20.5x10.5WPN (205x105WPN.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 -3.8415 0.0000 0.0000 0.6750 0.0000 0.3689 0.0000 0.4980 0.0000 0.3300 0.0000 0.0000 0.2150 1.3238 -2.3232 0.0230 -0.6476 0.6673 0.0159 0.3495 0.9755 0.4627 0.7392 0.3406 0.0056 0.0062 0.4300 1.3104 -0.8891 0.1729 -1.2130 0.6650 0.0588 0.3310 3.6607 0.4338 0.7523 0.3691 0.0114 0.0229 0.6450 1.3123 0.4606 0.5411 -1.5723 0.6671 0.1214 0.3135 7.6055 0.4114 0.7696 0.4098 0.0179 0.0477 0.8600 1.3313 1.7260 1.1751 -1.5158 0.6727 0.1964 0.2969 12.2691 0.3953 0.7617 0.4567 0.0262 0.0797 1.0750 1.3668 2.9070 2.0771 -0.9607 0.6808 0.2768 0.2813 17.0936 0.3845 0.7330 0.5060 0.0359 0.1160 1.2900 1.4150 4.0038 3.2075 0.0760 0.6905 0.3560 0.2666 21.5900 0.3772 0.6891 0.5540 0.0468 0.1534 1.5050 1.4692 5.0162 4.4897 1.4905 0.7008 0.4272 0.2529 25.3979 0.3715 0.6360 0.5966 0.0586 0.1888 1.7200 1.5205 5.9443 5.8155 3.1029 0.7107 0.4838 0.2401 28.2856 0.3650 0.5800 0.6288 0.0705 0.2181 1.9350 1.5599 6.7881 7.0482 4.6645 0.7194 0.5190 0.2282 30.1016 0.3560 0.5279 0.6450 0.0814 0.2366 2.1500 1.5785 7.5476 8.0229 5.8608 0.7258 0.5260 0.2173 30.7061 0.3430 0.4871 0.6393 0.0885 0.2381 2.3670 1.5813 8.2287 8.7331 6.6708 0.7303 0.5127 0.2073 30.4213 0.3278 0.4568 0.6178 0.0912 0.2270 2.6192 1.5843 8.9122 9.4446 7.5433 0.7347 0.4954 0.1968 29.8511 0.3118 0.4246 0.5929 0.0920 0.2150 2.8734 1.5867 9.4839 10.0413 8.3334 0.7381 0.4765 0.1876 29.0814 0.2977 0.3954 0.5682 0.0910 0.2040 3.1277 1.5881 9.9376 10.5182 9.0155 0.7406 0.4564 0.1797 28.1569 0.2854 0.3697 0.5437 0.0885 0.1938 3.3819 1.5881 10.2735 10.8764 9.5742 0.7421 0.4352 0.1731 27.1058 0.2749 0.3475 0.5197 0.0851 0.1843 3.6361 1.5864 10.4914 11.1169 9.9967 0.7427 0.4131 0.1678 25.9472 0.2661 0.3285 0.4960 0.0811 0.1755 3.8903 1.5826 10.5915 11.2372 10.2730 0.7423 0.3909 0.1627 24.6891 0.2576 0.3112 0.4726 0.0771 0.1677 4.1446 1.5768 10.5969 11.2605 10.4188 0.7410 0.3688 0.1579 23.3842 0.2490 0.2954 0.4496 0.0732 0.1604 4.3988 1.5696 10.5947 11.2744 10.5165 0.7387 0.3472 0.1533 22.1917 0.2405 0.2811 0.4269 0.0699 0.1521 4.6530 1.5609 10.5929 11.2873 10.5741 0.7355 0.3263 0.1488 21.1104 0.2322 0.2683 0.4046 0.0670 0.1430 4.9072 1.5509 10.5916 11.2992 10.5916 0.7313 0.3058 0.1445 20.1261 0.2241 0.2567 0.3826 0.0644 0.1330 5.1615 1.5394 10.5907 11.3104 10.5908 0.7262 0.2858 0.1404 19.2267 0.2161 0.2458 0.3610 0.0619 0.1226 5.4157 1.5265 10.5903 11.3209 10.5905 0.7201 0.2663 0.1364 18.4021 0.2082 0.2349 0.3397 0.0594 0.1119 5.6699 1.5123 10.5904 11.3308 10.5906 0.7130 0.2473 0.1326 17.6437 0.2006 0.2243 0.3187 0.0569 0.1011 5.9241 1.4966 10.5910 11.3403 10.5912 0.7050 0.2286 0.1290 16.9441 0.1931 0.2138 0.2981 0.0541 0.0901 6.1784 1.4796 10.5920 11.3495 10.5922 0.6961 0.2103 0.1256 16.2970 0.1859 0.2035 0.2779 0.0512 0.0790 6.4326 1.4612 10.5935 11.3585 10.5937 0.6862 0.1923 0.1224 15.6970 0.1788 0.1934 0.2580 0.0482 0.0678 6.6868 1.4413 10.5955 11.3674 10.5956 0.6754 0.1748 0.1193 15.1394 0.1720 0.1835 0.2384 