21x10.5PN (21x105PN.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 -7.7614 0.0000 0.0000 0.6750 0.0000 0.4205 0.0000 0.5676 0.0000 0.2500 0.0000 0.0000 0.2200 1.3204 -5.7594 0.0184 -0.9061 0.6685 0.0081 0.3969 0.7643 0.5240 0.7733 0.2558 0.0052 -0.0861 0.4400 1.2983 -3.8730 0.1399 -1.6857 0.6702 0.0300 0.3744 2.8978 0.4861 0.7580 0.2709 0.0196 -0.0760 0.6600 1.2856 -2.1022 0.4439 -2.1591 0.6783 0.0619 0.3531 6.1102 0.4540 0.7310 0.2925 0.0399 -0.0611 0.8800 1.2844 -0.4468 0.9799 -2.2048 0.6915 0.1006 0.3330 10.0495 0.4277 0.6952 0.3179 0.0646 -0.0428 1.1000 1.2953 1.0930 1.7642 -1.7679 0.7084 0.1426 0.3139 14.3189 0.4067 0.6537 0.3446 0.0921 -0.0225 1.3200 1.3172 2.5173 2.7788 -0.8631 0.7274 0.1844 0.2961 18.5232 0.3900 0.6088 0.3703 0.1212 -0.0017 1.5400 1.3464 3.8260 3.9719 0.4251 0.7472 0.2226 0.2793 22.3173 0.3761 0.5632 0.3921 0.1503 0.0177 1.7600 1.3778 5.0192 5.2588 1.9447 0.7664 0.2539 0.2637 25.4334 0.3634 0.5193 0.4074 0.1776 0.0334 1.9800 1.4053 6.0969 6.5244 3.4804 0.7834 0.2748 0.2493 27.6743 0.3503 0.4798 0.4132 0.2007 0.0424 2.2000 1.4226 7.0591 7.6242 4.7558 0.7968 0.2820 0.2360 28.8794 0.3357 0.4473 0.4067 0.2168 0.0411 2.4221 1.4318 7.9132 8.5130 5.7376 0.8077 0.2781 0.2237 29.2218 0.3203 0.4203 0.3914 0.2264 0.0324 2.6805 1.4435 8.7588 9.3928 6.8242 0.8208 0.2701 0.2109 29.1481 0.3044 0.3909 0.3733 0.2351 0.0238 2.9410 1.4562 9.4499 10.1141 7.8227 0.8341 0.2592 0.1995 28.6932 0.2906 0.3642 0.3548 0.2418 0.0163 3.2016 1.4693 9.9790 10.6704 8.6870 0.8474 0.2459 0.1898 27.9434 0.2789 0.3408 0.3362 0.2467 0.0093 3.4621 1.4823 10.3461 11.0629 9.3863 0.8604 0.2305 0.1817 26.9567 0.2693 0.3211 0.3174 0.2503 0.0029 3.7226 1.4948 10.5512 11.2920 9.8954 0.8727 0.2134 0.1748 25.7702 0.2613 0.3047 0.2984 0.2527 -0.0031 3.9831 1.5064 10.5972 11.3581 10.1983 0.8842 0.1955 0.1682 24.4105 0.2534 0.2903 0.2792 0.2543 -0.0083 4.2436 1.5167 10.5894 11.3679 10.3855 0.8945 0.1773 0.1620 23.0908 0.2457 0.2778 0.2599 0.2559 -0.0144 4.5041 1.5253 10.5809 11.3752 10.5072 0.9035 0.1592 0.1560 21.8974 0.2380 0.2670 0.2404 0.2578 -0.0219 4.7647 1.5318 10.5719 11.3803 10.5636 0.9109 0.1411 0.1503 20.8137 0.2303 0.2578 0.2207 0.2597 -0.0307 5.0252 1.5357 10.5623 11.3833 10.5623 0.9164 0.1230 0.1450 19.8255 0.2227 0.2496 0.2009 0.2613 -0.0405 5.2857 1.5367 10.5520 11.3845 10.5520 0.9197 0.1049 0.1399 18.9213 0.2151 0.2412 0.1809 0.2624 -0.0509 5.5462 1.5344 10.5411 11.3840 10.5412 0.9207 0.0867 0.1352 18.0911 0.2075 0.2323 0.1607 0.2627 -0.0617 5.8067 1.5283 10.5296 11.3822 10.5297 0.9189 0.0684 0.1308 17.3264 0.1999 0.2229 0.1404 0.2621 -0.0728 6.0672 1.5181 10.5175 11.3792 10.5175 0.9143 0.0501 0.1266 16.6203 0.1922 0.2130 0.1199 0.2606 -0.0841 6.3278 1.5034 10.5048 11.3753 10.5048 0.9064 0.0316 0.1228 15.9664 0.1846 0.2026 0.0992 0.2580 -0.0957 6.5883 1.4837 10.4915 11.3708 10.4914 0.8952 0.0130 0.1193 15.3596 0.1770 0.1917 0.0783 0.2543 -0.1075 6.8488 