21x10PN (21x10PN.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 -6.5750 0.0000 0.0000 0.6750 0.0000 0.3691 0.0000 0.4983 0.0000 0.2500 0.0000 0.0000 0.2200 1.3210 -4.7140 0.0195 -0.9056 0.6685 0.0086 0.3514 0.8102 0.4641 0.7742 0.2558 0.0049 -0.0864 0.4400 1.3006 -2.9624 0.1479 -1.6814 0.6702 0.0316 0.3344 3.0621 0.4349 0.7608 0.2708 0.0186 -0.0771 0.6600 1.2910 -1.3202 0.4673 -2.1432 0.6783 0.0652 0.3181 6.4297 0.4107 0.7353 0.2919 0.0378 -0.0633 0.8800 1.2940 0.2126 1.0269 -2.1692 0.6915 0.1056 0.3027 10.5213 0.3917 0.7008 0.3169 0.0611 -0.0463 1.1000 1.3104 1.6361 1.8394 -1.7079 0.7084 0.1493 0.2880 14.9029 0.3774 0.6602 0.3434 0.0871 -0.0272 1.3200 1.3382 2.9501 2.8807 -0.7805 0.7274 0.1926 0.2741 19.1535 0.3667 0.6160 0.3690 0.1147 -0.0075 1.5400 1.3733 4.1549 4.0911 0.5214 0.7472 0.2318 0.2609 22.9189 0.3583 0.5708 0.3910 0.1423 0.0111 1.7600 1.4098 5.2502 5.3780 2.0395 0.7664 0.2632 0.2485 25.9351 0.3504 0.5273 0.4067 0.1680 0.0265 1.9800 1.4410 6.2362 6.6183 3.5543 0.7834 0.2833 0.2369 28.0123 0.3414 0.4882 0.4130 0.1896 0.0357 2.2000 1.4600 7.1128 7.6602 4.7889 0.7968 0.2883 0.2260 28.9936 0.3300 0.4565 0.4067 0.2042 0.0350 2.4221 1.4698 7.8869 8.4706 5.7167 0.8077 0.2818 0.2158 29.1000 0.3172 0.4305 0.3914 0.2121 0.0272 2.6805 1.4821 8.6471 9.2668 6.7365 0.8208 0.2716 0.2050 28.8202 0.3038 0.4021 0.3733 0.2193 0.0195 2.9410 1.4952 9.2609 9.9122 7.6662 0.8341 0.2591 0.1951 28.2092 0.2917 0.3760 0.3548 0.2248 0.0129 3.2016 1.5087 9.7212 10.4005 8.4628 0.8474 0.2448 0.1863 27.3403 0.2811 0.3527 0.3362 0.2288 0.0069 3.4621 1.5221 10.0282 10.7327 9.0982 0.8604 0.2289 0.1786 26.2615 0.2718 0.3326 0.3174 0.2317 0.0014 3.7226 1.5351 10.1819 10.9091 9.5493 0.8727 0.2117 0.1717 25.0045 0.2635 0.3154 0.2984 0.2336 -0.0036 3.9831 1.5471 10.2021 10.9484 9.8182 0.8842 0.1937 0.1651 23.6279 0.2554 0.3003 0.2792 0.2351 -0.0082 4.2436 1.5578 10.2036 10.9667 10.0073 0.8945 0.1757 0.1588 22.3574 0.2474 0.2872 0.2599 0.2368 -0.0143 4.5041 1.5667 10.2048 10.9827 10.1337 0.9035 0.1578 0.1528 21.2101 0.2395 0.2759 0.2404 0.2386 -0.0218 4.7647 1.5736 10.2056 10.9966 10.1975 0.9109 0.1399 0.1471 20.1694 0.2316 0.2662 0.2207 0.2404 -0.0306 5.0252 1.5780 10.2059 11.0085 10.2060 0.9164 0.1221 0.1417 19.2215 0.2237 0.2576 0.2009 0.2420 -0.0405 5.2857 1.5795 10.2059 11.0187 10.2060 0.9197 0.1041 0.1366 18.3548 0.2158 0.2488 0.1809 0.2430 -0.0510 5.5462 1.5778 10.2055 11.0274 10.2056 0.9207 0.0862 0.1318 17.5597 0.2080 0.2395 0.1607 0.2431 -0.0618 5.8067 1.5724 10.2048 11.0348 10.2048 0.9189 0.0681 0.1273 16.8279 0.2001 0.2296 0.1404 0.2424 -0.0729 6.0672 1.5629 10.2036 11.0411 10.2036 0.9143 0.0500 0.1230 16.1525 0.1923 0.2193 0.1199 0.2407 -0.0844 6.3278 1.5489 10.2020 11.0465 10.2020 0.9064 0.0317 0.1191 15.5274 0.1844 0.2085 0.0992 0.2378 -0.0961 6.5883 1.5301 10.2001 11.0513 10.2000 0.8952 0.0134 0.1154 14.9477 0.1766 0.1973 0.0783 0.2337 -0.1080 