HAM-STD HS1-430 AIRFOIL (hs1430-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HAM-STD HS1-430 AIRFOIL (hs1430-il) Reynolds number: 100,000 Max Cl/Cd: 21.18 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1430-il-100000-n5.txt Download as CSV file: xf-hs1430-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.8514 0.07748 0.06883 -0.0859 0.9778 0.1613
-14.250 -0.8528 0.07411 0.06536 -0.0873 0.9756 0.1628
-14.000 -0.8363 0.07316 0.06447 -0.0873 0.9708 0.1639
-13.750 -0.8308 0.07109 0.06236 -0.0875 0.9669 0.1653
-13.500 -0.8352 0.06813 0.05928 -0.0875 0.9638 0.1669
-13.250 -0.8503 0.06473 0.05569 -0.0862 0.9600 0.1687
-13.000 -0.8754 0.06137 0.05210 -0.0824 0.9533 0.1705
-12.750 -0.8980 0.05785 0.04823 -0.0792 0.9493 0.1727
-12.500 -0.9038 0.05624 0.04651 -0.0756 0.9424 0.1740
-12.250 -0.8839 0.05555 0.04586 -0.0756 0.9386 0.1753
-12.000 -0.8647 0.05469 0.04498 -0.0756 0.9361 0.1768
-11.750 -0.8686 0.05373 0.04397 -0.0714 0.9279 0.1782
-11.500 -0.8592 0.05251 0.04264 -0.0698 0.9246 0.1801
-11.250 -0.8683 0.05131 0.04130 -0.0645 0.9164 0.1818
-11.000 -0.8753 0.04993 0.03971 -0.0595 0.9090 0.1838
-10.750 -0.8660 0.04863 0.03824 -0.0573 0.9040 0.1859
-10.500 -0.8555 0.04815 0.03779 -0.0546 0.8956 0.1871
-10.250 -0.8316 0.04741 0.03705 -0.0547 0.8921 0.1890
-10.000 -0.8258 0.04680 0.03639 -0.0512 0.8833 0.1907
-9.750 -0.8046 0.04581 0.03529 -0.0507 0.8799 0.1932
-9.500 -0.8023 0.04508 0.03442 -0.0466 0.8706 0.1953
-9.250 -0.7867 0.04389 0.03294 -0.0451 0.8663 0.1981
-9.000 -0.7704 0.04343 0.03253 -0.0434 0.8584 0.1996
-8.750 -0.7449 0.04283 0.03199 -0.0433 0.8531 0.2014
-8.500 -0.7151 0.04210 0.03126 -0.0441 0.8501 0.2037
-8.250 -0.7056 0.04178 0.03090 -0.0411 0.8412 0.2057
-8.000 -0.6832 0.04109 0.03013 -0.0405 0.8367 0.2083
-7.750 -0.6572 0.04024 0.02912 -0.0405 0.8337 0.2112
-7.500 -0.6426 0.03981 0.02858 -0.0384 0.8269 0.2134
-7.250 -0.6195 0.03938 0.02825 -0.0378 0.8209 0.2153
-7.000 -0.5898 0.03877 0.02767 -0.0385 0.8175 0.2177
-6.750 -0.5576 0.03804 0.02694 -0.0395 0.8149 0.2204
-6.500 -0.5414 0.03779 0.02666 -0.0376 0.8075 0.2228
-6.250 -0.5203 0.03740 0.02620 -0.0366 0.8015 0.2256
-6.000 -0.4920 0.03677 0.02545 -0.0369 0.7980 0.2286
-5.750 -0.4572 0.03599 0.02470 -0.0384 0.7954 0.2313
-5.500 -0.4198 0.03521 0.02397 -0.0403 0.7933 0.2341
-5.250 -0.4120 0.03538 0.02417 -0.0369 0.7828 0.2361
-5.000 -0.3826 0.03487 0.02366 -0.0373 0.7782 0.2393
-4.750 -0.3472 0.03416 0.02291 -0.0388 0.7748 0.2430
-4.500 -0.3075 0.03334 0.02199 -0.0410 0.7719 0.2468
-4.250 -0.2948 0.03335 0.02199 -0.0383 0.7619 0.2492
-4.000 -0.2636 0.03274 0.02146 -0.0391 0.7554 0.2524
-3.750 -0.2251 0.03199 0.02074 -0.0411 0.7510 0.2562
-3.500 -0.1805 0.03114 0.01988 -0.0443 0.7475 0.2608
-3.250 -0.1717 0.03136 0.02011 -0.0409 0.7375 0.2638
-3.000 -0.1443 0.03105 0.01976 -0.0409 0.7304 0.2675
-2.750 -0.1035 0.03034 0.01902 -0.0433 0.7251 0.2718
-2.500 -0.0575 0.02948 0.01823 -0.0469 0.7202 0.2768
-2.250 -0.0577 0.02989 0.01871 -0.0417 0.7088 0.2797
-2.000 -0.0256 0.02945 0.01827 -0.0425 0.7010 0.2846
-1.750 0.0254 0.02860 0.01735 -0.0469 0.6947 0.2904
-1.500 0.0214 0.02913 0.01791 -0.0409 0.6820 0.2931
-1.250 0.0541 0.02864 0.01744 -0.0418 0.6723 0.2984
-1.000 0.0766 0.02842 0.01730 -0.0409 0.6627 0.3039
-0.750 0.0886 0.02855 0.01748 -0.0380 0.6521 0.3091
-0.500 0.1215 0.02815 0.01705 -0.0389 0.6434 0.3165
0.000 0.1496 0.02827 0.01730 -0.0339 0.6210 0.3301
0.250 0.1686 0.02820 0.01728 -0.0324 0.6095 0.3401
