19x8W (19x8W.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 1.7500 1.7240 0.0000 0.0000 0.8750 0.0000 -0.3631 0.0000 -0.6355 0.0000 0.2000 0.0000 0.0000 0.2700 1.6712 2.4293 0.0186 -0.4853 0.8624 0.0112 -0.2124 0.6270 -0.3549 0.6462 0.2103 0.0255 -0.0178 0.5400 1.5987 3.0906 0.1434 -0.9002 0.8519 0.0410 -0.0870 2.4201 -0.1391 0.6327 0.2371 0.0546 -0.0048 0.8100 1.5364 3.7081 0.4637 -1.1100 0.8439 0.0840 0.0150 5.2066 0.0230 0.6157 0.2759 0.0852 0.0148 1.0800 1.4878 4.2818 1.0423 -1.0083 0.8388 0.1353 0.0957 8.7326 0.1423 0.5963 0.3223 0.1159 0.0392 1.3499 1.4555 4.8116 1.9037 -0.5308 0.8369 0.1900 0.1571 12.6499 0.2287 0.5753 0.3716 0.1458 0.0664 1.6199 1.4397 5.2976 3.0226 0.3278 0.8387 0.2428 0.2014 16.5393 0.2899 0.5537 0.4193 0.1742 0.0942 1.8899 1.4383 5.7397 4.3135 1.5000 0.8444 0.2890 0.2305 19.9634 0.3315 0.5319 0.4607 0.2005 0.1201 2.1599 1.4471 6.1379 5.6273 2.8363 0.8545 0.3234 0.2465 22.5215 0.3567 0.5104 0.4910 0.2242 0.1413 2.4299 1.4608 6.4923 6.7579 4.1092 0.8693 0.3411 0.2516 23.8756 0.3675 0.4891 0.5051 0.2446 0.1545 2.6999 1.4754 6.8028 7.4602 5.0312 0.8891 0.3370 0.2476 23.7384 0.3654 0.4675 0.4983 0.2610 0.1565 2.9667 1.4894 7.0666 7.7670 5.5831 0.9118 0.3206 0.2369 22.6204 0.3529 0.4426 0.4770 0.2746 0.1515 3.1787 1.5006 7.2457 7.9625 5.9839 0.9297 0.3114 0.2250 21.7360 0.3376 0.4182 0.4600 0.2859 0.1490 3.3875 1.5112 7.3956 8.1159 6.3437 0.9468 0.3045 0.2112 20.8724 0.3192 0.3914 0.4433 0.2970 0.1474 3.5963 1.5212 7.5195 8.2324 6.6654 0.9633 0.2989 0.1965 20.0180 0.2989 0.3632 0.4264 0.3078 0.1461 3.8051 1.5302 7.6290 8.3261 6.9564 0.9788 0.2936 0.1817 19.2010 0.2780 0.3351 0.4096 0.3182 0.1445 4.0139 1.5379 7.7301 8.4076 7.2204 0.9933 0.2877 0.1678 18.4369 0.2580 0.3084 0.3927 0.3280 0.1418 4.2227 1.5442 7.8230 8.4820 7.4561 1.0065 0.2801 0.1557 17.7287 0.2405 0.2850 0.3758 0.3372 0.1377 4.4315 1.5486 7.9076 8.5560 7.6620 1.0181 0.2699 0.1465 17.0814 0.2269 0.2665 0.3589 0.3455 0.1315 4.6403 1.5509 7.9840 8.6369 7.8367 1.0280 0.2563 0.1410 16.5012 0.2187 0.2545 0.3419 0.3530 0.1228 4.8491 1.5508 8.0521 8.7300 7.9789 1.0359 0.2387 0.1397 15.9889 0.2166 0.2498 0.3248 0.3598 0.1114 5.0579 1.5481 8.1120 8.8184 8.0876 1.0416 0.2207 0.1390 15.5086 0.2152 0.2463 0.3078 0.3658 0.0995 5.2667 1.5424 8.1636 8.8981 8.1621 1.0449 0.2028 0.1384 15.0506 0.2134 0.2426 0.2907 0.3708 0.0874 5.4755 1.5334 8.2070 8.9693 8.2070 1.0455 0.1852 0.1377 14.6123 0.2112 0.2385 0.2736 0.3748 0.0753 5.6842 1.5208 8.2421 9.0316 8.2421 1.0433 0.1677 0.1370 14.1913 0.2084 0.2334 0.2564 0.3776 0.0634 5.8930 1.5043 8.2689 9.0849 8.2690 1.0381 0.1505 0.1364 13.7857 0.2052 0.2272 0.2392 0.3790 0.0517 6.1018 1.4837 8.2875 9.1293 8.2875 1.0296 0.1336 0.1357 13.3939 0.2014 0.2199 0.2220 0.3790 0.0403 6.3106 1.4587 8.2978 9.1645 8.2978 1.0175 0.1170 0.1351 13.0143 0.1970 0.2115 0.2047 0.3774 0.0291 6.5194 1.4289 8.2998 9.1905 8.2999 1.0017 0.1007 0.1344 