HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.4 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hsnlf213-il-1000000-n5.txt Download as CSV file: xf-hsnlf213-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.2261 0.06246 0.05928 -0.0242 0.7854 0.0044
-16.500 -1.2482 0.05602 0.05265 -0.0270 0.7831 0.0044
-16.250 -1.2626 0.05138 0.04784 -0.0282 0.7805 0.0045
-16.000 -1.2716 0.04773 0.04404 -0.0284 0.7779 0.0045
-15.750 -1.2772 0.04469 0.04086 -0.0281 0.7753 0.0046
-15.500 -1.2799 0.04205 0.03808 -0.0275 0.7728 0.0046
-15.250 -1.2802 0.03973 0.03564 -0.0267 0.7706 0.0047
-15.000 -1.2784 0.03764 0.03342 -0.0258 0.7682 0.0048
-14.750 -1.2746 0.03577 0.03142 -0.0248 0.7659 0.0049
-14.500 -1.2696 0.03402 0.02955 -0.0238 0.7637 0.0050
-14.250 -1.2626 0.03248 0.02787 -0.0227 0.7616 0.0051
-14.000 -1.2549 0.03100 0.02627 -0.0216 0.7596 0.0051
-13.750 -1.2453 0.02969 0.02484 -0.0204 0.7578 0.0053
-13.500 -1.2352 0.02843 0.02345 -0.0192 0.7563 0.0053
-13.250 -1.2233 0.02730 0.02222 -0.0180 0.7546 0.0054
-13.000 -1.2100 0.02628 0.02109 -0.0168 0.7529 0.0055
-12.750 -1.1961 0.02535 0.02005 -0.0155 0.7512 0.0056
-12.500 -1.1814 0.02456 0.01916 -0.0141 0.7496 0.0057
-12.250 -1.1643 0.02367 0.01816 -0.0132 0.7480 0.0058
-12.000 -1.1472 0.02270 0.01708 -0.0122 0.7464 0.0059
-11.750 -1.1278 0.02192 0.01621 -0.0115 0.7448 0.0061
-11.500 -1.1071 0.02125 0.01547 -0.0109 0.7432 0.0063
-11.250 -1.0855 0.02062 0.01478 -0.0103 0.7419 0.0064
-11.000 -1.0634 0.02003 0.01413 -0.0099 0.7407 0.0066
-10.750 -1.0408 0.01945 0.01349 -0.0095 0.7395 0.0068
-10.500 -1.0179 0.01889 0.01287 -0.0091 0.7382 0.0070
-10.250 -0.9946 0.01834 0.01225 -0.0087 0.7369 0.0071
-10.000 -0.9710 0.01782 0.01166 -0.0084 0.7356 0.0073
-9.750 -0.9471 0.01731 0.01109 -0.0081 0.7344 0.0075
-9.500 -0.9227 0.01684 0.01055 -0.0078 0.7331 0.0077
-9.250 -0.8981 0.01639 0.01004 -0.0076 0.7319 0.0078
-9.000 -0.8739 0.01586 0.00944 -0.0073 0.7307 0.0081
-8.750 -0.8493 0.01536 0.00890 -0.0070 0.7295 0.0084
-8.500 -0.8241 0.01496 0.00845 -0.0069 0.7281 0.0086
-8.250 -0.7985 0.01458 0.00805 -0.0067 0.7269 0.0089
-8.000 -0.7726 0.01423 0.00767 -0.0067 0.7260 0.0093
-7.750 -0.7465 0.01390 0.00731 -0.0066 0.7250 0.0097
-7.500 -0.7202 0.01359 0.00698 -0.0066 0.7240 0.0101
-7.250 -0.6937 0.01328 0.00663 -0.0066 0.7229 0.0104
-7.000 -0.6678 0.01287 0.00621 -0.0065 0.7218 0.0110
-6.750 -0.6413 0.01256 0.00589 -0.0065 0.7207 0.0116
-6.500 -0.6145 0.01227 0.00557 -0.0065 0.7197 0.0121
-6.250 -0.5876 0.01199 0.00528 -0.0065 0.7185 0.0127
