6274 0.1780 32.4616 0.2449 0.2331 0.6554 0.1380 0.3551 2.3400 1.4532 10.0000 9.4939 8.6987 0.6823 0.6722 0.1608 32.8514 0.2337 0.2140 0.6933 0.1389 0.3954 2.6000 1.5185 10.0000 9.9955 9.3952 0.6961 0.6797 0.1466 31.4607 0.2227 0.2047 0.6998 0.1293 0.4111 2.8584 1.5700 10.0000 10.0000 9.4962 0.7073 0.6609 0.1352 29.1091 0.2122 0.2033 0.6843 0.1102 0.4070 3.0890 1.6058 10.0000 10.0000 9.5628 0.7137 0.6436 0.1270 27.2592 0.2040 0.2027 0.6703 0.0929 0.4020 3.3179 1.6323 10.0000 10.0000 9.6120 0.7168 0.6260 0.1207 25.6262 0.1970 0.2028 0.6563 0.0754 0.3957 3.5469 1.6504 10.0000 10.0000 9.6439 0.7169 0.6081 0.1159 24.1665 0.1913 0.2038 0.6424 0.0577 0.3883 3.7759 1.6604 10.0000 10.0000 9.6582 0.7141 0.5900 0.1126 22.8557 0.1869 0.2055 0.6285 0.0403 0.3802 4.0048 1.6628 10.0000 10.0000 9.6548 0.7086 0.5719 0.1105 21.6733 0.1837 0.2077 0.6145 0.0236 0.3717 4.2338 1.6581 10.0000 10.0000 9.6368 0.7004 0.5539 0.1094 20.6020 0.1813 0.2096 0.6006 0.0077 0.3631 4.4628 1.6467 10.0000 10.0000 9.6109 0.6897 0.5364 0.1083 19.6277 0.1784 0.2100 0.5868 -0.0071 0.3550 4.6917 1.6290 10.0000 10.0000 9.5740 0.6767 0.5196 0.1074 18.7382 0.1749 0.2084 0.5729 -0.0205 0.3474 4.9207 1.6055 10.0000 10.0000 9.5340 0.6615 0.5034 0.1065 17.9233 0.1710 0.2047 0.5590 -0.0324 0.3406 5.1497 1.5766 10.0000 10.0000 9.4956 0.6443 0.4879 0.1056 17.1743 0.1666 0.1989 0.5451 -0.0426 0.3346 5.3786 1.5429 10.0000 10.0000 9.4606 0.6251 0.4731 0.1049 16.4836 0.1618 0.1912 0.5312 -0.0513 0.3296 5.6076 1.5047 10.0000 10.0000 9.4315 0.6041 0.4589 0.1041 15.8450 0.1567 0.1818 0.5172 -0.0583 0.3254 5.8366 1.4625 10.0000 10.0000 9.4088 0.5815 0.4452 0.1034 15.2530 0.1513 0.1711 0.5033 -0.0640 0.3218 6.0655 1.4167 10.0000 10.0000 9.3880 0.5574 0.4319 0.1028 14.7026 0.1456 0.1598 0.4894 -0.0691 0.3182 6.2945 1.3679 10.0000 10.0000 9.3674 0.5320 0.4188 0.1022 14.1897 0.1398 0.1483 0.4755 -0.0741 0.3144 6.5234 1.3163 10.0000 10.0000 9.3470 0.5053 0.4060 0.1017 13.7108 0.1338 0.1368 0.4616 -0.0788 0.3102 6.7524 1.2626 10.0000 10.0000 9.3267 0.4776 0.3934 0.1012 13.2626 0.1277 0.1255 0.4477 -0.0836 0.3058 6.9814 1.2071 10.0000 10.0000 9.3065 0.4489 0.3810 0.1008 12.8423 0.1216 0.1144 0.4338 -0.0883 0.3010 7.2103 1.1503 10.0000 10.0000 9.2864 0.4195 0.3687 0.1004 12.4474 0.1155 0.1036 0.4199 -0.0932 0.2960 7.4393 1.0926 10.0000 10.0000 9.2663 0.3894 0.3565 0.1000 12.0757 0.1093 0.0933 0.4060 -0.0982 0.2905 7.6683 1.0345 10.0000 10.0000 9.2459 0.3587 0.3445 0.0998 11.7253 0.1032 0.0835 0.3920 -0.1034 