0.0449 0.0566 6.9410 1.4199 10.5979 11.3764 10.5981 0.6636 0.1575 0.1164 14.6201 0.1653 0.1739 0.2192 0.0415 0.0454 7.1953 1.3949 10.6008 11.3852 10.6010 0.6508 0.1407 0.1137 14.1352 0.1586 0.1640 0.2003 0.0388 0.0344 7.4495 1.3661 10.6042 11.3940 10.6044 0.6371 0.1242 0.1112 13.6812 0.1519 0.1539 0.1818 0.0369 0.0238 7.7037 1.3333 10.6081 11.4026 10.6082 0.6225 0.1082 0.1088 13.2556 0.1451 0.1436 0.1636 0.0358 0.0135 7.9579 1.2967 10.6124 11.4112 10.6125 0.6069 0.0926 0.1067 12.8558 0.1383 0.1331 0.1458 0.0356 0.0035 8.2122 1.2561 10.6172 11.4198 10.6173 0.5903 0.0773 0.1047 12.4796 0.1315 0.1227 0.1283 0.0362 -0.0062 8.4664 1.2116 10.6224 11.4284 10.6225 0.5728 0.0625 0.1028 12.1250 0.1246 0.1122 0.1111 0.0375 -0.0156 8.7206 1.1632 10.6281 11.4370 10.6283 0.5543 0.0480 0.1012 11.7900 0.1177 0.1019 0.0943 0.0398 -0.0247 8.9748 1.1109 10.6343 11.4453 10.6344 0.5349 0.0339 0.0997 11.4732 0.1108 0.0917 0.0778 0.0428 -0.0335 9.2291 1.0547 10.6410 11.4532 10.6411 0.5146 0.0202 0.0984 11.1727 0.1038 0.0817 0.0617 0.0466 -0.0419 9.4833 0.9946 10.6481 11.4602 10.6482 0.4933 0.0068 0.0973 10.8870 0.0968 0.0719 0.0459 0.0512 -0.0500 9.7269 0.9191 10.5584 11.5566 10.5133 0.4574 -0.0057 0.0964 10.7077 0.0886 0.0609 0.0290 0.0484 -0.0587 9.7893 0.8864 10.4998 11.6256 10.4478 0.4354 -0.0102 0.0962 10.7032 0.0853 0.0565 0.0224 0.0407 -0.0623 9.8410 0.8537 10.4400 11.7004 10.3924 0.4117 -0.0146 0.0961 10.7152 0.0820 0.0523 0.0159 0.0314 -0.0658 9.8928 0.8154 10.3701 11.7930 10.3375 0.3825 -0.0198 0.0959 10.7427 0.0782 0.0476 0.0085 0.0191 -0.0699 9.9446 0.7705 10.2901 11.9046 10.2872 0.3469 -0.0259 0.0957 10.7869 0.0738 0.0425 -0.0002 0.0033 -0.0747 9.9963 0.7177 10.2001 12.0368 10.2479 0.3037 -0.0333 0.0956 10.8487 0.0686 0.0368 -0.0103 -0.0167 -0.0802 10.0481 0.6547 10.1000 12.1911 10.2306 0.2506 -0.0424 0.0955 10.9292 0.0625 0.0306 -0.0224 -0.0421 -0.0868 10.0999 0.5775 9.9898 12.3686 10.2565 0.1837 -0.0541 0.0954 11.0290 0.0551 0.0238 -0.0374 -0.0751 -0.0949 10.1516 0.4767 9.8696 12.5708 10.3885 0.0936 -0.0705 0.0952 11.1491 0.0454 0.0162 -0.0574 -0.1208 -0.1057 10.2034 0.3142 9.7392 12.7996 10.9947 -0.0567 -0.0991 0.0951 11.2907 0.0299 0.0071 -0.0910 -0.1998 -0.1237 10.2500 0.0394 9.6133 9.6134 9.6133 -0.3174 -0.1528 0.0950 8.4899 0.0037 0.0000 -0.1528 0.0000 0.0000 RADIUS: 10.25 PROPELLER RADIUS (IN) HUBRAD: 0.68 HUB RADIUS (IN) HUBTRA: 2.15 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.392599 TOTAL WEIGHT (Kg) = 0.178049 TOTAL VOLUME (IN**3) = 6.395936 TOTAL PROJECTED AREA (IN**2) = 26.5591 MOMENT OF INERTIA (SNAIL-IN**2) = 0.016633 MOMENT OF INERTIA (Kg-M**2) = 0.001879 STATIC MOMENT, ONE SIDE (IN-LB) = 0.620773 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 = 90.347 INNER LIMIT (NORMALIZED BY RADIUS) = 0.066 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9077.39 BASED ON MODULUS (MILLION) = 3.50 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.15, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.