-6.000 -0.5605 0.01174 0.00500 -0.0066 0.7174 0.0133
-5.750 -0.5336 0.01145 0.00469 -0.0066 0.7162 0.0142
-5.500 -0.5064 0.01120 0.00444 -0.0067 0.7150 0.0151
-5.250 -0.4789 0.01098 0.00420 -0.0068 0.7140 0.0161
-5.000 -0.4513 0.01078 0.00398 -0.0069 0.7130 0.0170
-4.750 -0.4238 0.01055 0.00374 -0.0070 0.7119 0.0184
-4.500 -0.3960 0.01034 0.00354 -0.0072 0.7111 0.0199
-4.250 -0.3680 0.01016 0.00336 -0.0074 0.7103 0.0213
-4.000 -0.3401 0.00995 0.00317 -0.0075 0.7092 0.0236
-3.750 -0.3119 0.00977 0.00300 -0.0077 0.7081 0.0262
-3.500 -0.2838 0.00958 0.00284 -0.0080 0.7069 0.0302
-3.250 -0.2557 0.00939 0.00269 -0.0082 0.7058 0.0368
-3.000 -0.2276 0.00920 0.00254 -0.0084 0.7048 0.0483
-2.750 -0.1995 0.00900 0.00241 -0.0086 0.7037 0.0637
-2.500 -0.1715 0.00876 0.00228 -0.0089 0.7026 0.0888
-2.000 -0.1172 0.00800 0.00196 -0.0093 0.7002 0.2146
-1.750 -0.0903 0.00755 0.00180 -0.0095 0.6991 0.3014
-1.500 -0.0647 0.00683 0.00158 -0.0097 0.6978 0.4448
-1.000 -0.0118 0.00617 0.00187 -0.0097 0.6956 0.7366
-0.750 0.0177 0.00639 0.00210 -0.0099 0.6944 0.7482
-0.500 0.0471 0.00664 0.00235 -0.0100 0.6928 0.7578
-0.250 0.0763 0.00659 0.00232 -0.0103 0.6907 0.7605
0.000 0.1059 0.00657 0.00229 -0.0107 0.6877 0.7616
0.250 0.1354 0.00655 0.00224 -0.0111 0.6842 0.7625
0.500 0.1649 0.00654 0.00221 -0.0115 0.6810 0.7632
0.750 0.1947 0.00651 0.00219 -0.0120 0.6778 0.7635
1.000 0.2245 0.00648 0.00215 -0.0125 0.6736 0.7637
1.250 0.2540 0.00645 0.00210 -0.0129 0.6684 0.7639
1.500 0.2837 0.00644 0.00208 -0.0134 0.6631 0.7642
1.750 0.3133 0.00641 0.00205 -0.0138 0.6549 0.7645
2.000 0.3428 0.00640 0.00202 -0.0143 0.6434 0.7648
2.250 0.3721 0.00641 0.00199 -0.0147 0.6270 0.7649
2.500 0.4012 0.00647 0.00198 -0.0150 0.6040 0.7650
2.750 0.4281 0.00685 0.00206 -0.0152 0.5306 0.7652
3.000 0.4532 0.00761 0.00238 -0.0154 0.4271 0.7653
3.250 0.4801 0.00802 0.00258 -0.0156 0.3748 0.7655
3.500 0.5065 0.00850 0.00281 -0.0159 0.3169 0.7658
3.750 0.5314 0.00916 0.00312 -0.0160 0.2385 0.7660
4.000 0.5574 0.00962 0.00337 -0.0162 0.1894 0.7662
4.250 0.5840 0.00998 0.00358 -0.0164 0.1569 0.7663
4.500 0.6106 0.01031 0.00378 -0.0166 0.1310 0.7663
4.750 0.6372 0.01063 0.00401 -0.0167 0.1093 0.7664
5.000 0.6638 0.01093 0.00423 -0.0169 0.0909 0.7665
5.250 0.6903 0.01124 0.00445 -0.0170 0.0756 0.7668
5.500 0.7168 0.01152 0.00469 -0.0172 0.0645 0.7670
5.750 0.7432 0.01181 0.00492 -0.0173 0.0555 0.7671
6.000 0.7696 0.01208 0.00516 -0.0174 0.0493 0.7672
6.250 0.7959 0.01235 0.00541 -0.0175 0.0445 0.7673
6.500 0.8220 0.01263 0.00567 -0.0176 0.0405 0.7674
6.750 0.8478 0.01292 0.00595 -0.0177 0.0368 0.7674
