19x8E (19x8E.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 0.2500 0.0000 0.0000 0.2100 1.1894 8.0000 0.0235 -0.3403 0.6154 0.0160 0.3258 1.0207 0.3875 0.4187 0.2593 0.0231 0.0449 0.4200 1.1372 8.0000 0.1821 -0.5950 0.6077 0.0592 0.3191 3.9471 0.3629 0.4042 0.2834 0.0440 0.0593 0.6300 1.0997 8.0000 0.5886 -0.5659 0.6021 0.1228 0.3081 8.4575 0.3388 0.3772 0.3182 0.0648 0.0835 0.8400 1.0832 8.0000 1.3168 -0.1034 0.5989 0.2001 0.2926 14.0088 0.3169 0.3432 0.3610 0.0843 0.1155 1.0500 1.0911 8.0000 2.3808 0.8628 0.5982 0.2845 0.2726 19.8430 0.2975 0.3069 0.4090 0.1019 0.1535 1.2600 1.1221 8.0000 3.7168 2.2930 0.6001 0.3694 0.2484 25.1493 0.2787 0.2713 0.4594 0.1170 0.1957 1.4700 1.1706 8.0000 5.1768 3.9266 0.6048 0.4482 0.2247 29.2699 0.2630 0.2391 0.5087 0.1291 0.2398 1.6800 1.2290 8.0000 6.5423 5.4867 0.6125 0.5143 0.2037 31.7901 0.2504 0.2123 0.5529 0.1376 0.2830 1.8900 1.2900 8.0000 7.5611 6.6859 0.6233 0.5611 0.1854 32.4855 0.2391 0.1931 0.5869 0.1408 0.3209 2.1000 1.3490 8.0000 7.9961 7.2700 0.6375 0.5820 0.1694 31.2163 0.2286 0.1846 0.6049 0.1347 0.3468 2.3111 1.4048 8.0000 8.0000 7.3726 0.6524 0.5815 0.1557 28.8512 0.2187 0.1846 0.6077 0.1197 0.3585 2.5416 1.4583 8.0000 8.0000 7.4631 0.6650 0.5720 0.1432 26.6095 0.2088 0.1849 0.6017 0.1024 0.3613 2.7731 1.5015 8.0000 8.0000 7.5395 0.6741 0.5534 0.1329 24.6617 0.1996 0.1847 0.5867 0.0853 0.3546 3.0047 1.5348 8.0000 8.0000 7.5992 0.6795 0.5323 0.1249 22.9651 0.1916 0.1845 0.5692 0.0687 0.3448 3.2362 1.5585 8.0000 8.0000 7.6411 0.6816 0.5112 0.1187 21.4765 0.1850 0.1845 0.5516 0.0525 0.3343 3.4678 1.5733 8.0000 8.0000 7.6654 0.6805 0.4900 0.1143 20.1615 0.1799 0.1850 0.5341 0.0368 0.3232 3.6993 1.5797 8.0000 8.0000 7.6717 0.6763 0.4687 0.1115 18.9926 0.1761 0.1858 0.5165 0.0219 0.3116 3.9309 1.5781 8.0000 8.0000 7.6599 0.6693 0.4474 0.1099 17.9476 0.1734 0.1867 0.4988 0.0080 0.2995 4.1624 1.5691 8.0000 8.0000 7.6400 0.6595 0.4265 0.1088 17.0083 0.1707 0.1866 0.4811 -0.0051 0.2875 4.3940 1.5532 8.0000 8.0000 7.6140 0.6471 0.4062 0.1078 16.1600 0.1674 0.1848 0.4634 -0.0173 0.2756 4.6255 1.5309 8.0000 8.0000 7.5798 0.6323 0.3865 0.1068 15.3903 0.1635 0.1814 0.4456 -0.0286 0.2641 4.8571 1.5028 8.0000 8.0000 7.5435 0.6152 0.3673 0.1059 14.6891 0.1591 0.1764 0.4277 -0.0387 0.2528 5.0886 1.4692 8.0000 8.0000 7.5068 0.5961 0.3486 0.1050 14.0477 0.1543 0.1698 0.4099 -0.0477 0.2420 5.3202 1.4309 8.0000 8.0000 7.4711 0.5750 0.3305 0.1042 13.4590 0.1491 0.1619 0.3919 -0.0557 0.2315 5.5517 1.3881 8.0000 8.0000 7.4378 0.5522 0.3127 0.1035 12.9169 0.1436 0.1528 0.3740 -0.0625 0.2214 5.7833 1.3416 8.0000 8.0000 7.4083 0.5277 0.2953 0.1028 12.4161 0.1379 0.1428 0.3559 -0.0684 0.2115 6.0148 1.2918 8.0000 8.0000 7.3830 0.5018 0.2783 0.1022 11.9521 0.1320 0.1321 0.3378 -0.0734 0.2019 6.2464 1.2391 8.0000 8.0000 7.3619 0.4747 0.2615 0.1016 11.5211 0.1259 0.1211 0.3196 -0.0779 0.1922 