20x15(WCAR-T6) (20x15(WCAR-T6).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 2.0000 -3.1382 0.0000 0.0000 1.0000 0.0000 0.4968 0.0000 0.9936 0.0000 0.5000 0.0000 0.0000 0.1900 1.9642 -1.6665 0.0138 -0.4664 0.9810 0.0126 0.4767 0.6636 0.9364 1.4784 0.5006 0.0010 0.0457 0.3800 1.9013 -0.2956 0.1061 -0.8917 0.9460 0.0470 0.4579 2.5436 0.8706 1.4256 0.5022 -0.0014 0.0478 0.5700 1.8219 0.9793 0.3455 -1.2248 0.8993 0.0977 0.4402 5.5107 0.8020 1.3494 0.5045 -0.0048 0.0512 0.7600 1.7377 2.1632 0.7930 -1.3346 0.8457 0.1588 0.4237 9.4291 0.7362 1.2231 0.5068 -0.0051 0.0579 0.9500 1.6590 3.2608 1.4977 -1.1079 0.7894 0.2253 0.4082 14.0857 0.6771 1.0643 0.5089 -0.0019 0.0682 1.1400 1.5934 4.2768 2.4856 -0.4773 0.7346 0.2919 0.3937 19.1377 0.6273 0.8978 0.5111 0.0044 0.0821 1.3300 1.5448 5.2158 3.7379 0.5601 0.6854 0.3536 0.3801 24.0988 0.5873 0.7435 0.5134 0.0136 0.0994 1.5200 1.5129 6.0825 5.1604 1.8969 0.6459 0.4053 0.3675 28.3836 0.5560 0.6155 0.5161 0.0253 0.1189 1.7100 1.4935 6.8812 6.5543 3.2604 0.6202 0.4419 0.3558 31.3845 0.5314 0.5236 0.5187 0.0378 0.1377 1.9000 1.4819 7.6166 7.6132 4.2121 0.6125 0.4582 0.3449 32.5268 0.5111 0.4756 0.5199 0.0479 0.1501 2.0934 1.4736 8.3044 8.3044 4.7030 0.6171 0.4598 0.3346 32.2664 0.4930 0.4575 0.5193 0.0543 0.1559 2.3455 1.4634 9.1165 9.1165 5.2873 0.6226 0.4601 0.3222 31.7408 0.4715 0.4363 0.5179 0.0609 0.1633 2.6010 1.4534 9.8512 9.8512 5.8235 0.6275 0.4591 0.3108 31.0810 0.4518 0.4167 0.5159 0.0660 0.1706 2.8566 1.4436 10.5070 10.5070 6.3068 0.6315 0.4570 0.3006 30.3449 0.4339 0.3987 0.5131 0.0702 0.1774 3.1121 1.4338 11.0936 11.0936 6.7364 0.6348 0.4540 0.2912 29.5679 0.4175 0.3820 0.5098 0.0736 0.1837 3.3676 1.4236 11.6205 11.6205 7.1196 0.6373 0.4504 0.2827 28.7753 0.4024 0.3664 0.5059 0.0765 0.1894 3.6231 1.4129 12.0970 12.0970 7.4582 0.6390 0.4462 0.2749 27.9859 0.3884 0.3516 0.5014 0.0791 0.1945 3.8786 1.4013 12.5321 12.5321 7.7655 0.6399 0.4416 0.2674 27.2141 0.3747 0.3370 0.4963 0.0816 0.1990 4.1341 1.3886 12.9343 12.9343 8.0559 0.6401 0.4367 0.2598 26.4706 0.3608 0.3220 0.4906 0.0841 0.2030 4.3897 1.3745 13.3065 13.3065 8.3324 0.6395 0.4315 0.2523 25.7550 0.3468 0.3067 0.4843 0.0866 0.2064 4.6452 1.3590 13.6509 13.6509 8.5921 0.6381 0.4259 0.2448 25.0661 0.3327 0.2911 0.4773 0.0892 0.2092 4.9007 1.3422 13.9699 13.9699 8.8419 0.6359 0.4199 0.2373 24.4032 0.3185 0.2754 0.4697 0.0918 0.2115 5.1562 1.3240 14.2659 14.2659 9.0830 0.6329 0.4136 0.2298 23.7659 0.3042 0.2596 0.4616 0.0943 0.2132 5.4117 1.3046 14.5409 14.5409 9.3168 0.6292 0.4068 0.2222 23.1533 0.2899 0.2438 0.4527 0.0969 0.2142 5.6672 1.2837 14.7965 14.7965 9.5436 0.6247 0.3996 0.2147 22.5646 0.2756 0.2281 0.4433 0.0994 0.2146 5.9228 1.2615 15.0344 15.0344 9.7689 0.6194 0.3919 0.2072 21.9987 0.2614 0.2126 0.4333 0.1019 0.2143 6.1783 1.2380 15.2558 15.2558 9.9930 0.6134 0.3836 0.1997 21.4546 0.2472 0.1973 0.4226 0.1043 0.2133 6.4338 1.2131 15.4619 15.4619 10.2176 0.6065 0.3747 0.1922 20.9312 0.2331 0.1823 0.4114 0.1066 0.2116 6.6893 1.1869 15.6535 15.6535 10.4455 0.5989 0.3653 0.1846 