HAM-STD HS1-620 AIRFOIL (hs1620-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-620 AIRFOIL (hs1620-il) Reynolds number: 100,000 Max Cl/Cd: 43.63 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1620-il-100000.txt Download as CSV file: xf-hs1620-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-620 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.7123 0.08801 0.08264 -0.0367 1.0000 0.1299
-9.000 -0.7381 0.08229 0.07683 -0.0349 1.0000 0.1294
-8.750 -0.7724 0.07415 0.06841 -0.0335 1.0000 0.1289
-8.500 -0.8161 0.06194 0.05532 -0.0322 1.0000 0.1296
-8.250 -0.8086 0.05991 0.05321 -0.0308 1.0000 0.1315
-8.000 -0.7870 0.06144 0.05498 -0.0295 0.9997 0.1335
-7.750 -0.7547 0.05744 0.05054 -0.0340 0.9931 0.1376
-7.500 -0.7351 0.05161 0.04385 -0.0367 0.9865 0.1425
-7.250 -0.6914 0.05253 0.04502 -0.0400 0.9811 0.1460
-7.000 -0.6646 0.05036 0.04250 -0.0415 0.9734 0.1509
-6.750 -0.6284 0.04852 0.04028 -0.0446 0.9687 0.1562
-6.500 -0.6007 0.04828 0.04013 -0.0452 0.9604 0.1601
-6.250 -0.5662 0.04649 0.03770 -0.0477 0.9561 0.1674
-6.000 -0.5403 0.04615 0.03755 -0.0481 0.9485 0.1712
-5.750 -0.5034 0.04577 0.03709 -0.0504 0.9432 0.1774
-5.500 -0.4757 0.04473 0.03574 -0.0513 0.9366 0.1839
-5.250 -0.4453 0.04462 0.03573 -0.0524 0.9307 0.1892
-5.000 -0.4039 0.04408 0.03477 -0.0554 0.9270 0.1983
-4.750 -0.3846 0.04359 0.03444 -0.0546 0.9184 0.2030
-4.500 -0.3474 0.04336 0.03412 -0.0568 0.9136 0.2115
-4.250 -0.3170 0.04285 0.03347 -0.0579 0.9079 0.2189
-4.000 -0.2902 0.04266 0.03332 -0.0583 0.9007 0.2262
-3.750 -0.2485 0.04225 0.03268 -0.0612 0.8968 0.2363
-3.500 -0.2283 0.04203 0.03257 -0.0605 0.8890 0.2429
-3.250 -0.1935 0.04184 0.03223 -0.0621 0.8833 0.2529
-3.000 -0.1499 0.04125 0.03169 -0.0653 0.8801 0.2630
-2.750 -0.1352 0.04135 0.03177 -0.0636 0.8707 0.2706
-2.500 -0.0962 0.04090 0.03126 -0.0659 0.8659 0.2812
-2.250 -0.0499 0.04047 0.03087 -0.0694 0.8629 0.2938
-2.000 -0.0391 0.04071 0.03104 -0.0670 0.8521 0.3010
-1.750 0.0061 0.04002 0.03049 -0.0702 0.8478 0.3141
-1.500 0.0307 0.03985 0.03028 -0.0698 0.8372 0.3245
-1.250 0.0817 0.03866 0.02921 -0.0734 0.8310 0.3406
-1.000 0.1119 0.03810 0.02875 -0.0736 0.8204 0.3540
-0.750 0.1572 0.03707 0.02781 -0.0762 0.8141 0.3731
-0.500 0.2077 0.03585 0.02679 -0.0796 0.8110 0.3980
-0.250 0.2210 0.03617 0.02725 -0.0774 0.7987 0.4187
0.000 0.2664 0.03481 0.02635 -0.0799 0.7947 0.4769
0.250 0.3074 0.03276 0.02601 -0.0790 0.7927 0.8720
0.500 0.4036 0.03214 0.02523 -0.0911 0.7896 1.0000
0.750 0.4153 0.03230 0.02526 -0.0882 0.7772 1.0000
1.000 0.4684 0.03087 0.02366 -0.0918 0.7745 1.0000
1.250 0.5287 0.02923 0.02187 -0.0967 0.7728 1.0000
1.500 0.5333 0.02965 0.02222 -0.0924 0.7583 1.0000
1.750 0.5960 0.02797 0.02042 -0.0978 0.7555 1.0000
2.000 0.6754 0.02607 0.01839 -0.1066 0.7531 1.0000
2.250 0.6827 0.02625 0.01852 -0.1023 0.7384 1.0000