6.4779 1.1842 8.0000 8.0000 7.3413 0.4464 0.2449 0.1011 11.1198 0.1197 0.1102 0.3014 -0.0824 0.1823 6.7095 1.1275 8.0000 8.0000 7.3210 0.4171 0.2284 0.1007 10.7451 0.1135 0.0997 0.2831 -0.0869 0.1720 6.9410 1.0696 8.0000 8.0000 7.3008 0.3870 0.2120 0.1003 10.3946 0.1073 0.0895 0.2647 -0.0916 0.1613 7.1726 1.0110 8.0000 8.0000 7.2808 0.3563 0.1957 0.1000 10.0660 0.1011 0.0798 0.2462 -0.0965 0.1503 7.4041 0.9521 8.0000 8.0000 7.2605 0.3252 0.1794 0.0997 9.7573 0.0949 0.0706 0.2277 -0.1017 0.1388 7.6357 0.8935 8.0000 8.0000 7.2401 0.2937 0.1631 0.0995 9.4669 0.0889 0.0621 0.2090 -0.1073 0.1270 7.8672 0.8357 8.0000 8.0000 7.2194 0.2620 0.1468 0.0994 9.1931 0.0830 0.0543 0.1903 -0.1133 0.1147 8.0988 0.7792 8.0000 8.0000 7.1984 0.2304 0.1303 0.0993 8.9345 0.0774 0.0472 0.1715 -0.1199 0.1020 8.3303 0.7246 8.0000 8.0000 7.1768 0.1989 0.1138 0.0993 8.6900 0.0719 0.0408 0.1526 -0.1270 0.0888 8.5619 0.6723 8.0000 8.0000 7.1541 0.1677 0.0972 0.0993 8.4585 0.0668 0.0352 0.1336 -0.1348 0.0752 8.7934 0.6229 8.0000 8.0000 7.1298 0.1370 0.0803 0.0994 8.2388 0.0619 0.0302 0.1145 -0.1433 0.0610 9.0154 0.5787 8.0000 8.0000 7.1031 0.1082 0.0640 0.0995 8.0387 0.0576 0.0261 0.0961 -0.1522 0.0469 9.0730 0.5678 8.0000 8.0000 7.0771 0.1009 0.0597 0.0996 7.9883 0.0565 0.0251 0.0910 -0.1547 0.0429 9.1210 0.5587 8.0000 8.0000 7.0355 0.0946 0.0561 0.0996 7.9468 0.0557 0.0243 0.0864 -0.1569 0.0391 9.1689 0.5451 8.0000 8.0000 6.9742 0.0837 0.0518 0.0997 7.9058 0.0543 0.0232 0.0806 -0.1616 0.0346 9.2169 0.5249 8.0000 8.0000 6.8938 0.0662 0.0466 0.0997 7.8652 0.0523 0.0215 0.0734 -0.1701 0.0292 9.2649 0.4972 8.0000 8.0000 6.7976 0.0410 0.0404 0.0998 7.8249 0.0496 0.0193 0.0646 -0.1828 0.0227 9.3129 0.4600 8.0000 8.0000 6.4137 0.0063 0.0328 0.0998 7.7851 0.0459 0.0165 0.0540 -0.2009 0.0153 9.3609 0.4094 8.0000 8.0000 5.9540 -0.0418 0.0235 0.0999 7.7457 0.0409 0.0131 0.0411 -0.2265 0.0065 9.4088 0.3350 8.0000 8.0000 5.4962 -0.1138 0.0110 0.0999 7.7067 0.0335 0.0088 0.0243 -0.2653 -0.0043 9.4568 0.1887 8.0000 8.0000 5.4860 -0.2570 -0.0111 0.1000 7.6680 0.0189 0.0028 -0.0043 -0.3434 -0.0206 9.5000 0.0248 8.0000 8.0040 8.0040 -0.4181 -0.0349 0.1000 7.6374 0.0025 0.0000 -0.0349 0.0000 0.0000 RADIUS: 9.50 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.10 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.190450 TOTAL WEIGHT (Kg) = 0.086372 TOTAL VOLUME (IN**3) = 3.102670 TOTAL PROJECTED AREA (IN**2) = 21.4368 MOMENT OF INERTIA (SNAIL-IN**2) = 0.007687 MOMENT OF INERTIA (Kg-M**2) = 0.000868 STATIC MOMENT, ONE SIDE (IN-LB) = 0.301546 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 = 73.340 INNER LIMIT (NORMALIZED BY RADIUS) = 0.066 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5785.72 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.10, E63 (Transition Start, Airfoil 1) AIRFOIL2: 6.08, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412