6.8488 1.5060 10.1977 11.0558 10.1976 0.8802 -0.0052 0.1121 14.4087 0.1688 0.1856 0.0573 0.2283 -0.1201 7.1093 1.4763 10.1950 11.0601 10.1949 0.8613 -0.0238 0.1090 13.9067 0.1609 0.1734 0.0361 0.2215 -0.1323 7.3698 1.4406 10.1919 11.0644 10.1918 0.8381 -0.0427 0.1062 13.4383 0.1530 0.1609 0.0147 0.2132 -0.1447 7.6303 1.3984 10.1884 11.0689 10.1882 0.8105 -0.0616 0.1037 13.0005 0.1450 0.1481 -0.0069 0.2033 -0.1571 7.8909 1.3493 10.1845 11.0739 10.1843 0.7782 -0.0807 0.1015 12.5907 0.1370 0.1350 -0.0286 0.1917 -0.1696 8.1514 1.2930 10.1802 11.0795 10.1801 0.7409 -0.1000 0.0996 12.2065 0.1288 0.1217 -0.0505 0.1783 -0.1822 8.4119 1.2291 10.1755 11.0858 10.1754 0.6983 -0.1193 0.0980 11.8458 0.1204 0.1082 -0.0726 0.1630 -0.1947 8.6724 1.1571 10.1704 11.0928 10.1704 0.6502 -0.1387 0.0966 11.5067 0.1118 0.0946 -0.0949 0.1458 -0.2072 8.9329 1.0767 10.1650 11.1005 10.1649 0.5964 -0.1581 0.0956 11.1872 0.1029 0.0811 -0.1173 0.1266 -0.2197 9.1934 0.9874 10.1592 11.1086 10.1591 0.5366 -0.1775 0.0949 10.8856 0.0937 0.0677 -0.1399 0.1052 -0.2320 9.4540 0.8889 10.1529 11.1164 10.1529 0.4704 -0.1969 0.0944 10.5999 0.0839 0.0547 -0.1627 0.0816 -0.2442 9.7145 0.7808 10.0818 11.0577 10.0818 0.3978 -0.2161 0.0942 10.2684 0.0735 0.0421 -0.1856 0.0556 -0.2560 9.9642 0.6677 9.7909 10.7701 9.7909 0.3217 -0.2346 0.0939 9.7610 0.0627 0.0308 -0.2078 0.0284 -0.2663 10.0280 0.6373 9.6801 10.6582 9.6801 0.3013 -0.2392 0.0937 9.6011 0.0597 0.0280 -0.2135 0.0211 -0.2688 10.0811 0.6116 9.5768 10.5531 9.5768 0.2839 -0.2431 0.0936 9.4590 0.0573 0.0258 -0.2182 0.0149 -0.2708 10.1341 0.5854 9.4633 10.4371 9.4633 0.2663 -0.2470 0.0935 9.3088 0.0547 0.0236 -0.2230 0.0086 -0.2729 10.1871 0.5587 9.3396 10.3098 9.3396 0.2484 -0.2508 0.0934 9.1502 0.0522 0.0215 -0.2277 0.0022 -0.2750 10.2402 0.5277 9.2056 10.1721 9.2063 0.2263 -0.2552 0.0933 8.9839 0.0492 0.0191 -0.2333 -0.0065 -0.2774 10.2932 0.4863 9.0614 10.0242 9.0684 0.1940 -0.2611 0.0931 8.8105 0.0453 0.0163 -0.2407 -0.0208 -0.2810 10.3462 0.4309 8.9069 9.8656 8.9369 0.1481 -0.2689 0.0930 8.6295 0.0401 0.0128 -0.2507 -0.0426 -0.2861 10.3992 0.3528 8.7423 9.6959 8.8235 0.0798 -0.2798 0.0928 8.4406 0.0327 0.0086 -0.2647 -0.0768 -0.2934 10.4523 0.2079 8.5674 9.5174 8.8844 -0.0545 -0.2998 0.0926 8.2459 0.0193 0.0030 -0.2909 -0.1477 -0.3077 10.5000 0.0196 8.4012 8.4011 8.4012 -0.2326 -0.3254 0.0925 7.2570 0.0018 0.0000 -0.3254 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) = 0.381876 TOTAL WEIGHT (Kg) = 0.173187 TOTAL VOLUME (IN**3) = 6.221256 TOTAL PROJECTED AREA (IN**2) = 26.5742 MOMENT OF INERTIA (SNAIL-IN**2) = 0.016276 MOMENT OF INERTIA (Kg-M**2) = 0.001838 STATIC MOMENT, ONE SIDE (IN-LB) = 0.607835 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 = 80.224 INNER LIMIT (NORMALIZED BY RADIUS) = 0.064 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 8307.74 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.