20x8E (20x8E.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 8.0000 0.0000 0.0000 0.6250 0.0000 0.3280 0.0000 0.4100 0.0000 0.2100 0.0000 0.0000 0.2400 1.1859 8.0000 0.0269 -0.4873 0.6155 0.0180 0.3251 1.0239 0.3855 0.4177 0.2225 0.0230 0.0119 0.4800 1.1397 8.0000 0.2076 -0.8555 0.6109 0.0659 0.3164 3.9370 0.3606 0.4027 0.2547 0.0442 0.0342 0.7200 1.1156 8.0000 0.6624 -0.8635 0.6105 0.1358 0.3018 8.3302 0.3367 0.3789 0.3010 0.0638 0.0691 0.9600 1.1172 8.0000 1.4544 -0.3518 0.6139 0.2196 0.2815 13.5563 0.3144 0.3501 0.3570 0.0812 0.1131 1.2000 1.1448 8.0000 2.5713 0.7226 0.6205 0.3098 0.2562 18.8306 0.2933 0.3194 0.4183 0.0961 0.1629 1.4400 1.1949 8.0000 3.9213 2.2707 0.6299 0.3983 0.2324 23.4317 0.2777 0.2888 0.4799 0.1086 0.2151 1.6800 1.2603 8.0000 5.3451 4.0042 0.6415 0.4775 0.2113 26.8561 0.2662 0.2602 0.5362 0.1186 0.2659 1.9200 1.3327 8.0000 6.6403 5.5749 0.6548 0.5395 0.1925 28.8298 0.2566 0.2357 0.5815 0.1258 0.3107 2.1600 1.4044 8.0000 7.5912 6.7483 0.6693 0.5765 0.1761 29.2202 0.2473 0.2178 0.6090 0.1281 0.3433 2.4000 1.4702 8.0000 7.9964 7.3066 0.6844 0.5807 0.1618 27.9359 0.2379 0.2104 0.6119 0.1209 0.3551 2.6398 1.5272 8.0000 8.0000 7.3924 0.6981 0.5621 0.1496 25.7490 0.2285 0.2111 0.5975 0.1046 0.3501 2.8766 1.5731 8.0000 8.0000 7.4633 0.7079 0.5438 0.1394 23.8755 0.2193 0.2113 0.5832 0.0882 0.3443 3.1131 1.6090 8.0000 8.0000 7.5240 0.7141 0.5257 0.1309 22.2442 0.2107 0.2113 0.5688 0.0715 0.3375 3.3497 1.6353 8.0000 8.0000 7.5737 0.7170 0.5077 0.1240 20.8123 0.2028 0.2114 0.5544 0.0544 0.3297 3.5862 1.6527 8.0000 8.0000 7.6111 0.7166 0.4898 0.1186 19.5468 0.1960 0.2117 0.5401 0.0373 0.3212 3.8228 1.6615 8.0000 8.0000 7.6327 0.7132 0.4719 0.1144 18.4213 0.1901 0.2122 0.5257 0.0205 0.3121 4.0593 1.6623 8.0000 8.0000 7.6368 0.7069 0.4542 0.1115 17.4145 0.1853 0.2127 0.5113 0.0047 0.3027 4.2959 1.6556 8.0000 8.0000 7.6224 0.6977 0.4367 0.1096 16.5092 0.1814 0.2127 0.4969 -0.0100 0.2933 4.5324 1.6419 8.0000 8.0000 7.5872 0.6860 0.4195 0.1085 15.6910 0.1781 0.2119 0.4825 -0.0232 0.2842 4.7690 1.6217 8.0000 8.0000 7.5468 0.6718 0.4031 0.1075 14.9484 0.1743 0.2090 0.4682 -0.0350 0.2757 5.0055 1.5954 8.0000 8.0000 7.5064 0.6554 0.3873 0.1066 14.2715 0.1700 0.2040 0.4538 -0.0453 0.2679 5.2421 1.5636 8.0000 8.0000 7.4688 0.6367 0.3721 0.1057 13.6521 0.1653 0.1968 0.4394 -0.0540 0.2608 5.4786 1.5267 8.0000 8.0000 7.4356 0.6161 0.3576 0.1049 13.0834 0.1601 0.1878 0.4251 -0.0612 0.2545 5.7152 1.4853 8.0000 8.0000 7.4088 0.5937 0.3435 0.1041 12.5594 0.1547 0.1773 0.4107 -0.0669 0.2488 5.9517 1.4399 8.0000 8.0000 7.3867 0.5696 0.3299 0.1034 12.0751 0.1489 0.1658 0.3963 -0.0717 0.2433 6.1883 1.3909 8.0000 8.0000 7.3649 0.5440 0.3166 0.1028 11.6264 0.1430 0.1540 0.3820 -0.0762 0.2377 6.4248 1.3388 8.0000 8.0000 7.3431 0.5170 0.3036 0.1022 11.2093 0.1368 0.1421 0.3676 -0.0807 0.2319 6.6614 1.2842 8.0000 