HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.37 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hsnlf213-il-1000000.txt Download as CSV file: xf-hsnlf213-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9820 0.06588 0.06337 -0.0220 0.7966 0.0068
-14.000 -1.0368 0.05430 0.05144 -0.0277 0.7949 0.0067
-13.750 -1.0567 0.04927 0.04619 -0.0283 0.7927 0.0068
-13.500 -1.0750 0.04482 0.04151 -0.0279 0.7904 0.0069
-13.250 -1.0832 0.04164 0.03814 -0.0271 0.7882 0.0070
-13.000 -1.0875 0.03894 0.03527 -0.0260 0.7863 0.0071
-12.750 -1.0898 0.03649 0.03263 -0.0247 0.7843 0.0073
-12.500 -1.0877 0.03448 0.03044 -0.0233 0.7821 0.0075
-12.250 -1.0833 0.03269 0.02847 -0.0217 0.7799 0.0076
-12.000 -1.0749 0.03132 0.02692 -0.0201 0.7778 0.0078
-11.750 -1.0644 0.03031 0.02577 -0.0184 0.7758 0.0079
-11.500 -1.0666 0.02696 0.02203 -0.0159 0.7737 0.0082
-11.250 -1.0503 0.02591 0.02089 -0.0149 0.7723 0.0084
-11.000 -1.0307 0.02521 0.02014 -0.0143 0.7709 0.0086
-10.750 -1.0102 0.02457 0.01943 -0.0138 0.7694 0.0088
-10.500 -0.9894 0.02386 0.01864 -0.0132 0.7679 0.0091
-10.250 -0.9683 0.02306 0.01773 -0.0127 0.7664 0.0094
-10.000 -0.9469 0.02222 0.01678 -0.0121 0.7650 0.0096
-9.750 -0.9249 0.02139 0.01582 -0.0116 0.7636 0.0099
-9.500 -0.9021 0.02065 0.01496 -0.0112 0.7621 0.0102
-9.250 -0.8784 0.02006 0.01425 -0.0109 0.7605 0.0104
-9.000 -0.8580 0.01865 0.01267 -0.0101 0.7588 0.0107
-8.750 -0.8352 0.01781 0.01178 -0.0097 0.7575 0.0112
-8.500 -0.8101 0.01737 0.01131 -0.0096 0.7566 0.0115
-8.250 -0.7849 0.01693 0.01084 -0.0095 0.7555 0.0119
-8.000 -0.7597 0.01643 0.01029 -0.0093 0.7543 0.0123
-7.750 -0.7341 0.01599 0.00980 -0.0091 0.7531 0.0128
-7.500 -0.7078 0.01567 0.00943 -0.0091 0.7519 0.0132
-7.250 -0.6817 0.01528 0.00898 -0.0090 0.7506 0.0136
-7.000 -0.6589 0.01434 0.00799 -0.0085 0.7494 0.0143
-6.750 -0.6328 0.01398 0.00763 -0.0085 0.7481 0.0149
-6.500 -0.6066 0.01360 0.00722 -0.0084 0.7468 0.0155
-6.250 -0.5805 0.01322 0.00679 -0.0083 0.7457 0.0162
-6.000 -0.5540 0.01290 0.00643 -0.0082 0.7445 0.0168
-5.750 -0.5287 0.01240 0.00588 -0.0080 0.7432 0.0177
-5.500 -0.5022 0.01203 0.00551 -0.0080 0.7422 0.0189
-5.250 -0.4750 0.01175 0.00524 -0.0081 0.7414 0.0202
-5.000 -0.4474 0.01151 0.00499 -0.0082 0.7404 0.0213
-4.750 -0.4212 0.01105 0.00452 -0.0081 0.7392 0.0233
-4.500 -0.3936 0.01081 0.00427 -0.0082 0.7380 0.0253
-4.250 -0.3658 0.01060 0.00404 -0.0084 0.7368 0.0271
-4.000 -0.3385 0.01029 0.00376 -0.0084 0.7357 0.0308
