20x10PN (20x10PN.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 -5.4358 0.0000 0.0000 0.6750 0.0000 0.5185 0.0000 0.7000 0.0000 0.2000 0.0000 0.0000 0.2140 1.2847 -3.7225 0.0200 -1.0080 0.6683 0.0051 0.5156 0.8534 0.6623 0.7550 0.2068 0.0213 -0.1323 0.4280 1.2386 -2.1100 0.1545 -1.9163 0.6688 0.0192 0.5067 3.2884 0.6276 0.7377 0.2250 0.0466 -0.1250 0.6420 1.2127 -0.5983 0.4943 -2.4930 0.6751 0.0399 0.4918 6.9860 0.5964 0.7198 0.2514 0.0712 -0.1130 0.8560 1.2077 0.8127 1.0930 -2.5757 0.6860 0.0655 0.4710 11.4874 0.5689 0.7011 0.2828 0.0948 -0.0974 1.0700 1.2227 2.1229 1.9598 -2.0958 0.7003 0.0937 0.4443 16.2521 0.5433 0.6812 0.3157 0.1172 -0.0795 1.2840 1.2538 3.3324 3.0593 -1.0831 0.7168 0.1226 0.4146 20.7673 0.5199 0.6595 0.3471 0.1381 -0.0606 1.4980 1.2948 4.4411 4.3168 0.3416 0.7342 0.1502 0.3864 24.6382 0.5003 0.6349 0.3736 0.1574 -0.0422 1.7120 1.3373 5.4491 5.6261 1.9821 0.7513 0.1744 0.3598 27.6109 0.4812 0.6068 0.3921 0.1748 -0.0260 1.9260 1.3730 6.3564 6.8560 3.5807 0.7669 0.1933 0.3348 29.5335 0.4597 0.5743 0.3997 0.1900 -0.0141 2.1400 1.3934 7.1628 7.8532 4.8272 0.7798 0.2048 0.3114 30.2872 0.4339 0.5370 0.3937 0.2024 -0.0089 2.3557 1.4022 7.8737 8.5997 5.7081 0.7908 0.2096 0.2893 30.1571 0.4057 0.4971 0.3784 0.2122 -0.0086 2.6004 1.4132 8.5564 9.3123 6.6512 0.8035 0.2112 0.2663 29.6809 0.3763 0.4549 0.3608 0.2217 -0.0086 2.8468 1.4251 9.1106 9.8877 7.5127 0.8165 0.2093 0.2452 28.9330 0.3494 0.4160 0.3429 0.2295 -0.0091 3.0932 1.4373 9.5313 10.3213 8.2573 0.8293 0.2044 0.2262 27.9708 0.3251 0.3809 0.3248 0.2358 -0.0100 3.3397 1.4495 9.8184 10.6148 8.8607 0.8418 0.1969 0.2093 26.8331 0.3033 0.3495 0.3065 0.2407 -0.0113 3.5861 1.4612 9.9719 10.7703 9.3032 0.8537 0.1869 0.1944 25.5479 0.2841 0.3222 0.2880 0.2445 -0.0129 3.8325 1.4720 10.0000 10.7985 9.5775 0.8647 0.1747 0.1817 24.1533 0.2675 0.2990 0.2694 0.2472 -0.0151 4.0789 1.4815 10.0000 10.7998 9.7686 0.8745 0.1610 0.1711 22.8505 0.2535 0.2801 0.2507 0.2497 -0.0191 4.3253 1.4894 10.0000 10.8049 9.9027 0.8830 0.1457 0.1626 21.6817 0.2422 0.2654 0.2318 0.2520 -0.0253 4.5717 1.4952 10.0000 10.8159 9.9797 0.8900 0.1289 0.1562 20.6330 0.2335 0.2549 0.2127 0.2539 -0.0336 4.8181 1.4986 10.0000 10.8348 10.0000 0.8950 0.1105 0.1518 19.6923 0.2276 0.2485 0.1934 0.2554 -0.0438 5.0646 1.4993 10.0000 10.8631 10.0000 0.8979 0.0905 0.1495 18.8487 0.2242 0.2448 0.1740 0.2563 -0.0557 5.3110 1.4967 10.0000 10.8938 10.0000 0.8985 0.0701 0.1478 18.0797 0.2212 0.2411 0.1544 0.2564 -0.0681 5.5574 1.4905 10.0000 10.9237 10.0000 0.8965 0.0499 0.1461 17.3717 0.2178 0.2363 0.1347 0.2556 -0.0806 5.8038 1.4803 10.0000 10.9527 10.0000 0.8917 0.0300 0.1444 16.7177 0.2137 0.2303 0.1147 0.2539 -0.0932 6.0502 1.4658 10.0000 10.9808 10.0000 0.8838 0.0102 0.1426 16.1117 0.2091 0.2231 0.0947 0.2512 -0.1059 6.2966 1.4464 10.0000 11.0078 10.0000 0.8725 -0.0092 0.1409 15.5484 0.2038 0.2146 0.0744 0.2474 -0.1185 6.5430 1.4218 10.0000 11.0337 9.9999 0.8576 -0.0285 0.1392 15.0234 0.1979 0.2048 0.0540 0.2424 -0.1311 6.7894 1.3916 10.0000 11.0584 9.9999 0.8389 -0.0474 0.1375 14.5326 0.1913 0.1938 0.0334 0.2360 -0.1435 7.0359 1.3554 10.0000 11.0818 9.9999 0.8161 -0.0661 0.1357 14.0727 0.1840 0.1815 0.0127 0.2283 -0.1557 7.2823 1.3128 10.0000 11.1038 9.9999 0.7890 -0.0844 0.1340 13.6405 0.1759 0.1681 -0.0082 0.2191 -0.1677 7.5287 1.2633 10.0000 11.1242 9.9999 0.7573 -0.1025 0.1323 13.2334 0.1671 0.1537 -0.0293 0.2083 -0.1795 7.7751 1.2066 10.0000 11.1429 9.9998 0.7207 -0.1203 0.1306 12.8489 0.1576 0.1385 -0.0506 0.1959 -0.1910 8.0215 1.1423 10.0000 11.1596 9.9999 0.6791 -0.1377 0.1288 12.4848 0.1472 0.1225 -0.0720 0.1818 -0.2022 8.2679 1.0700 10.0000 11.1738 9.9999 0.6322 -0.1549 0.1271 12.1389 0.1360 0.1061 -0.0936 0.1660 -0.2131 8.5143 0.9892 10.0000 11.1851 9.9999 0.5797 -0.1717 0.1254 11.8092 0.1240 0.0895 -0.1154 0.1482 -0.2237 8.7608 0.8996 10.0000 11.1926 9.9999 0.5214 -0.1882 0.1237 11.4935 0.1113 0.0731 -0.1373 0.1285 -0.2339 9.0072 0.8007 10.0000 11.1949 9.9999 0.4571 -0.2043 0.1219 11.1893 0.0976 0.0572 -0.1594 0.1068 -0.2438 9.2536 0.6922 9.9830 11.1723 9.9830 0.3864 -0.2202 0.1202 10.8771 0.0832 0.0422 -0.1816 0.0830 -0.2533 9.4898 0.5788 9.7682 10.9397 9.7682 0.3125 -0.2355 0.1186 10.3965 0.0686 0.0292 -0.2031 0.0580 -0.2615 9.5505 0.5481 9.6731 10.8370 9.6731 0.2925 -0.2394 0.1181 10.2369 0.0648 0.0261 -0.2087 0.0513 -0.2635 9.6010 0.5220 9.5816 10.7379 9.5816 0.2755 -0.2426 0.1178 10.0930 0.0615 0.0236 -0.2133 0.0455 -0.2651 9.6515 0.4956 9.4788 10.6263 9.4788 0.2583 -0.2459 0.1174 9.9389 0.0582 0.0212 -0.2179 0.0397 -0.2668 9.7020 0.4687 9.3647 10.5017 9.3647 0.2408 -0.2491 0.1171 9.7746 0.0549 0.0190 -0.2226 0.0338 -0.2684 9.7525 0.4413 9.2394 10.3639 9.2394 0.2229 -0.2523 0.1167 9.5997 0.0515 0.0168 -0.2272 0.0278 -0.2700 9.8030 0.4101 9.1028 10.2131 9.1035 0.2015 -0.2560 0.1164 9.4147 0.0477 0.0145 -0.2326 0.0199 -0.2720 9.8535 0.3666 8.9548 10.0499 8.9681 0.1681 -0.2616 0.1160 9.2202 0.0425 0.0116 -0.2406 0.0054 -0.2755 9.9040 0.3043 8.7957 9.8731 8.8600 0.1161 -0.2699 0.1157 9.0153 0.0352 0.0080 -0.2524 -0.0193 -0.2811 9.9545 0.1949 8.6252 9.6821 8.9090 0.0179 -0.2851 0.1153 8.7995 0.0225 0.0033 -0.2738 -0.0696 -0.2921 10.0000 0.0150 8.4621 8.4621 8.4621 -0.1511 -0.3105 0.1150 7.6704 0.0017 0.0000 -0.3105 0.0000 0.0000 RADIUS: 10.00 PROPELLER RADIUS (IN) HUBRAD: 0.68 HUB RADIUS (IN) HUBTRA: 2.14 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.385600 TOTAL WEIGHT (Kg) = 0.174875 TOTAL VOLUME (IN**3) = 6.281908 TOTAL PROJECTED AREA (IN**2) = 23.7219 MOMENT OF INERTIA (SNAIL-IN**2) = 0.015083 MOMENT OF INERTIA (Kg-M**2) = 0.001704 STATIC MOMENT, ONE SIDE (IN-LB) = 0.590775 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 = 77.587 INNER LIMIT (NORMALIZED BY RADIUS) = 0.068 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9913.43 BASED ON MODULUS (MILLION) = 2.80 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.