0.750 0.1971 0.02827 0.01754 -0.0276 0.5816 0.3698
1.000 0.2138 0.02812 0.01753 -0.0256 0.5650 0.4000
1.250 0.2246 0.02808 0.01776 -0.0227 0.5460 0.4506
1.500 0.2381 0.02780 0.01798 -0.0199 0.5251 0.5507
1.750 0.2551 0.02782 0.01823 -0.0177 0.5008 0.6427
2.000 0.2723 0.02809 0.01851 -0.0155 0.4753 0.6950
2.250 0.2885 0.02859 0.01898 -0.0133 0.4503 0.7356
2.500 0.3064 0.02933 0.01970 -0.0116 0.4256 0.7705
2.750 0.3280 0.03031 0.02064 -0.0107 0.4019 0.8019
3.000 0.3515 0.03141 0.02167 -0.0103 0.3811 0.8285
3.250 0.3752 0.03250 0.02266 -0.0100 0.3646 0.8512
3.500 0.3978 0.03359 0.02363 -0.0096 0.3519 0.8735
3.750 0.4219 0.03459 0.02455 -0.0094 0.3424 0.8951
4.000 0.4454 0.03555 0.02541 -0.0092 0.3347 0.9131
4.250 0.4647 0.03639 0.02612 -0.0082 0.3292 0.9289
4.500 0.5009 0.03725 0.02692 -0.0106 0.3238 0.9365
4.750 0.5268 0.03805 0.02763 -0.0110 0.3194 0.9496
5.000 0.5653 0.03888 0.02836 -0.0140 0.3153 0.9546
5.250 0.5991 0.03962 0.02898 -0.0161 0.3121 0.9613
5.500 0.6310 0.04033 0.02960 -0.0177 0.3093 0.9700
5.750 0.6705 0.04099 0.03022 -0.0210 0.3064 0.9746
6.000 0.7076 0.04167 0.03085 -0.0238 0.3035 0.9804
6.250 0.7435 0.04247 0.03158 -0.0264 0.3007 0.9872
6.500 0.7844 0.04314 0.03218 -0.0300 0.2980 0.9917
6.750 0.8266 0.04381 0.03274 -0.0339 0.2957 0.9967
7.000 0.8626 0.04432 0.03314 -0.0364 0.2939 1.0000
7.250 0.8737 0.04455 0.03333 -0.0343 0.2925 1.0000
7.500 0.8850 0.04482 0.03359 -0.0321 0.2911 1.0000
7.750 0.8964 0.04514 0.03390 -0.0300 0.2895 1.0000
8.000 0.9082 0.04549 0.03424 -0.0280 0.2880 1.0000
8.250 0.9211 0.04585 0.03457 -0.0262 0.2865 1.0000
8.500 0.9350 0.04620 0.03490 -0.0245 0.2852 1.0000
8.750 0.9490 0.04659 0.03526 -0.0229 0.2838 1.0000
9.000 0.9637 0.04698 0.03562 -0.0214 0.2825 1.0000
9.250 0.9794 0.04736 0.03595 -0.0200 0.2812 1.0000
9.500 0.9965 0.04773 0.03625 -0.0189 0.2798 1.0000
9.750 1.0167 0.04802 0.03646 -0.0182 0.2784 1.0000
10.000 1.0295 0.04861 0.03706 -0.0165 0.2771 1.0000
10.250 1.0387 0.04936 0.03786 -0.0145 0.2757 1.0000
10.500 1.0478 0.05014 0.03870 -0.0124 0.2742 1.0000
10.750 1.0563 0.05097 0.03957 -0.0104 0.2723 1.0000
11.000 1.0663 0.05177 0.04040 -0.0086 0.2706 1.0000
11.250 1.0781 0.05253 0.04115 -0.0071 0.2690 1.0000
11.500 1.0921 0.05319 0.04179 -0.0058 0.2673 1.0000
11.750 1.1096 0.05372 0.04226 -0.0050 0.2657 1.0000
12.000 1.1334 0.05402 0.04246 -0.0050 0.2641 1.0000
12.250 1.1303 0.05559 0.04417 -0.0020 0.2624 1.0000
12.500 1.1287 0.05718 0.04589 0.0007 0.2605 1.0000
12.750 1.1297 0.05871 0.04751 0.0029 0.2586 1.0000
13.000 1.1342 0.06009 0.04895 0.0047 0.2566 1.0000
13.250 1.1443 0.06118 0.05004 0.0059 0.2548 1.0000
13.500 1.1617 0.06185 0.05067 0.0064 0.2531 1.0000
13.750 1.1893 0.06197 0.05067 0.0060 0.2515 1.0000
14.000 1.1653 0.06536 0.05433 0.0098 0.2493 1.0000
14.250 1.1508 0.06841 0.05756 0.0124 0.2470 1.0000
14.500 1.1463 0.07085 0.06011 0.0141 0.2448 1.0000
14.750 1.1522 0.07254 0.06184 0.0150 0.2429 1.0000
15.000 1.1708 0.07324 0.06249 0.0151 0.2413 1.0000
15.250 1.1756 0.07512 0.06440 0.0159 0.2394 1.0000
15.500 1.1040 0.08397 0.07374 0.0198 0.2357 1.0000
15.750 1.0868 0.08826 0.07816 0.0208 0.2330 1.0000
16.000 1.1022 0.08925 0.07913 0.0208 0.2314 1.0000
16.250 1.1312 0.08890 0.07868 0.0204 0.2302 1.0000
17.750 0.6637 0.17795 0.16932 0.0004 0.1759 1.0000
18.000 0.6773 0.17933 0.17069 -0.0006 0.1746 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HAM-STD HS1-430 AIRFOIL (hs1430-il)