-3.750 -0.3106 0.01009 0.00354 -0.0086 0.7346 0.0348
-3.500 -0.2828 0.00985 0.00335 -0.0087 0.7335 0.0424
-3.250 -0.2554 0.00955 0.00315 -0.0089 0.7323 0.0642
-3.000 -0.2285 0.00917 0.00296 -0.0090 0.7312 0.1078
-2.750 -0.2032 0.00855 0.00273 -0.0090 0.7300 0.2126
-2.500 -0.1798 0.00757 0.00243 -0.0090 0.7289 0.3949
-2.250 -0.1593 0.00625 0.00220 -0.0085 0.7274 0.6758
-2.000 -0.1294 0.00656 0.00254 -0.0087 0.7264 0.7294
-1.750 -0.0996 0.00674 0.00271 -0.0090 0.7254 0.7389
-1.500 -0.0700 0.00689 0.00284 -0.0094 0.7243 0.7463
-1.250 -0.0408 0.00711 0.00307 -0.0095 0.7230 0.7554
-1.000 -0.0123 0.00730 0.00330 -0.0094 0.7215 0.7652
-0.750 0.0159 0.00748 0.00353 -0.0091 0.7200 0.7759
-0.500 0.0445 0.00782 0.00388 -0.0089 0.7183 0.7861
-0.250 0.0726 0.00767 0.00374 -0.0089 0.7163 0.7902
0.000 0.1017 0.00766 0.00370 -0.0092 0.7140 0.7920
0.250 0.1309 0.00767 0.00370 -0.0095 0.7113 0.7935
0.500 0.1606 0.00761 0.00365 -0.0100 0.7089 0.7947
0.750 0.1902 0.00756 0.00359 -0.0104 0.7062 0.7956
1.000 0.2199 0.00749 0.00350 -0.0109 0.7031 0.7962
1.250 0.2495 0.00741 0.00339 -0.0113 0.6996 0.7966
1.500 0.2790 0.00738 0.00334 -0.0117 0.6960 0.7969
1.750 0.3088 0.00727 0.00325 -0.0122 0.6915 0.7971
2.000 0.3384 0.00716 0.00313 -0.0127 0.6858 0.7974
2.250 0.3679 0.00710 0.00305 -0.0131 0.6802 0.7979
2.500 0.3976 0.00703 0.00300 -0.0136 0.6744 0.7982
2.750 0.4271 0.00696 0.00290 -0.0140 0.6668 0.7983
3.000 0.4568 0.00688 0.00285 -0.0144 0.6560 0.7985
3.250 0.4863 0.00685 0.00283 -0.0149 0.6473 0.7986
3.500 0.5157 0.00683 0.00279 -0.0154 0.6313 0.7987
3.750 0.5439 0.00694 0.00275 -0.0156 0.5852 0.7989
4.000 0.5692 0.00752 0.00295 -0.0156 0.4959 0.7992
4.250 0.5941 0.00821 0.00328 -0.0157 0.4119 0.7994
4.500 0.6190 0.00885 0.00359 -0.0159 0.3366 0.7996
4.750 0.6437 0.00947 0.00391 -0.0160 0.2685 0.7996
5.000 0.6683 0.01007 0.00422 -0.0160 0.2081 0.7997
5.250 0.6930 0.01061 0.00453 -0.0161 0.1595 0.7998
5.500 0.7182 0.01107 0.00482 -0.0161 0.1256 0.7998
5.750 0.7437 0.01147 0.00510 -0.0162 0.1004 0.7998
6.000 0.7690 0.01187 0.00539 -0.0163 0.0802 0.8000
6.250 0.7946 0.01224 0.00568 -0.0163 0.0661 0.8002
6.500 0.8199 0.01260 0.00599 -0.0163 0.0555 0.8003
6.750 0.8450 0.01298 0.00631 -0.0163 0.0480 0.8003
7.000 0.8707 0.01328 0.00663 -0.0163 0.0438 0.8003
7.250 0.8954 0.01367 0.00698 -0.0163 0.0399 0.8003
7.500 0.9195 0.01410 0.00743 -0.0161 0.0369 0.8003
7.750 0.9446 0.01440 0.00775 -0.0160 0.0356 0.8003