12.6456 0.1921 0.2020 0.1874 0.3742 0.0183 6.7282 1.3940 8.2936 9.2071 8.2937 0.9820 0.0847 0.1338 12.2866 0.1865 0.1913 0.1701 0.3693 0.0078 6.9370 1.3538 8.2792 9.2140 8.2792 0.9582 0.0690 0.1331 11.9363 0.1802 0.1796 0.1527 0.3626 -0.0023 7.1458 1.3080 8.2565 9.2110 8.2565 0.9299 0.0538 0.1324 11.5935 0.1732 0.1669 0.1353 0.3540 -0.0121 7.3546 1.2562 8.2255 9.1979 8.2255 0.8971 0.0389 0.1318 11.2572 0.1655 0.1532 0.1178 0.3434 -0.0215 7.5634 1.1982 8.1863 9.1740 8.1863 0.8594 0.0244 0.1311 10.9264 0.1571 0.1388 0.1003 0.3307 -0.0305 7.7722 1.1337 8.1388 9.1390 8.1388 0.8167 0.0104 0.1305 10.5998 0.1479 0.1238 0.0828 0.3158 -0.0391 7.9810 1.0623 8.0830 9.0917 8.0831 0.7688 -0.0031 0.1298 10.2763 0.1379 0.1083 0.0653 0.2987 -0.0472 8.1898 0.9838 8.0190 9.0310 8.0191 0.7154 -0.0161 0.1291 9.9542 0.1270 0.0925 0.0477 0.2792 -0.0550 8.3986 0.8979 7.9369 8.9451 7.9370 0.6563 -0.0286 0.1285 9.6209 0.1154 0.0769 0.0301 0.2572 -0.0623 8.6074 0.8043 7.8131 8.8072 7.8131 0.5913 -0.0407 0.1278 9.2494 0.1028 0.0615 0.0124 0.2327 -0.0690 8.8162 0.7027 7.6464 8.6107 7.6465 0.5201 -0.0522 0.1272 8.8356 0.0894 0.0469 -0.0053 0.2056 -0.0752 9.0166 0.5974 7.4462 8.3573 7.4463 0.4459 -0.0626 0.1265 8.3916 0.0756 0.0339 -0.0223 0.1771 -0.0808 9.0730 0.5663 7.3828 8.2723 7.3829 0.4239 -0.0655 0.1263 8.2566 0.0716 0.0305 -0.0271 0.1686 -0.0822 9.1210 0.5394 7.3264 8.1944 7.3264 0.4048 -0.0679 0.1262 8.1374 0.0681 0.0277 -0.0312 0.1612 -0.0835 9.1689 0.5120 7.2677 8.1109 7.2677 0.3854 -0.0702 0.1260 8.0139 0.0645 0.0250 -0.0353 0.1537 -0.0847 9.2169 0.4842 7.2067 8.0209 7.2068 0.3656 -0.0725 0.1259 7.8855 0.0610 0.0224 -0.0394 0.1460 -0.0859 9.2649 0.4556 7.1435 7.9238 7.1436 0.3453 -0.0748 0.1257 7.7513 0.0573 0.0199 -0.0435 0.1380 -0.0871 9.3129 0.4202 7.0780 7.8193 7.0790 0.3182 -0.0779 0.1256 7.6113 0.0528 0.0169 -0.0489 0.1265 -0.0890 9.3609 0.3726 7.0103 7.7058 7.0553 0.2792 -0.0824 0.1254 7.4641 0.0467 0.0134 -0.0566 0.1084 -0.0921 9.4088 0.3058 6.9403 7.5810 7.1127 0.2211 -0.0892 0.1253 7.3075 0.0383 0.0091 -0.0680 0.0800 -0.0970 9.4568 0.1855 6.8680 7.4429 7.6576 0.1102 -0.1022 0.1251 7.1397 0.0232 0.0034 -0.0893 0.0228 -0.1071 9.5000 0.0155 6.8011 6.8011 6.8011 -0.0510 -0.1212 0.1250 6.5002 0.0019 0.0000 -0.1212 0.0000 0.0000 RADIUS: 9.50 PROPELLER RADIUS (IN) HUBRAD: 0.88 HUB RADIUS (IN) HUBTRA: 2.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.365265 TOTAL WEIGHT (Kg) = 0.165653 TOTAL VOLUME (IN**3) = 5.950626 TOTAL PROJECTED AREA (IN**2) = 24.6864 MOMENT OF INERTIA (SNAIL-IN**2) = 0.013951 MOMENT OF INERTIA (Kg-M**2) = 0.001576 STATIC MOMENT, ONE SIDE (IN-LB) = 0.565155 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 = 84.446 INNER LIMIT (NORMALIZED BY RADIUS) = 0.092 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 10124.30 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 5.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.