HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Reynolds number: 500,000 Max Cl/Cd: 59.78 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hsnlf213-il-500000-n5.txt Download as CSV file: xf-hsnlf213-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HSNLF(1)-0213 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.9660 0.05596 0.05256 -0.0280 0.7843 0.0071
-13.000 -1.0011 0.04902 0.04527 -0.0286 0.7823 0.0071
-12.750 -1.0235 0.04401 0.03993 -0.0277 0.7802 0.0072
-12.500 -1.0365 0.04017 0.03577 -0.0263 0.7782 0.0073
-12.250 -1.0432 0.03702 0.03230 -0.0246 0.7762 0.0075
-12.000 -1.0440 0.03443 0.02940 -0.0228 0.7744 0.0076
-11.750 -1.0395 0.03231 0.02700 -0.0211 0.7726 0.0078
-11.500 -1.0319 0.03066 0.02511 -0.0193 0.7709 0.0079
-11.250 -1.0209 0.02912 0.02342 -0.0179 0.7690 0.0081
-11.000 -1.0050 0.02803 0.02220 -0.0169 0.7670 0.0083
-10.750 -0.9869 0.02715 0.02123 -0.0162 0.7652 0.0084
-10.500 -0.9672 0.02641 0.02039 -0.0156 0.7634 0.0087
-10.250 -0.9469 0.02567 0.01955 -0.0150 0.7619 0.0090
-10.000 -0.9262 0.02486 0.01861 -0.0145 0.7605 0.0093
-9.750 -0.9049 0.02402 0.01760 -0.0139 0.7592 0.0098
-9.500 -0.8829 0.02320 0.01659 -0.0134 0.7579 0.0102
-9.250 -0.8610 0.02226 0.01552 -0.0130 0.7566 0.0106
-9.000 -0.8386 0.02147 0.01467 -0.0126 0.7553 0.0110
-8.750 -0.8152 0.02084 0.01398 -0.0123 0.7539 0.0113
-8.500 -0.7916 0.02016 0.01322 -0.0120 0.7525 0.0116
-8.250 -0.7678 0.01947 0.01245 -0.0116 0.7510 0.0120
-8.000 -0.7438 0.01879 0.01168 -0.0113 0.7495 0.0124
-7.750 -0.7197 0.01813 0.01092 -0.0110 0.7480 0.0128
-7.500 -0.6953 0.01751 0.01021 -0.0106 0.7468 0.0132
-7.250 -0.6707 0.01694 0.00955 -0.0103 0.7457 0.0135
-7.000 -0.6466 0.01633 0.00892 -0.0100 0.7445 0.0142
-6.750 -0.6211 0.01594 0.00849 -0.0099 0.7435 0.0148
-6.500 -0.5955 0.01554 0.00805 -0.0098 0.7424 0.0156
-6.250 -0.5698 0.01510 0.00757 -0.0097 0.7413 0.0164
-6.000 -0.5438 0.01470 0.00712 -0.0095 0.7401 0.0171
-5.750 -0.5186 0.01419 0.00661 -0.0094 0.7387 0.0180
-5.500 -0.4923 0.01383 0.00623 -0.0093 0.7373 0.0191
-5.250 -0.4658 0.01350 0.00588 -0.0093 0.7359 0.0204
-5.000 -0.4390 0.01321 0.00555 -0.0093 0.7347 0.0216
-4.750 -0.4126 0.01286 0.00521 -0.0093 0.7336 0.0237
-4.500 -0.3855 0.01260 0.00492 -0.0094 0.7325 0.0259
-4.250 -0.3586 0.01231 0.00463 -0.0094 0.7314 0.0284
-4.000 -0.3314 0.01207 0.00439 -0.0095 0.7303 0.0320
-3.750 -0.3042 0.01182 0.00414 -0.0095 0.7292 0.0372