20.4270 0.2191 0.1677 0.3995 0.1088 0.2092 6.9448 1.1596 15.8312 15.8312 10.6784 0.5905 0.3551 0.1771 19.9410 0.2054 0.1537 0.3870 0.1108 0.2059 7.2003 1.1313 15.9954 15.9954 10.9171 0.5813 0.3443 0.1696 19.4715 0.1919 0.1401 0.3739 0.1124 0.2019 7.4559 1.1022 16.1462 16.1462 11.1642 0.5714 0.3328 0.1621 19.0171 0.1786 0.1273 0.3601 0.1138 0.1970 7.7114 1.0721 16.2837 16.2837 11.4211 0.5607 0.3206 0.1546 18.5764 0.1657 0.1150 0.3458 0.1148 0.1913 7.9669 1.0410 16.4074 16.4074 11.6888 0.5492 0.3076 0.1470 18.1477 0.1531 0.1034 0.3308 0.1155 0.1848 8.2224 1.0090 16.5166 16.5166 11.9684 0.5369 0.2939 0.1395 17.7290 0.1408 0.0925 0.3153 0.1158 0.1775 8.4779 0.9761 16.6105 16.6105 12.2608 0.5239 0.2794 0.1320 17.3188 0.1288 0.0823 0.2991 0.1158 0.1693 8.7334 0.9423 16.6895 16.6895 12.5674 0.5100 0.2642 0.1245 16.9168 0.1173 0.0727 0.2823 0.1153 0.1603 8.9890 0.9075 16.7540 16.7540 12.8892 0.4954 0.2482 0.1170 16.5224 0.1062 0.0639 0.2649 0.1145 0.1505 9.2445 0.8718 16.8037 16.8037 13.2273 0.4800 0.2314 0.1095 16.1350 0.0955 0.0557 0.2468 0.1133 0.1398 9.4893 0.8314 16.8374 16.8374 13.5674 0.4595 0.2132 0.1024 15.7695 0.0851 0.0479 0.2275 0.1088 0.1279 9.5505 0.8105 16.8436 16.8436 13.6547 0.4439 0.2057 0.1006 15.6790 0.0815 0.0448 0.2195 0.1019 0.1230 9.6010 0.7875 16.8481 16.8481 13.7270 0.4256 0.1979 0.0991 15.6045 0.0781 0.0418 0.2113 0.0931 0.1180 9.6515 0.7588 16.8519 16.8519 13.8097 0.4017 0.1887 0.0977 15.5301 0.0741 0.0384 0.2015 0.0811 0.1121 9.7020 0.7236 16.8552 16.8552 13.9077 0.3716 0.1777 0.0962 15.4560 0.0696 0.0345 0.1898 0.0655 0.1050 9.7525 0.6805 16.8578 16.8578 14.0167 0.3338 0.1647 0.0947 15.3820 0.0645 0.0301 0.1761 0.0456 0.0966 9.8030 0.6274 16.8598 16.8598 14.1427 0.2864 0.1492 0.0933 15.3082 0.0585 0.0253 0.1596 0.0202 0.0866 9.8535 0.5602 16.8611 16.8611 14.2994 0.2254 0.1300 0.0918 15.2346 0.0514 0.0200 0.1393 -0.0130 0.0743 9.9040 0.4691 16.8618 16.8618 14.5256 0.1412 0.1048 0.0903 15.1610 0.0424 0.0139 0.1124 -0.0592 0.0581 9.9545 0.3082 16.8618 16.8618 15.0833 -0.0104 0.0615 0.0889 15.0877 0.0274 0.0060 0.0665 -0.1437 0.0306 10.0000 0.0380 16.8613 16.8699 16.8699 -0.2680 -0.0094 0.0875 15.0291 0.0033 0.0000 -0.0094 0.0000 0.0000 RADIUS: 10.00 PROPELLER RADIUS (IN) HUBRAD: 1.00 HUB RADIUS (IN) HUBTRA: 1.90 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.351376 TOTAL WEIGHT (Kg) = 0.159354 TOTAL VOLUME (IN**3) = 7.485706 TOTAL PROJECTED AREA (IN**2) = 23.8077 MOMENT OF INERTIA (SNAIL-IN**2) = 0.011230 MOMENT OF INERTIA (Kg-M**2) = 0.001268 STATIC MOMENT, ONE SIDE (IN-LB) = 0.456392 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.300 DENSITY (INPUT FILE, LB/IN**3) = 0.4694E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.4694E-01 ACTIVITY FACTOR = 79.376 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 14984.55 BASED ON MODULUS (MILLION) = 3.50 AND, MATERIAL DENSITY (S.G.) = 1.30 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.75, AS-16 (Transition Start, Airfoil 1) AIRFOIL2: 9.50, AS-9 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.