0.2848 7.8972 0.9764 10.0000 10.0000 9.2252 0.3278 0.3326 0.0996 11.3943 0.0972 0.0743 0.3781 -0.1089 0.2787 8.1262 0.9189 10.0000 10.0000 9.2043 0.2965 0.3208 0.0994 11.0813 0.0913 0.0657 0.3642 -0.1147 0.2722 8.3552 0.8622 10.0000 10.0000 9.1829 0.2652 0.3089 0.0993 10.7849 0.0856 0.0578 0.3503 -0.1210 0.2653 8.5841 0.8070 10.0000 10.0000 9.1608 0.2340 0.2972 0.0992 10.5037 0.0801 0.0506 0.3364 -0.1278 0.2580 8.8131 0.7536 10.0000 10.0000 9.1377 0.2029 0.2853 0.0992 10.2367 0.0747 0.0441 0.3225 -0.1351 0.2504 9.0421 0.7024 10.0000 10.0000 9.1131 0.1722 0.2735 0.0992 9.9827 0.0697 0.0384 0.3086 -0.1430 0.2423 9.2710 0.6540 10.0000 10.0000 9.0866 0.1419 0.2616 0.0993 9.7410 0.0650 0.0333 0.2947 -0.1516 0.2337 9.4907 0.6105 10.0000 10.0000 9.0583 0.1135 0.2500 0.0995 9.5197 0.0607 0.0290 0.2813 -0.1605 0.2251 9.5505 0.5993 10.0000 10.0000 9.0403 0.1059 0.2469 0.0995 9.4611 0.0596 0.0280 0.2775 -0.1631 0.2225 9.6010 0.5897 10.0000 10.0000 9.0024 0.0992 0.2442 0.0995 9.4123 0.0587 0.0271 0.2740 -0.1654 0.2199 9.6515 0.5754 10.0000 10.0000 8.9429 0.0877 0.2407 0.0996 9.3639 0.0573 0.0258 0.2691 -0.1704 0.2164 9.7020 0.5542 10.0000 10.0000 8.8599 0.0693 0.2360 0.0996 9.3160 0.0552 0.0239 0.2624 -0.1793 0.2118 9.7525 0.5250 10.0000 10.0000 8.7592 0.0428 0.2300 0.0997 9.2686 0.0523 0.0215 0.2539 -0.1928 0.2059 9.8030 0.4857 10.0000 10.0000 8.4057 0.0063 0.2224 0.0997 9.2217 0.0484 0.0184 0.2433 -0.2118 0.1988 9.8535 0.4323 10.0000 10.0000 7.8970 -0.0444 0.2126 0.0998 9.1752 0.0431 0.0146 0.2299 -0.2387 0.1901 9.9040 0.3537 10.0000 10.0000 7.3767 -0.1201 0.1988 0.0998 9.1292 0.0353 0.0098 0.2118 -0.2795 0.1789 9.9545 0.1993 10.0000 10.0000 7.2931 -0.2708 0.1731 0.0999 9.0837 0.0199 0.0031 0.1797 -0.3617 0.1608 10.0000 0.0262 10.0000 10.0050 10.0050 -0.4405 0.1448 0.1000 9.0475 0.0026 0.0000 0.1448 0.0000 0.0000 RADIUS: 10.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.60 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.221805 TOTAL WEIGHT (Kg) = 0.100592 TOTAL VOLUME (IN**3) = 3.613497 TOTAL PROJECTED AREA (IN**2) = 23.3769 MOMENT OF INERTIA (SNAIL-IN**2) = 0.010015 MOMENT OF INERTIA (Kg-M**2) = 0.001131 STATIC MOMENT, ONE SIDE (IN-LB) = 0.374194 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 = 73.400 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5572.35 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.60, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.76, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412