8.000 0.9690 0.01475 0.00813 -0.0159 0.0341 0.8004
8.250 0.9926 0.01516 0.00854 -0.0157 0.0326 0.8004
8.500 1.0140 0.01575 0.00914 -0.0152 0.0307 0.8006
8.750 1.0354 0.01630 0.00975 -0.0147 0.0298 0.8007
9.000 1.0582 0.01670 0.01019 -0.0144 0.0292 0.8007
9.250 1.0800 0.01715 0.01068 -0.0140 0.0286 0.8007
9.500 1.1008 0.01764 0.01121 -0.0135 0.0279 0.8007
9.750 1.1183 0.01816 0.01177 -0.0125 0.0272 0.8007
10.000 1.1364 0.01876 0.01241 -0.0118 0.0266 0.8007
10.250 1.1547 0.01945 0.01313 -0.0112 0.0260 0.8008
10.500 1.1710 0.02031 0.01402 -0.0105 0.0252 0.8008
10.750 1.1812 0.02165 0.01543 -0.0092 0.0242 0.8008
11.000 1.1948 0.02272 0.01657 -0.0082 0.0238 0.8009
11.250 1.2124 0.02344 0.01735 -0.0077 0.0236 0.8009
11.500 1.2289 0.02425 0.01822 -0.0070 0.0233 0.8010
11.750 1.2446 0.02512 0.01915 -0.0063 0.0229 0.8010
12.000 1.2597 0.02605 0.02014 -0.0056 0.0226 0.8011
12.250 1.2745 0.02698 0.02113 -0.0049 0.0221 0.8011
12.500 1.2892 0.02791 0.02212 -0.0043 0.0216 0.8012
12.750 1.3051 0.02874 0.02298 -0.0038 0.0211 0.8013
13.000 1.3206 0.02959 0.02385 -0.0034 0.0205 0.8013
13.250 1.3321 0.03078 0.02507 -0.0027 0.0199 0.8014
13.500 1.3336 0.03284 0.02722 -0.0011 0.0192 0.8015
13.750 1.3422 0.03430 0.02877 -0.0002 0.0188 0.8017
14.000 1.3558 0.03534 0.02988 0.0003 0.0186 0.8018
14.250 1.3676 0.03652 0.03113 0.0008 0.0184 0.8020
14.500 1.3772 0.03792 0.03262 0.0014 0.0181 0.8023
14.750 1.3860 0.03941 0.03419 0.0020 0.0179 0.8027
15.000 1.3936 0.04102 0.03589 0.0026 0.0176 0.8029
15.250 1.4008 0.04267 0.03763 0.0032 0.0173 0.8031
15.500 1.4072 0.04445 0.03948 0.0037 0.0170 0.8032
15.750 1.4136 0.04629 0.04140 0.0040 0.0168 0.8034
16.000 1.4198 0.04820 0.04338 0.0042 0.0165 0.8036
16.250 1.4259 0.05019 0.04543 0.0043 0.0162 0.8037
16.500 1.4305 0.05242 0.04774 0.0042 0.0159 0.8039
16.750 1.4324 0.05504 0.05043 0.0041 0.0157 0.8041
17.000 1.4300 0.05821 0.05369 0.0039 0.0154 0.8043
17.250 1.4226 0.06209 0.05768 0.0035 0.0152 0.8044
17.500 1.4088 0.06698 0.06272 0.0027 0.0149 0.8045
17.750 1.4036 0.07098 0.06683 0.0017 0.0148 0.8047
18.000 1.4005 0.07483 0.07080 0.0004 0.0147 0.8049
18.250 1.3980 0.07874 0.07483 -0.0010 0.0146 0.8051
18.500 1.3918 0.08329 0.07949 -0.0027 0.0145 0.8052
18.750 1.3842 0.08819 0.08452 -0.0048 0.0144 0.8054
19.000 1.3737 0.09363 0.09009 -0.0072 0.0143 0.8056
19.250 1.3621 0.09941 0.09599 -0.0098 0.0142 0.8057
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