HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il) Reynolds number: 500,000 Max Cl/Cd: 120.84 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1708-il-500000-n5.txt Download as CSV file: xf-hs1708-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-708 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2878 0.09210 0.08970 -0.0574 0.9636 0.0080
-9.250 -0.2815 0.08750 0.08509 -0.0607 0.9510 0.0079
-8.750 -0.3466 0.02283 0.01875 -0.1306 0.8954 0.0068
-8.500 -0.3197 0.02021 0.01578 -0.1326 0.8896 0.0069
-8.250 -0.2924 0.01852 0.01381 -0.1338 0.8844 0.0070
-8.000 -0.2647 0.01723 0.01228 -0.1346 0.8791 0.0072
-7.750 -0.2369 0.01616 0.01097 -0.1353 0.8744 0.0074
-7.500 -0.2087 0.01527 0.00988 -0.1359 0.8704 0.0077
-7.250 -0.1802 0.01449 0.00893 -0.1364 0.8663 0.0080
-7.000 -0.1517 0.01384 0.00811 -0.1368 0.8625 0.0082
-6.750 -0.1231 0.01322 0.00732 -0.1372 0.8591 0.0086
-6.500 -0.0944 0.01260 0.00656 -0.1376 0.8559 0.0093
-6.250 -0.0655 0.01211 0.00595 -0.1379 0.8524 0.0100
-6.000 -0.0367 0.01168 0.00542 -0.1382 0.8489 0.0112
-5.750 -0.0079 0.01125 0.00492 -0.1385 0.8457 0.0138
-5.250 0.0498 0.01061 0.00420 -0.1391 0.8403 0.0243
-5.000 0.0787 0.01037 0.00395 -0.1394 0.8376 0.0297
-4.750 0.1075 0.01020 0.00373 -0.1396 0.8349 0.0340
-4.500 0.1364 0.01000 0.00352 -0.1398 0.8323 0.0382
-4.250 0.1652 0.00988 0.00334 -0.1400 0.8298 0.0429
-4.000 0.1941 0.00972 0.00317 -0.1402 0.8274 0.0479
-3.750 0.2231 0.00958 0.00302 -0.1405 0.8249 0.0521
-3.500 0.2521 0.00947 0.00287 -0.1407 0.8225 0.0560
-3.250 0.2811 0.00933 0.00275 -0.1409 0.8199 0.0632
-3.000 0.3099 0.00923 0.00263 -0.1411 0.8171 0.0697
-2.750 0.3386 0.00913 0.00252 -0.1413 0.8136 0.0769
-2.500 0.3673 0.00901 0.00241 -0.1414 0.8080 0.0840
-2.250 0.3958 0.00892 0.00230 -0.1414 0.8022 0.0927
-2.000 0.4244 0.00884 0.00223 -0.1415 0.7968 0.1020
-1.750 0.4530 0.00875 0.00217 -0.1417 0.7914 0.1129
-1.500 0.4815 0.00871 0.00210 -0.1417 0.7867 0.1237
-1.250 0.5102 0.00866 0.00208 -0.1418 0.7820 0.1341
-1.000 0.5388 0.00861 0.00205 -0.1419 0.7764 0.1435
-0.750 0.5672 0.00859 0.00202 -0.1420 0.7711 0.1539
-0.500 0.5958 0.00855 0.00202 -0.1421 0.7652 0.1640
-0.250 0.6243 0.00852 0.00201 -0.1422 0.7600 0.1725
0.000 0.6528 0.00852 0.00201 -0.1423 0.7555 0.1822
0.250 0.6813 0.00849 0.00203 -0.1424 0.7497 0.1918
0.500 0.7096 0.00847 0.00204 -0.1424 0.7434 0.2017
0.750 0.7380 0.00846 0.00206 -0.1425 0.7361 0.2127
1.000 0.7661 0.00846 0.00208 -0.1425 0.7278 0.2244
1.250 0.7943 0.00844 0.00212 -0.1425 0.7187 0.2378
1.500 0.8223 0.00843 0.00215 -0.1425 0.7090 0.2542
1.750 0.8501 0.00843 0.00220 -0.1425 0.6955 0.2762
2.000 0.8775 0.00838 0.00226 -0.1424 0.6749 0.3304
2.500 0.9196 0.00761 0.00248 -0.1396 0.5900 1.0000
2.750 0.9431 0.00807 0.00268 -0.1387 0.5456 1.0000
3.000 0.9672 0.00848 0.00291 -0.1380 0.5099 1.0000
3.250 0.9917 0.00887 0.00314 -0.1374 0.4767 1.0000
3.500 1.0151 0.00933 0.00341 -0.1367 0.4358 1.0000
3.750 1.0368 0.00994 0.00374 -0.1357 0.3832 1.0000
4.000 1.0596 0.01045 0.00405 -0.1348 0.3482 1.0000
4.250 1.0837 0.01084 0.00433 -0.1342 0.3242 1.0000
4.500 1.1073 0.01126 0.00462 -0.1335 0.2988 1.0000