-3.500 -0.2769 0.01158 0.00393 -0.0096 0.7281 0.0456
-3.250 -0.2496 0.01134 0.00374 -0.0097 0.7270 0.0609
-3.000 -0.2223 0.01104 0.00356 -0.0099 0.7259 0.0856
-2.750 -0.1959 0.01062 0.00337 -0.0100 0.7247 0.1374
-2.500 -0.1706 0.01001 0.00315 -0.0101 0.7234 0.2362
-2.250 -0.1467 0.00918 0.00287 -0.0101 0.7219 0.3788
-2.000 -0.1276 0.00778 0.00257 -0.0093 0.7204 0.6416
-1.750 -0.0993 0.00825 0.00318 -0.0090 0.7191 0.7298
-1.500 -0.0707 0.00862 0.00354 -0.0089 0.7178 0.7498
-1.250 -0.0428 0.00889 0.00384 -0.0085 0.7165 0.7644
-1.000 -0.0152 0.00909 0.00405 -0.0082 0.7152 0.7760
-0.750 0.0136 0.00915 0.00409 -0.0083 0.7141 0.7800
-0.500 0.0430 0.00915 0.00405 -0.0087 0.7130 0.7819
-0.250 0.0725 0.00916 0.00401 -0.0091 0.7116 0.7831
0.000 0.1022 0.00914 0.00398 -0.0097 0.7099 0.7839
0.250 0.1319 0.00911 0.00394 -0.0102 0.7077 0.7844
0.500 0.1615 0.00907 0.00389 -0.0107 0.7051 0.7847
0.750 0.1911 0.00902 0.00382 -0.0112 0.7020 0.7852
1.000 0.2205 0.00897 0.00373 -0.0116 0.6988 0.7857
1.250 0.2499 0.00894 0.00367 -0.0120 0.6959 0.7860
1.500 0.2796 0.00890 0.00366 -0.0125 0.6918 0.7862
2.000 0.3383 0.00874 0.00347 -0.0133 0.6819 0.7866
2.250 0.3677 0.00867 0.00345 -0.0137 0.6745 0.7869
2.500 0.3968 0.00857 0.00333 -0.0140 0.6658 0.7873
2.750 0.4261 0.00849 0.00328 -0.0144 0.6537 0.7876
3.000 0.4553 0.00845 0.00325 -0.0148 0.6409 0.7878
3.250 0.4841 0.00841 0.00317 -0.0150 0.6195 0.7879
3.500 0.5111 0.00855 0.00307 -0.0150 0.5599 0.7881
3.750 0.5356 0.00913 0.00328 -0.0149 0.4773 0.7883
4.000 0.5598 0.00980 0.00362 -0.0149 0.4032 0.7885
4.250 0.5829 0.01058 0.00402 -0.0148 0.3198 0.7888
4.500 0.6061 0.01131 0.00441 -0.0147 0.2462 0.7892
4.750 0.6300 0.01191 0.00476 -0.0147 0.1935 0.7895
5.000 0.6546 0.01241 0.00508 -0.0147 0.1541 0.7896
5.250 0.6796 0.01285 0.00538 -0.0147 0.1266 0.7898
5.500 0.7045 0.01326 0.00570 -0.0147 0.1051 0.7899
5.750 0.7295 0.01365 0.00601 -0.0147 0.0875 0.7900
6.000 0.7543 0.01404 0.00634 -0.0147 0.0733 0.7902
6.250 0.7791 0.01442 0.00668 -0.0146 0.0626 0.7904
6.500 0.8036 0.01481 0.00703 -0.0145 0.0549 0.7907
6.750 0.8281 0.01518 0.00739 -0.0144 0.0494 0.7910
7.000 0.8522 0.01557 0.00778 -0.0143 0.0451 0.7912
7.250 0.8763 0.01595 0.00818 -0.0142 0.0419 0.7914
7.500 0.8994 0.01640 0.00862 -0.0139 0.0387 0.7915
7.750 0.9224 0.01683 0.00908 -0.0136 0.0364 0.7916
8.000 0.9453 0.01725 0.00954 -0.0133 0.0346 0.7918
8.250 0.9674 0.01771 0.01003 -0.0130 0.0330 0.7919