2.500 0.7710 0.02441 0.01654 -0.1132 0.7333 1.0000
2.750 0.7872 0.02439 0.01647 -0.1105 0.7181 1.0000
3.000 0.8356 0.02366 0.01562 -0.1139 0.7054 1.0000
3.250 0.8874 0.02293 0.01473 -0.1181 0.6910 1.0000
3.500 0.9061 0.02290 0.01463 -0.1158 0.6725 1.0000
3.750 0.9285 0.02281 0.01443 -0.1142 0.6529 1.0000
4.000 0.9512 0.02275 0.01424 -0.1127 0.6318 1.0000
4.250 0.9733 0.02273 0.01407 -0.1111 0.6093 1.0000
4.500 0.9947 0.02280 0.01393 -0.1094 0.5858 1.0000
4.750 1.0044 0.02310 0.01412 -0.1055 0.5611 1.0000
5.000 1.0186 0.02343 0.01428 -0.1026 0.5377 1.0000
5.250 1.0352 0.02382 0.01447 -0.1003 0.5165 1.0000
5.500 1.0541 0.02427 0.01473 -0.0985 0.4975 1.0000
5.750 1.0760 0.02477 0.01503 -0.0974 0.4807 1.0000
6.000 1.1027 0.02529 0.01532 -0.0973 0.4657 1.0000
6.250 1.1168 0.02592 0.01592 -0.0948 0.4522 1.0000
6.500 1.1432 0.02654 0.01638 -0.0948 0.4403 1.0000
6.750 1.1656 0.02714 0.01689 -0.0940 0.4291 1.0000
7.000 1.1893 0.02783 0.01750 -0.0935 0.4191 1.0000
7.250 1.2133 0.02846 0.01805 -0.0931 0.4097 1.0000
7.500 1.2401 0.02920 0.01871 -0.0933 0.4011 1.0000
7.750 1.2581 0.02989 0.01940 -0.0917 0.3928 1.0000
8.000 1.2982 0.03066 0.01996 -0.0946 0.3848 1.0000
8.250 1.3052 0.03143 0.02089 -0.0909 0.3780 1.0000
8.500 1.3295 0.03215 0.02155 -0.0906 0.3708 1.0000
8.750 1.3641 0.03304 0.02233 -0.0925 0.3640 1.0000
9.000 1.3697 0.03390 0.02334 -0.0886 0.3581 1.0000
9.250 1.3920 0.03468 0.02410 -0.0880 0.3517 1.0000
9.500 1.4344 0.03566 0.02491 -0.0914 0.3452 1.0000
9.750 1.4321 0.03661 0.02609 -0.0862 0.3404 1.0000
10.000 1.4436 0.03754 0.02710 -0.0837 0.3349 1.0000
10.250 1.4836 0.03834 0.02775 -0.0865 0.3288 1.0000
10.500 1.4975 0.03954 0.02904 -0.0846 0.3239 1.0000
10.750 1.4934 0.04071 0.03042 -0.0794 0.3195 1.0000
11.000 1.5045 0.04174 0.03151 -0.0770 0.3145 1.0000
11.250 1.5539 0.04254 0.03210 -0.0815 0.3085 1.0000
11.500 1.5495 0.04398 0.03375 -0.0765 0.3047 1.0000
11.750 1.5397 0.04546 0.03546 -0.0708 0.3006 1.0000
12.000 1.5428 0.04675 0.03687 -0.0675 0.2962 1.0000
12.250 1.5767 0.04746 0.03747 -0.0690 0.2912 1.0000
12.500 1.5911 0.04901 0.03907 -0.0677 0.2870 1.0000
12.750 1.5671 0.05112 0.04148 -0.0605 0.2837 1.0000
13.000 1.5560 0.05310 0.04366 -0.0557 0.2799 1.0000
13.250 1.5630 0.05448 0.04510 -0.0535 0.2758 1.0000
13.500 1.6301 0.05452 0.04484 -0.0596 0.2704 1.0000
13.750 1.5832 0.05772 0.04844 -0.0504 0.2682 1.0000
14.000 1.5378 0.06169 0.05278 -0.0427 0.2654 1.0000
14.250 1.4993 0.06598 0.05734 -0.0369 0.2623 1.0000
14.500 1.4921 0.06860 0.06007 -0.0345 0.2586 1.0000
14.750 1.5960 0.06491 0.05596 -0.0416 0.2533 1.0000
15.000 1.5161 0.07185 0.06336 -0.0328 0.2515 1.0000
15.250 0.8097 0.18723 0.18009 -0.0636 0.2748 1.0000
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Polar data table (+)
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