4.750 1.1314 0.01162 0.00489 -0.1329 0.2777 1.0000
5.000 1.1552 0.01200 0.00519 -0.1323 0.2565 1.0000
5.250 1.1781 0.01244 0.00550 -0.1315 0.2304 1.0000
5.500 1.2006 0.01291 0.00585 -0.1306 0.2038 1.0000
5.750 1.2221 0.01346 0.00625 -0.1296 0.1748 1.0000
6.000 1.2426 0.01408 0.00672 -0.1284 0.1439 1.0000
6.250 1.2614 0.01484 0.00728 -0.1270 0.1076 1.0000
6.500 1.2798 0.01561 0.00787 -0.1255 0.0774 1.0000
6.750 1.2998 0.01622 0.00840 -0.1243 0.0627 1.0000
7.000 1.3206 0.01673 0.00891 -0.1231 0.0547 1.0000
7.250 1.3412 0.01723 0.00941 -0.1219 0.0491 1.0000
7.500 1.3612 0.01775 0.00993 -0.1206 0.0444 1.0000
7.750 1.3813 0.01822 0.01043 -0.1194 0.0410 1.0000
8.000 1.4000 0.01877 0.01099 -0.1179 0.0378 1.0000
8.250 1.4175 0.01938 0.01164 -0.1162 0.0349 1.0000
8.500 1.4352 0.01987 0.01220 -0.1145 0.0337 1.0000
8.750 1.4514 0.02041 0.01280 -0.1125 0.0323 1.0000
9.000 1.4672 0.02101 0.01345 -0.1106 0.0306 1.0000
9.250 1.4822 0.02169 0.01416 -0.1086 0.0289 1.0000
9.500 1.4955 0.02251 0.01501 -0.1064 0.0270 1.0000
9.750 1.5088 0.02332 0.01591 -0.1043 0.0259 1.0000
10.000 1.5236 0.02404 0.01671 -0.1024 0.0252 1.0000
10.250 1.5376 0.02483 0.01759 -0.1005 0.0244 1.0000
10.500 1.5508 0.02568 0.01852 -0.0986 0.0235 1.0000
10.750 1.5638 0.02657 0.01948 -0.0967 0.0225 1.0000
11.000 1.5762 0.02752 0.02048 -0.0949 0.0214 1.0000
11.250 1.5866 0.02864 0.02165 -0.0928 0.0202 1.0000
11.500 1.5943 0.03000 0.02310 -0.0906 0.0190 1.0000
11.750 1.6080 0.03089 0.02408 -0.0891 0.0183 1.0000
12.000 1.6199 0.03194 0.02522 -0.0875 0.0174 1.0000
12.250 1.6310 0.03306 0.02642 -0.0859 0.0164 1.0000
12.500 1.6409 0.03431 0.02773 -0.0843 0.0155 1.0000
12.750 1.6493 0.03572 0.02921 -0.0826 0.0147 1.0000
13.000 1.6550 0.03739 0.03096 -0.0807 0.0140 1.0000
13.250 1.6603 0.03914 0.03280 -0.0790 0.0134 1.0000
13.500 1.6671 0.04077 0.03457 -0.0774 0.0130 1.0000
13.750 1.6731 0.04253 0.03644 -0.0759 0.0124 1.0000
14.000 1.6783 0.04437 0.03839 -0.0745 0.0118 1.0000
14.250 1.6828 0.04631 0.04042 -0.0731 0.0112 1.0000
14.500 1.6861 0.04844 0.04263 -0.0719 0.0105 1.0000
14.750 1.6873 0.05086 0.04513 -0.0706 0.0099 1.0000
15.000 1.6868 0.05355 0.04794 -0.0695 0.0094 1.0000
15.250 1.6872 0.05621 0.05073 -0.0686 0.0090 1.0000
15.500 1.6866 0.05911 0.05375 -0.0679 0.0085 1.0000
15.750 1.6850 0.06223 0.05700 -0.0673 0.0080 1.0000
16.000 1.6822 0.06563 0.06052 -0.0671 0.0075 1.0000
16.250 1.6775 0.06943 0.06442 -0.0670 0.0071 1.0000
16.500 1.6707 0.07366 0.06878 -0.0673 0.0067 1.0000
16.750 1.6623 0.07832 0.07358 -0.0680 0.0064 1.0000
17.000 1.6539 0.08316 0.07859 -0.0689 0.0062 1.0000
17.250 1.6440 0.08838 0.08395 -0.0702 0.0060 1.0000
17.500 1.6327 0.09394 0.08967 -0.0718 0.0058 1.0000
17.750 1.6203 0.09983 0.09571 -0.0737 0.0056 1.0000
18.000 1.6066 0.10608 0.10211 -0.0760 0.0055 1.0000
18.250 1.5921 0.11264 0.10882 -0.0787 0.0053 1.0000
18.500 1.5768 0.11943 0.11576 -0.0816 0.0052 1.0000
18.750 1.5609 0.12645 0.12292 -0.0849 0.0051 1.0000
19.000 1.5450 0.13362 0.13023 -0.0884 0.0050 1.0000
19.250 1.5290 0.14096 0.13770 -0.0923 0.0049 1.0000
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