8.500 0.9885 0.01824 0.01057 -0.0125 0.0316 0.7921
8.750 1.0076 0.01888 0.01124 -0.0118 0.0302 0.7922
9.000 1.0255 0.01943 0.01185 -0.0109 0.0295 0.7924
9.250 1.0438 0.02002 0.01250 -0.0101 0.0288 0.7926
9.500 1.0628 0.02067 0.01321 -0.0096 0.0280 0.7928
9.750 1.0816 0.02135 0.01394 -0.0091 0.0271 0.7930
10.000 1.0998 0.02207 0.01471 -0.0086 0.0263 0.7932
10.250 1.1169 0.02287 0.01555 -0.0080 0.0257 0.7933
10.500 1.1328 0.02376 0.01648 -0.0073 0.0250 0.7935
10.750 1.1467 0.02481 0.01758 -0.0065 0.0244 0.7937
11.000 1.1598 0.02592 0.01876 -0.0055 0.0239 0.7939
11.250 1.1753 0.02683 0.01975 -0.0048 0.0236 0.7941
11.500 1.1900 0.02780 0.02081 -0.0041 0.0232 0.7943
11.750 1.2044 0.02879 0.02189 -0.0034 0.0228 0.7946
12.000 1.2183 0.02983 0.02301 -0.0026 0.0223 0.7949
12.250 1.2316 0.03091 0.02416 -0.0019 0.0218 0.7953
12.500 1.2442 0.03206 0.02539 -0.0012 0.0213 0.7956
12.750 1.2559 0.03328 0.02669 -0.0004 0.0210 0.7958
13.000 1.2669 0.03456 0.02806 0.0003 0.0206 0.7960
13.250 1.2772 0.03592 0.02950 0.0011 0.0203 0.7962
13.500 1.2861 0.03740 0.03106 0.0019 0.0200 0.7964
13.750 1.2934 0.03904 0.03277 0.0027 0.0197 0.7966
14.000 1.2987 0.04090 0.03471 0.0035 0.0193 0.7968
14.250 1.3007 0.04309 0.03699 0.0045 0.0190 0.7970
14.500 1.3072 0.04488 0.03890 0.0051 0.0188 0.7972
14.750 1.3133 0.04674 0.04090 0.0056 0.0186 0.7974
15.000 1.3185 0.04872 0.04301 0.0060 0.0183 0.7976
15.250 1.3230 0.05083 0.04525 0.0063 0.0180 0.7978
15.500 1.3267 0.05311 0.04766 0.0064 0.0177 0.7980
15.750 1.3296 0.05557 0.05024 0.0064 0.0174 0.7982
16.000 1.3308 0.05830 0.05309 0.0062 0.0171 0.7985
16.250 1.3323 0.06110 0.05600 0.0059 0.0168 0.7987
16.500 1.3334 0.06406 0.05907 0.0053 0.0165 0.7989
16.750 1.3332 0.06730 0.06242 0.0045 0.0162 0.7992
17.000 1.3315 0.07085 0.06608 0.0034 0.0160 0.7994
17.250 1.3291 0.07462 0.06996 0.0021 0.0158 0.7996
17.500 1.3242 0.07888 0.07434 0.0006 0.0156 0.7998
17.750 1.3174 0.08358 0.07915 -0.0013 0.0154 0.8001
18.000 1.3075 0.08889 0.08460 -0.0035 0.0153 0.8003
18.250 1.2957 0.09465 0.09048 -0.0061 0.0151 0.8004
18.500 1.2814 0.10100 0.09696 -0.0091 0.0150 0.8006
18.750 1.2651 0.10788 0.10398 -0.0126 0.0149 0.8007
19.000 1.2486 0.11501 0.11127 -0.0163 0.0148 0.8009
19.250 1.2306 0.12268 0.11910 -0.0204 0.0148 0.8010
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Polar data table (+)
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