18x7WP (18x7WP.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 1.7500 3.8750 0.0000 0.0000 0.8750 0.0000 0.2571 0.0000 0.4500 0.0000 0.2000 0.0000 0.0000 0.2550 1.6723 4.3138 0.0180 -0.4566 0.8618 0.0118 0.2566 0.6446 0.4292 0.6449 0.2094 0.0242 -0.0180 0.5100 1.5952 4.7194 0.1392 -0.8321 0.8484 0.0432 0.2551 2.4878 0.4069 0.6201 0.2337 0.0519 -0.0042 0.7650 1.5240 5.0918 0.4517 -0.9735 0.8357 0.0887 0.2525 5.3687 0.3848 0.5835 0.2685 0.0808 0.0172 1.0200 1.4641 5.4310 1.0208 -0.7566 0.8246 0.1431 0.2489 9.0502 0.3644 0.5398 0.3103 0.1099 0.0443 1.2750 1.4193 5.7371 1.8769 -0.1025 0.8160 0.2011 0.2442 13.1860 0.3467 0.4932 0.3552 0.1384 0.0747 1.5300 1.3915 6.0100 2.9993 0.9994 0.8108 0.2576 0.2386 17.3279 0.3320 0.4468 0.3990 0.1656 0.1062 1.7850 1.3793 6.2497 4.2998 2.4642 0.8099 0.3071 0.2319 20.9761 0.3198 0.4034 0.4374 0.1908 0.1363 2.0400 1.3790 6.4562 5.6123 4.0919 0.8141 0.3446 0.2241 23.6467 0.3091 0.3648 0.4655 0.2134 0.1618 2.2950 1.3862 6.6296 6.6983 5.5673 0.8244 0.3647 0.2153 24.9156 0.2985 0.3323 0.4786 0.2324 0.1793 2.5500 1.3974 6.7698 7.2749 6.4923 0.8417 0.3622 0.2055 24.4205 0.2872 0.3069 0.4717 0.2467 0.1850 2.8020 1.4107 6.8757 7.4064 6.8221 0.8631 0.3448 0.1948 22.8157 0.2748 0.2883 0.4510 0.2579 0.1808 3.0031 1.4213 6.9370 7.4785 6.9370 0.8801 0.3319 0.1856 21.6203 0.2637 0.2769 0.4344 0.2677 0.1757 3.2012 1.4314 6.9772 7.5230 6.9773 0.8963 0.3202 0.1758 20.5070 0.2516 0.2662 0.4180 0.2777 0.1701 3.3993 1.4408 6.9974 7.5438 6.9975 0.9120 0.3086 0.1663 19.4532 0.2396 0.2552 0.4017 0.2874 0.1643 3.5974 1.4494 7.0000 7.5483 7.0001 0.9268 0.2959 0.1582 18.4667 0.2293 0.2459 0.3853 0.2968 0.1578 3.7955 1.4568 7.0000 7.5529 7.0002 0.9406 0.2824 0.1516 17.5735 0.2209 0.2381 0.3690 0.3057 0.1503 3.9936 1.4628 7.0000 7.5611 7.0002 0.9532 0.2678 0.1465 16.7690 0.2143 0.2320 0.3526 0.3143 0.1417 4.1917 1.4671 7.0000 7.5741 7.0002 0.9643 0.2522 0.1428 16.0441 0.2095 0.2275 0.3363 0.3223 0.1321 4.3898 1.4693 7.0000 7.5929 7.0002 0.9737 0.2355 0.1406 15.3914 0.2066 0.2246 0.3200 0.3297 0.1216 4.5879 1.4694 7.0000 7.6178 7.0001 0.9813 0.2179 0.1397 14.8027 0.2053 0.2231 0.3036 0.3364 0.1102 4.7860 1.4668 7.0000 7.6436 7.0001 0.9868 0.2003 0.1390 14.2615 0.2040 0.2212 0.2873 0.3423 0.0986 4.9841 1.4615 7.0000 7.6691 7.0001 0.9900 0.1829 0.1384 13.7604 0.2023 0.2185 0.2710 0.3472 0.0870 5.1822 1.4530 7.0000 7.6941 7.0001 0.9907 0.1659 0.1377 13.2951 0.2001 0.2149 0.2547 0.3511 0.0754 5.3803 1.4412 7.0000 7.7187 7.0001 0.9887 0.1492 0.1371 12.8617 0.1975 0.2103 0.2383 0.3538 0.0640 5.5784 1.4257 7.0000 7.7428 7.0001 0.9838 0.1328 0.1364 12.4569 0.1945 0.2048 0.2220 0.3553 0.0527 5.7766 1.4063 7.0000 7.7662 7.0001 0.9758 0.1168 0.1357 12.0777 0.1909 0.1983 0.2057 0.3554 0.0416 5.9747 1.3826 7.0000 7.7889 7.0001 0.9644 0.1012 0.1351 11.7216 0.1868 0.1907 0.1893 0.3541 0.0307 6.1728 1.3544 7.0000 7.8107 7.0001 0.9496 0.0859 0.1344 11.3863 0.1821 0.1822 0.1730 