21.5x10.5PN (215x105PN.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 1.3500 -7.7531 0.0000 0.0000 0.6750 0.0000 0.3691 0.0000 0.4983 0.0000 0.2500 0.0000 0.0000 0.2200 1.3211 -5.7295 0.0191 -0.8854 0.6685 0.0081 0.3514 0.7909 0.4642 0.7635 0.2553 0.0049 -0.0823 0.4400 1.3010 -3.8247 0.1446 -1.6436 0.6702 0.0298 0.3344 2.9933 0.4350 0.7505 0.2692 0.0185 -0.0740 0.6600 1.2916 -2.0387 0.4574 -2.0946 0.6783 0.0616 0.3181 6.2944 0.4109 0.7258 0.2888 0.0375 -0.0617 0.8800 1.2947 -0.3716 1.0065 -2.1193 0.6915 0.1002 0.3027 10.3168 0.3919 0.6925 0.3121 0.0606 -0.0465 1.1000 1.3108 1.1766 1.8058 -1.6669 0.7084 0.1420 0.2880 14.6427 0.3775 0.6533 0.3369 0.0866 -0.0294 1.3200 1.3381 2.6060 2.8341 -0.7566 0.7274 0.1839 0.2741 18.8661 0.3667 0.6106 0.3612 0.1141 -0.0114 1.5400 1.3726 3.9166 4.0365 0.5249 0.7472 0.2224 0.2609 22.6442 0.3581 0.5669 0.3824 0.1418 0.0059 1.7600 1.4087 5.1083 5.3268 2.0274 0.7664 0.2541 0.2485 25.7200 0.3501 0.5247 0.3982 0.1678 0.0204 1.9800 1.4399 6.1812 6.5898 3.5419 0.7834 0.2756 0.2369 27.9100 0.3411 0.4869 0.4056 0.1898 0.0295 2.2000 1.4593 7.1352 7.6830 4.8040 0.7968 0.2837 0.2260 29.0660 0.3298 0.4562 0.4018 0.2048 0.0297 2.4226 1.4696 7.9794 8.5641 5.7839 0.8077 0.2812 0.2158 29.3637 0.3172 0.4309 0.3899 0.2134 0.0237 2.6890 1.4828 8.8302 9.4528 6.8932 0.8212 0.2752 0.2046 29.2260 0.3034 0.4022 0.3754 0.2213 0.0186 2.9581 1.4967 9.5123 10.1681 7.9017 0.8350 0.2667 0.1945 28.6821 0.2911 0.3755 0.3606 0.2272 0.0151 3.2271 1.5108 10.0167 10.7014 8.7580 0.8487 0.2561 0.1855 27.8240 0.2802 0.3517 0.3455 0.2313 0.0126 3.4961 1.5246 10.3433 11.0540 9.4284 0.8620 0.2438 0.1776 26.7122 0.2708 0.3312 0.3303 0.2342 0.0110 3.7652 1.5378 10.4922 11.2258 9.8863 0.8746 0.2300 0.1706 25.3851 0.2623 0.3135 0.3148 0.2359 0.0102 4.0342 1.5498 10.5048 11.2574 10.1523 0.8863 0.2156 0.1639 23.9470 0.2540 0.2981 0.2992 0.2372 0.0096 4.3032 1.5604 10.5079 11.2771 10.3407 0.8967 0.2013 0.1574 22.6402 0.2457 0.2847 0.2834 0.2389 0.0074 4.5723 1.5689 10.5101 11.2940 10.4600 0.9056 0.1870 0.1513 21.4612 0.2374 0.2733 0.2675 0.2407 0.0037 4.8413 1.5752 10.5114 11.3082 10.5101 0.9127 0.1727 0.1455 20.3926 0.2292 0.2636 0.2513 0.2425 -0.0014 5.1103 1.5787 10.5120 11.3201 10.5120 0.9177 0.1584 0.1400 19.4200 0.2211 0.2547 0.2350 0.2438 -0.0074 5.3794 1.5791 10.5117 11.3297 10.5117 0.9204 0.1440 0.1349 18.5313 0.2130 0.2454 0.2185 0.2445 -0.0140 5.6484 1.5760 10.5106 11.3374 10.5106 0.9203 0.1296 0.1300 17.7163 0.2049 0.2356 0.2018 0.2442 -0.0209 5.9174 1.5689 10.5086 11.3435 10.5086 0.9173 0.1150 0.1254 16.9666 0.1968 0.2253 0.1849 0.2428 -0.0282 6.1865 1.5575 10.5058 11.3481 10.5058 0.9111 0.1004 0.1212 16.2748 0.1887 0.2146 0.1678 0.2403 -0.0358 6.4555 1.5414 10.5022 11.3515 10.5022 0.9013 0.0856 0.1172 15.6349 0.1807 0.2033 0.1506 0.2364 -0.0437 6.7246 1.5201 10.4978 11.3540 10.4977 0.8878 0.0706 0.1136 15.0414 0.1727 0.1917 0.1331 0.2311 -0.0518 6.9936 1.4932 10.4925 11.3558 10.4924 0.8702 0.0555 0.1103 14.4898 0.1647 0.1796 0.1155 0.2242 -0.0601 7.2626 1.4604 10.4864 11.3572 10.4863 0.8482 0.0402 0.1073 13.9761 0.1567 0.1671 0.0977 0.2156 -0.0686 7.5317 1.4212 10.4795 11.3584 10.4794 0.8215 0.0248 0.1046 13.4968 0.1487 0.1543 0.0797 0.2052 -0.0772 7.8007 1.3752 10.4717 11.3596 10.4716 0.7899 0.0091 0.1022 13.0489 0.1406 0.1412 0.0615 0.1929 -0.0859 8.0697 1.3221 10.4631 11.3611 10.4630 0.7531 -0.0066 0.1002 12.6296 0.1324 0.1279 0.0432 0.1786 -0.0947 8.3388 1.2614 10.4537 11.3629 10.4536 0.7108 -0.0226 0.0984 12.2365 0.1241 0.1144 0.0246 0.1621 -0.1035 8.6078 1.1926 10.4435 11.3653 10.4434 0.6627 -0.0386 0.0969 11.8675 0.1156 0.1008 0.0059 0.1433 -0.1123 8.8768 1.1155 10.4324 11.3681 10.4323 0.6085 -0.0546 0.0958 11.5204 0.1069 0.0872 -0.0131 0.1222 -0.1212 9.1459 1.0296 10.4205 11.3714 10.4204 0.5479 -0.0707 0.0950 11.1933 0.0978 0.0737 -0.0322 0.0987 -0.1299 9.4149 0.9344 10.4078 11.3746 10.4077 0.4808 -0.0868 0.0945 10.8842 0.0883 0.0604 -0.0515 0.0725 -0.1385 9.6839 0.8296 10.3671 11.3495 10.3670 0.4066 -0.1028 0.0942 10.5658 0.0782 0.0475 -0.0710 0.0436 -0.1469 9.9530 0.7148 10.1815 11.1724 10.1814 0.3253 -0.1187 0.0939 10.1293 0.0671 0.0352 -0.0906 0.0119 -0.1545 10.2108 0.5949 9.8550 10.8421 9.8550 0.2403 -0.1335 0.0933 9.5920 0.0555 0.0243 -0.1097 -0.0214 -0.1612 10.2763 0.5629 9.7488 10.7322 9.7488 0.2176 -0.1373 0.0932 9.4371 0.0524 0.0217 -0.1145 -0.0302 -0.1628 10.3307 0.5359 9.6537 10.6328 9.6537 0.1984 -0.1403 0.0930 9.3030 0.0498 0.0197 -0.1186 -0.0377 -0.1642 10.3850 0.5084 9.5521 10.5259 9.5521 0.1789 -0.1434 0.0928 9.1636 0.0472 0.0177 -0.1226 -0.0454 -0.1656 10.4394 0.4804 9.4440 10.4110 9.4440 0.1590 -0.1464 0.0927 9.0188 0.0445 0.0158 -0.1267 -0.0531 -0.1669 10.4937 0.4520 9.3295 10.2880 9.3295 0.1388 -0.1494 0.0925 8.8686 0.0418 0.0140 -0.1307 -0.0610 -0.1683 10.5481 0.4213 9.2085 10.1569 9.2088 0.1166 -0.1527 0.0923 8.7129 0.0389 0.0121 -0.1352 -0.0699 -0.1698 10.6024 0.3784 9.0810 10.0184 9.0906 0.0823 -0.1577 0.0921 8.5526 0.0349 0.0098 -0.1418 -0.0855 -0.1727 10.6567 0.3157 8.9471 9.8717 8.9975 0.0285 -0.1653 0.0919 8.3867 0.0290 0.0068 -0.1520 -0.1119 -0.1776 10.7111 0.2054 8.8067 9.7161 9.0322 -0.0721 -0.1795 0.0917 8.2151 0.0188 0.0029 -0.1708 -0.1642 -0.1874 10.7600 0.0153 8.6749 8.6749 8.6749 -0.2527 -0.2048 0.0915 7.3119 0.0014 0.0000 -0.2048 0.0000 0.0000 RADIUS: 10.76 PROPELLER RADIUS (IN) HUBRAD: 0.68 HUB RADIUS (IN) HUBTRA: 2.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.381955 TOTAL WEIGHT (Kg) = 0.173222 TOTAL VOLUME (IN**3) = 6.222542 TOTAL PROJECTED AREA (IN**2) = 26.8990 MOMENT OF INERTIA (SNAIL-IN**2) = 0.016651 MOMENT OF INERTIA (Kg-M**2) = 0.001881 STATIC MOMENT, ONE SIDE (IN-LB) = 0.615062 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 = 75.013 INNER LIMIT (NORMALIZED BY RADIUS) = 0.063 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 7999.80 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.25, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.25, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.