HAM-STD HS1-430 AIRFOIL (hs1430-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-430 AIRFOIL (hs1430-il) Reynolds number: 50,000 Max Cl/Cd: 14.2 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1430-il-50000-n5.txt Download as CSV file: xf-hs1430-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-430 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3836 0.13704 0.12759 -0.0532 0.9706 0.1988
-11.000 -0.3569 0.13616 0.12674 -0.0546 0.9657 0.2007
-10.500 -0.5637 0.10032 0.09035 -0.0635 0.9538 0.2141
-10.250 -0.5179 0.10167 0.09180 -0.0648 0.9501 0.2158
-10.000 -0.6049 0.09134 0.08119 -0.0617 0.9422 0.2188
-9.750 -0.6952 0.08341 0.07284 -0.0539 0.9354 0.2209
-9.500 -0.7562 0.07934 0.06849 -0.0442 0.9262 0.2225
-9.250 -0.7900 0.07598 0.06483 -0.0375 0.9182 0.2247
-9.000 -0.8132 0.07262 0.06108 -0.0321 0.9119 0.2274
-8.750 -0.8285 0.07005 0.05817 -0.0271 0.9048 0.2298
-8.500 -0.8098 0.06933 0.05752 -0.0265 0.8996 0.2317
-8.250 -0.7929 0.06851 0.05671 -0.0256 0.8943 0.2341
-8.000 -0.7793 0.06748 0.05563 -0.0243 0.8888 0.2368
-7.750 -0.7693 0.06625 0.05429 -0.0224 0.8824 0.2397
-7.500 -0.7534 0.06475 0.05257 -0.0216 0.8779 0.2430
-7.250 -0.7549 0.06358 0.05118 -0.0176 0.8702 0.2457
-7.000 -0.7399 0.06216 0.04947 -0.0165 0.8659 0.2489
-6.750 -0.7227 0.06161 0.04902 -0.0154 0.8594 0.2513
-6.500 -0.6998 0.06096 0.04840 -0.0153 0.8535 0.2541
-6.250 -0.6688 0.06009 0.04749 -0.0165 0.8495 0.2577
-6.000 -0.6628 0.05966 0.04699 -0.0135 0.8415 0.2603
-5.750 -0.6403 0.05886 0.04605 -0.0132 0.8361 0.2640
-5.500 -0.6102 0.05784 0.04480 -0.0143 0.8323 0.2683
-5.250 -0.6059 0.05754 0.04437 -0.0109 0.8229 0.2709
-5.000 -0.5734 0.05685 0.04381 -0.0122 0.8175 0.2743
-4.750 -0.5351 0.05609 0.04310 -0.0144 0.8138 0.2784
-4.500 -0.5291 0.05609 0.04311 -0.0113 0.8038 0.2814
-4.250 -0.5001 0.05551 0.04247 -0.0119 0.7979 0.2859
-4.000 -0.4637 0.05474 0.04157 -0.0137 0.7940 0.2910
-3.750 -0.4576 0.05488 0.04159 -0.0106 0.7842 0.2942
-3.500 -0.4282 0.05443 0.04125 -0.0113 0.7777 0.2984
-3.250 -0.3903 0.05384 0.04075 -0.0132 0.7735 0.3035
-3.000 -0.3672 0.05371 0.04065 -0.0129 0.7667 0.3084
-2.750 -0.3531 0.05385 0.04080 -0.0111 0.7572 0.3130
-2.500 -0.3183 0.05338 0.04025 -0.0125 0.7518 0.3189
-2.250 -0.2743 0.05259 0.03952 -0.0152 0.7478 0.3252
-2.000 -0.2703 0.05316 0.04019 -0.0119 0.7352 0.3293
-1.750 -0.2352 0.05258 0.03967 -0.0131 0.7279 0.3365
-1.500 -0.1866 0.05142 0.03847 -0.0161 0.7230 0.3458
-1.250 -0.1793 0.05178 0.03888 -0.0131 0.7079 0.3511