0.3513 0.0201 6.3709 1.3214 7.0000 7.8315 7.0001 0.9309 0.0711 0.1338 11.0697 0.1768 0.1726 0.1567 0.3469 0.0097 6.5690 1.2834 7.0000 7.8511 7.0001 0.9084 0.0566 0.1331 10.7700 0.1708 0.1620 0.1403 0.3407 -0.0003 6.7671 1.2400 7.0000 7.8692 7.0001 0.8817 0.0426 0.1324 10.4854 0.1642 0.1506 0.1240 0.3328 -0.0100 6.9652 1.1910 7.0000 7.8855 7.0001 0.8506 0.0291 0.1318 10.2143 0.1570 0.1383 0.1077 0.3230 -0.0193 7.1633 1.1361 7.0000 7.8997 7.0001 0.8149 0.0160 0.1311 9.9550 0.1490 0.1253 0.0913 0.3112 -0.0282 7.3614 1.0749 7.0000 7.9112 7.0001 0.7745 0.0034 0.1305 9.7061 0.1402 0.1117 0.0750 0.2973 -0.0367 7.5595 1.0073 7.0000 7.9191 7.0001 0.7291 -0.0087 0.1298 9.4657 0.1308 0.0977 0.0587 0.2813 -0.0448 7.7576 0.9330 7.0000 7.9224 7.0001 0.6784 -0.0202 0.1291 9.2319 0.1205 0.0835 0.0424 0.2631 -0.0524 7.9557 0.8516 6.9950 7.9140 6.9950 0.6224 -0.0313 0.1285 8.9965 0.1094 0.0694 0.0260 0.2425 -0.0595 8.1538 0.7629 6.9739 7.8804 6.9740 0.5608 -0.0419 0.1278 8.7446 0.0975 0.0555 0.0097 0.2196 -0.0661 8.3519 0.6665 6.9366 7.8159 6.9366 0.4933 -0.0519 0.1272 8.4714 0.0848 0.0424 -0.0067 0.1941 -0.0721 8.5420 0.5667 6.8853 7.7163 6.8854 0.4229 -0.0609 0.1265 8.1814 0.0717 0.0306 -0.0223 0.1672 -0.0774 8.5955 0.5373 6.8682 7.6796 6.8683 0.4021 -0.0634 0.1264 8.0930 0.0679 0.0276 -0.0267 0.1592 -0.0788 8.6409 0.5118 6.8527 7.6446 6.8528 0.3840 -0.0654 0.1262 8.0148 0.0646 0.0250 -0.0305 0.1523 -0.0800 8.6864 0.4859 6.8364 7.6056 6.8364 0.3656 -0.0675 0.1260 7.9333 0.0612 0.0226 -0.0342 0.1452 -0.0811 8.7318 0.4595 6.8191 7.5620 6.8192 0.3469 -0.0694 0.1259 7.8478 0.0579 0.0202 -0.0380 0.1380 -0.0822 8.7773 0.4325 6.8011 7.5132 6.8012 0.3276 -0.0714 0.1257 7.7578 0.0544 0.0179 -0.0418 0.1305 -0.0833 8.8227 0.3989 6.7821 7.4656 6.7831 0.3019 -0.0742 0.1256 7.6701 0.0501 0.0153 -0.0468 0.1197 -0.0850 8.8682 0.3538 6.7623 7.4645 6.8023 0.2649 -0.0783 0.1254 7.6301 0.0444 0.0120 -0.0540 0.1032 -0.0878 8.9136 0.2904 6.7417 7.5302 6.8690 0.2098 -0.0849 0.1253 7.6577 0.0364 0.0080 -0.0649 0.0775 -0.0926 8.9591 0.1762 6.7202 7.6848 7.1139 0.1045 -0.0983 0.1251 7.7738 0.0220 0.0029 -0.0862 0.0246 -0.1030 9.0000 0.0147 6.7000 6.7001 6.7000 -0.0482 -0.1193 0.1250 6.7571 0.0018 0.0000 -0.1193 0.0000 0.0000 RADIUS: 9.00 PROPELLER RADIUS (IN) HUBRAD: 0.88 HUB RADIUS (IN) HUBTRA: 2.55 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.289422 TOTAL WEIGHT (Kg) = 0.131257 TOTAL VOLUME (IN**3) = 4.715051 TOTAL PROJECTED AREA (IN**2) = 22.4088 MOMENT OF INERTIA (SNAIL-IN**2) = 0.010157 MOMENT OF INERTIA (Kg-M**2) = 0.001147 STATIC MOMENT, ONE SIDE (IN-LB) = 0.421509 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 = 84.482 INNER LIMIT (NORMALIZED BY RADIUS) = 0.097 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 8868.87 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.60, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 5.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.