1.4587 10.4775 11.3658 10.4775 0.8802 -0.0057 0.1160 14.7952 0.1693 0.1803 0.0573 0.2492 -0.1195 7.1093 1.4278 10.4630 11.3605 10.4629 0.8613 -0.0245 0.1131 14.2693 0.1615 0.1684 0.0361 0.2429 -0.1315 7.3698 1.3908 10.4478 11.3553 10.4477 0.8381 -0.0435 0.1105 13.7783 0.1537 0.1561 0.0147 0.2350 -0.1437 7.6303 1.3473 10.4320 11.3502 10.4319 0.8105 -0.0626 0.1082 13.3193 0.1458 0.1434 -0.0069 0.2257 -0.1560 7.8909 1.2967 10.4156 11.3455 10.4155 0.7782 -0.0818 0.1062 12.8893 0.1377 0.1304 -0.0286 0.2147 -0.1683 8.1514 1.2387 10.3986 11.3413 10.3985 0.7409 -0.1010 0.1045 12.4860 0.1294 0.1171 -0.0505 0.2020 -0.1806 8.4119 1.1730 10.3809 11.3377 10.3808 0.6983 -0.1204 0.1031 12.1072 0.1209 0.1037 -0.0726 0.1875 -0.1929 8.6724 1.0990 10.3627 11.3347 10.3626 0.6502 -0.1397 0.1020 11.7507 0.1121 0.0901 -0.0949 0.1712 -0.2051 8.9329 1.0164 10.3438 11.3320 10.3438 0.5964 -0.1590 0.1012 11.4145 0.1028 0.0765 -0.1173 0.1528 -0.2173 9.1934 0.9247 10.3243 11.3293 10.3243 0.5366 -0.1783 0.1007 11.0966 0.0931 0.0630 -0.1399 0.1325 -0.2292 9.4540 0.8236 10.3042 11.3257 10.3042 0.4704 -0.1974 0.1005 10.7947 0.0828 0.0500 -0.1627 0.1100 -0.2410 9.7145 0.7127 10.2304 11.2655 10.2304 0.3978 -0.2163 0.1006 10.4572 0.0717 0.0375 -0.1856 0.0853 -0.2523 9.9642 0.5968 9.9759 11.0137 9.9759 0.3217 -0.2342 0.1006 9.9773 0.0600 0.0263 -0.2078 0.0593 -0.2623 10.0280 0.5656 9.8808 10.9167 9.8808 0.3013 -0.2387 0.1005 9.8294 0.0569 0.0237 -0.2135 0.0524 -0.2648 10.0811 0.5392 9.7925 10.8258 9.7924 0.2839 -0.2424 0.1005 9.6989 0.0542 0.0215 -0.2182 0.0465 -0.2668 10.1341 0.5123 9.6957 10.7253 9.6957 0.2663 -0.2461 0.1005 9.5611 0.0515 0.0194 -0.2230 0.0404 -0.2688 10.1871 0.4850 9.5905 10.6149 9.5905 0.2484 -0.2498 0.1004 9.4162 0.0487 0.0174 -0.2277 0.0343 -0.2708 10.2402 0.4572 9.4769 10.4945 9.4769 0.2302 -0.2535 0.1004 9.2638 0.0459 0.0155 -0.2325 0.0281 -0.2728 10.2932 0.4256 9.3548 10.3644 9.3555 0.2083 -0.2576 0.1003 9.1046 0.0427 0.0134 -0.2379 0.0200 -0.2752 10.3462 0.3811 9.2243 10.2251 9.2385 0.1738 -0.2637 0.1003 8.9389 0.0382 0.0108 -0.2459 0.0049 -0.2790 10.3992 0.3169 9.0854 10.0756 9.1442 0.1200 -0.2725 0.1002 8.7660 0.0317 0.0075 -0.2576 -0.0209 -0.2850 10.4523 0.2039 8.9380 9.9157 9.1907 0.0181 -0.2883 0.1001 8.5859 0.0204 0.0031 -0.2786 -0.0733 -0.2962 10.5000 0.0157 8.7982 8.7981 8.7982 -0.1591 -0.3148 0.1000 7.5960 0.0016 0.0000 -0.3148 0.0000 0.0000 RADIUS: 10.50 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) = 0.373361 TOTAL WEIGHT (Kg) = 0.169325 TOTAL VOLUME (IN**3) = 6.082527 TOTAL PROJECTED AREA (IN**2) = 25.6942 MOMENT OF INERTIA (SNAIL-IN**2) = 0.015632 MOMENT OF INERTIA (Kg-M**2) = 0.001765 STATIC MOMENT, ONE SIDE (IN-LB) = 0.587678 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 = 75.814 INNER LIMIT (NORMALIZED BY RADIUS) = 0.064 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 8385.34 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.