8.0000 7.3215 0.4887 0.2908 0.1017 10.8209 0.1306 0.1302 0.3532 -0.0852 0.2258 6.8979 1.2275 8.0000 8.0000 7.3001 0.4595 0.2783 0.1012 10.4581 0.1242 0.1186 0.3388 -0.0896 0.2195 7.1345 1.1692 8.0000 8.0000 7.2788 0.4293 0.2659 0.1008 10.1186 0.1178 0.1073 0.3245 -0.0942 0.2130 7.3710 1.1099 8.0000 8.0000 7.2576 0.3984 0.2537 0.1004 9.8003 0.1114 0.0964 0.3101 -0.0990 0.2061 7.6076 1.0499 8.0000 8.0000 7.2364 0.3669 0.2417 0.1001 9.5012 0.1051 0.0861 0.2957 -0.1040 0.1990 7.8441 0.9899 8.0000 8.0000 7.2152 0.3350 0.2297 0.0998 9.2197 0.0988 0.0764 0.2814 -0.1093 0.1916 8.0807 0.9303 8.0000 8.0000 7.1934 0.3027 0.2178 0.0996 8.9542 0.0927 0.0674 0.2670 -0.1151 0.1839 8.3172 0.8715 8.0000 8.0000 7.1710 0.2704 0.2060 0.0995 8.7035 0.0867 0.0591 0.2526 -0.1213 0.1759 8.5538 0.8142 8.0000 8.0000 7.1480 0.2381 0.1941 0.0994 8.4664 0.0809 0.0516 0.2382 -0.1280 0.1675 8.7903 0.7588 8.0000 8.0000 7.1241 0.2060 0.1823 0.0994 8.2417 0.0754 0.0448 0.2239 -0.1353 0.1588 9.0269 0.7057 8.0000 8.0000 7.0987 0.1742 0.1704 0.0994 8.0286 0.0701 0.0388 0.2095 -0.1433 0.1497 9.2634 0.6556 8.0000 8.0000 7.0713 0.1429 0.1584 0.0994 7.8261 0.0652 0.0335 0.1951 -0.1520 0.1402 9.4903 0.6106 8.0000 8.0000 7.0423 0.1135 0.1467 0.0996 7.6413 0.0608 0.0290 0.1814 -0.1611 0.1307 9.5505 0.5993 8.0000 8.0000 7.0241 0.1059 0.1436 0.0996 7.5937 0.0597 0.0280 0.1775 -0.1637 0.1279 9.6010 0.5896 8.0000 8.0000 6.9865 0.0991 0.1409 0.0996 7.5542 0.0588 0.0271 0.1739 -0.1660 0.1252 9.6515 0.5751 8.0000 8.0000 6.9270 0.0875 0.1376 0.0997 7.5151 0.0573 0.0258 0.1690 -0.1712 0.1216 9.7020 0.5537 8.0000 8.0000 6.8464 0.0688 0.1334 0.0997 7.4765 0.0552 0.0239 0.1626 -0.1802 0.1171 9.7525 0.5244 8.0000 8.0000 6.7464 0.0421 0.1281 0.0998 7.4382 0.0523 0.0214 0.1546 -0.1938 0.1115 9.8030 0.4851 8.0000 8.0000 6.4046 0.0054 0.1215 0.0998 7.4003 0.0484 0.0184 0.1446 -0.2130 0.1048 9.8535 0.4316 8.0000 8.0000 5.9038 -0.0456 0.1131 0.0999 7.3628 0.0431 0.0146 0.1323 -0.2401 0.0967 9.9040 0.3529 8.0000 8.0000 5.3924 -0.1217 0.1015 0.0999 7.3256 0.0353 0.0098 0.1160 -0.2811 0.0867 9.9545 0.1986 8.0000 8.0000 5.3169 -0.2730 0.0803 0.1000 7.2889 0.0199 0.0031 0.0877 -0.3638 0.0710 10.0000 0.0262 8.0000 8.0040 8.0040 -0.4427 0.0574 0.1000 7.2597 0.0026 0.0000 0.0574 0.0000 0.0000 RADIUS: 10.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.40 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.221594 TOTAL WEIGHT (Kg) = 0.100496 TOTAL VOLUME (IN**3) = 3.610055 TOTAL PROJECTED AREA (IN**2) = 23.8071 MOMENT OF INERTIA (SNAIL-IN**2) = 0.010069 MOMENT OF INERTIA (Kg-M**2) = 0.001137 STATIC MOMENT, ONE SIDE (IN-LB) = 0.375948 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) = 5605.30 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.40, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.75, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412