7.000 0.8737 0.01319 0.00623 -0.0177 0.0342 0.7675
7.250 0.8989 0.01352 0.00654 -0.0177 0.0316 0.7676
7.500 0.9241 0.01384 0.00686 -0.0176 0.0297 0.7677
7.750 0.9493 0.01413 0.00718 -0.0176 0.0287 0.7678
8.000 0.9740 0.01446 0.00752 -0.0175 0.0275 0.7678
8.250 0.9982 0.01481 0.00788 -0.0174 0.0264 0.7679
8.500 1.0219 0.01520 0.00827 -0.0172 0.0253 0.7680
8.750 1.0445 0.01566 0.00876 -0.0168 0.0240 0.7681
9.000 1.0679 0.01602 0.00915 -0.0166 0.0236 0.7682
9.250 1.0907 0.01641 0.00958 -0.0163 0.0231 0.7683
9.500 1.1128 0.01683 0.01003 -0.0159 0.0226 0.7684
9.750 1.1342 0.01728 0.01052 -0.0155 0.0221 0.7685
10.000 1.1529 0.01775 0.01103 -0.0146 0.0216 0.7686
10.250 1.1711 0.01829 0.01160 -0.0138 0.0211 0.7687
10.500 1.1900 0.01891 0.01226 -0.0132 0.0206 0.7688
10.750 1.2082 0.01959 0.01297 -0.0127 0.0201 0.7689
11.000 1.2250 0.02039 0.01381 -0.0120 0.0194 0.7690
11.250 1.2411 0.02124 0.01470 -0.0113 0.0189 0.7691
11.500 1.2588 0.02193 0.01546 -0.0107 0.0187 0.7693
11.750 1.2760 0.02267 0.01625 -0.0102 0.0185 0.7695
12.000 1.2927 0.02345 0.01708 -0.0096 0.0182 0.7697
12.250 1.3092 0.02423 0.01791 -0.0090 0.0179 0.7698
12.500 1.3254 0.02503 0.01877 -0.0084 0.0175 0.7699
12.750 1.3417 0.02581 0.01959 -0.0078 0.0169 0.7699
13.000 1.3574 0.02664 0.02046 -0.0072 0.0164 0.7700
13.250 1.3721 0.02756 0.02140 -0.0066 0.0159 0.7701
13.500 1.3850 0.02861 0.02249 -0.0058 0.0153 0.7702
13.750 1.3955 0.02987 0.02381 -0.0049 0.0148 0.7703
14.000 1.4090 0.03088 0.02489 -0.0043 0.0147 0.7703
14.250 1.4212 0.03200 0.02608 -0.0036 0.0145 0.7704
14.500 1.4325 0.03320 0.02735 -0.0029 0.0142 0.7705
14.750 1.4429 0.03448 0.02870 -0.0022 0.0140 0.7706
15.000 1.4529 0.03580 0.03010 -0.0015 0.0138 0.7707
15.250 1.4621 0.03721 0.03158 -0.0008 0.0135 0.7707
15.500 1.4706 0.03869 0.03313 -0.0002 0.0132 0.7708
15.750 1.4785 0.04024 0.03475 0.0004 0.0130 0.7709
16.000 1.4851 0.04192 0.03651 0.0010 0.0127 0.7710
16.250 1.4918 0.04365 0.03830 0.0015 0.0124 0.7710
16.500 1.4974 0.04557 0.04028 0.0019 0.0122 0.7711
16.750 1.5018 0.04765 0.04243 0.0023 0.0119 0.7712
17.000 1.5043 0.04999 0.04486 0.0025 0.0116 0.7712
17.250 1.5070 0.05241 0.04736 0.0026 0.0114 0.7713
17.500 1.5092 0.05496 0.05001 0.0025 0.0113 0.7714
17.750 1.5104 0.05769 0.05284 0.0023 0.0112 0.7714
18.000 1.5100 0.06070 0.05595 0.0020 0.0110 0.7715
18.250 1.5091 0.06387 0.05923 0.0014 0.0108 0.7716
18.500 1.5064 0.06737 0.06284 0.0007 0.0107 0.7716
18.750 1.5025 0.07116 0.06674 -0.0003 0.0105 0.7717
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