-1.000 -0.1352 0.05039 0.03763 -0.0151 0.6998 0.3608
-0.750 -0.0820 0.04853 0.03578 -0.0184 0.6951 0.3741
-0.500 -0.0860 0.04936 0.03671 -0.0137 0.6769 0.3810
-0.250 -0.0470 0.04806 0.03559 -0.0150 0.6715 0.3977
0.000 -0.0068 0.04675 0.03448 -0.0165 0.6677 0.4208
0.250 -0.0181 0.04806 0.03597 -0.0111 0.6499 0.4368
0.500 0.0129 0.04679 0.03517 -0.0108 0.6446 0.4828
1.000 0.0419 0.04690 0.03633 -0.0055 0.6219 0.6376
1.250 0.0894 0.04618 0.03588 -0.0070 0.6164 0.7208
1.750 0.1604 0.04747 0.03741 -0.0085 0.5910 0.8044
2.250 0.2321 0.04843 0.03829 -0.0104 0.5641 0.8555
2.500 0.2523 0.04977 0.03963 -0.0098 0.5445 0.8729
2.750 0.2845 0.05029 0.04007 -0.0106 0.5282 0.8906
3.000 0.3349 0.04981 0.03939 -0.0136 0.5157 0.9093
3.250 0.3742 0.05056 0.04001 -0.0157 0.4973 0.9289
3.500 0.4377 0.05087 0.04010 -0.0218 0.4797 0.9457
3.750 0.5031 0.05077 0.03967 -0.0282 0.4634 0.9585
4.000 0.5469 0.05142 0.04013 -0.0317 0.4467 0.9711
4.250 0.6003 0.05206 0.04054 -0.0373 0.4314 0.9818
4.500 0.6602 0.05251 0.04071 -0.0439 0.4185 0.9927
4.750 0.6976 0.05338 0.04148 -0.0472 0.4071 1.0000
5.000 0.7025 0.05356 0.04152 -0.0443 0.3999 1.0000
5.250 0.7150 0.05341 0.04115 -0.0424 0.3942 1.0000
5.500 0.7168 0.05392 0.04161 -0.0392 0.3880 1.0000
5.750 0.7206 0.05439 0.04202 -0.0362 0.3823 1.0000
6.000 0.7293 0.05466 0.04219 -0.0338 0.3773 1.0000
6.250 0.7442 0.05471 0.04206 -0.0323 0.3731 1.0000
6.500 0.7568 0.05499 0.04223 -0.0304 0.3692 1.0000
6.750 0.7585 0.05590 0.04316 -0.0274 0.3649 1.0000
7.000 0.7641 0.05667 0.04391 -0.0248 0.3609 1.0000
7.250 0.7742 0.05725 0.04443 -0.0228 0.3573 1.0000
7.500 0.7897 0.05761 0.04469 -0.0214 0.3541 1.0000
7.750 0.8115 0.05771 0.04465 -0.0208 0.3513 1.0000
8.000 0.8271 0.05824 0.04510 -0.0195 0.3487 1.0000
8.250 0.8199 0.06004 0.04702 -0.0158 0.3457 1.0000
8.500 0.8136 0.06191 0.04897 -0.0123 0.3426 1.0000
8.750 0.8100 0.06370 0.05083 -0.0093 0.3395 1.0000
9.000 0.8121 0.06520 0.05234 -0.0069 0.3366 1.0000
9.250 0.8229 0.06617 0.05326 -0.0053 0.3340 1.0000
9.500 0.8462 0.06635 0.05333 -0.0049 0.3316 1.0000
9.750 0.8659 0.06686 0.05373 -0.0043 0.3291 1.0000
10.000 0.7553 0.07748 0.06494 0.0059 0.3238 1.0000
10.250 0.6484 0.09113 0.07903 0.0115 0.3161 1.0000
10.500 0.6582 0.09250 0.08036 0.0125 0.3136 1.0000
10.750 0.6845 0.09199 0.07974 0.0130 0.3120 1.0000
11.250 0.5536 0.11502 0.10318 0.0151 0.2946 1.0000
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Polar data table (+)
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