HT22 (ht22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT22 (ht22-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.36 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht22-il-1000000-n5.txt Download as CSV file: xf-ht22-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HT22
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7117 0.13565 0.13401 0.0556 1.0001 0.0050
-10.500 -0.7079 0.13194 0.13030 0.0543 1.0001 0.0049
-7.500 -0.7344 0.01979 0.01610 -0.0136 1.0001 0.0050
-7.250 -0.7104 0.01762 0.01358 -0.0135 1.0001 0.0051
-7.000 -0.6851 0.01614 0.01185 -0.0134 1.0001 0.0051
-6.750 -0.6604 0.01414 0.00950 -0.0132 1.0001 0.0054
-6.500 -0.6339 0.01337 0.00862 -0.0130 1.0001 0.0057
-6.250 -0.6071 0.01285 0.00802 -0.0129 1.0001 0.0059
-6.000 -0.5801 0.01235 0.00746 -0.0127 1.0001 0.0062
-5.750 -0.5531 0.01177 0.00678 -0.0126 1.0001 0.0065
-5.500 -0.5260 0.01116 0.00607 -0.0124 1.0001 0.0068
-5.250 -0.4987 0.01062 0.00544 -0.0122 1.0001 0.0072
-5.000 -0.4713 0.01016 0.00490 -0.0120 1.0001 0.0074
-4.750 -0.4439 0.00977 0.00445 -0.0118 1.0001 0.0076
-4.500 -0.4165 0.00916 0.00377 -0.0117 1.0001 0.0082
-4.250 -0.3889 0.00883 0.00342 -0.0115 1.0001 0.0087
-4.000 -0.3612 0.00853 0.00310 -0.0114 1.0001 0.0093
-3.750 -0.3334 0.00826 0.00280 -0.0113 1.0001 0.0099
-3.500 -0.3056 0.00804 0.00257 -0.0111 1.0001 0.0106
-3.250 -0.2777 0.00772 0.00225 -0.0110 1.0001 0.0119
-3.000 -0.2499 0.00750 0.00203 -0.0109 1.0001 0.0131
-2.750 -0.2219 0.00731 0.00183 -0.0107 1.0001 0.0143
-2.500 -0.1877 0.00711 0.00161 -0.0120 0.9510 0.0164
-2.250 -0.1646 0.00718 0.00148 -0.0104 0.8674 0.0189
-2.000 -0.1397 0.00730 0.00132 -0.0095 0.7871 0.0220
-1.750 -0.1130 0.00741 0.00119 -0.0091 0.7103 0.0262
-1.500 -0.0856 0.00750 0.00108 -0.0090 0.6401 0.0325
-1.250 -0.0579 0.00756 0.00098 -0.0089 0.5819 0.0422
-1.000 -0.0300 0.00759 0.00090 -0.0088 0.5348 0.0559
-0.750 -0.0022 0.00758 0.00083 -0.0088 0.4924 0.0804
-0.500 0.0258 0.00752 0.00077 -0.0088 0.4578 0.1190
-0.250 0.0537 0.00736 0.00073 -0.0088 0.4285 0.1882
0.000 0.0815 0.00713 0.00070 -0.0089 0.4019 0.2886
0.250 0.1092 0.00680 0.00069 -0.0091 0.3776 0.4268
0.500 0.1368 0.00653 0.00069 -0.0091 0.3543 0.5457
0.750 0.1634 0.00607 0.00071 -0.0090 0.3317 0.7276
1.000 0.1824 0.00550 0.00075 -0.0065 0.3111 0.9447
1.250 0.2162 0.00559 0.00076 -0.0077 0.2857 0.9999
1.500 0.2442 0.00575 0.00079 -0.0077 0.2608 0.9999
1.750 0.2721 0.00592 0.00085 -0.0076 0.2346 0.9999
2.000 0.3000 0.00610 0.00091 -0.0075 0.2077 0.9999
2.250 0.3279 0.00627 0.00098 -0.0075 0.1857 0.9999
2.500 0.3557 0.00648 0.00107 -0.0074 0.1604 0.9999
3.000 0.4113 0.00691 0.00130 -0.0073 0.1150 0.9999
3.250 0.4391 0.00712 0.00143 -0.0072 0.0981 0.9999
3.500 0.4669 0.00734 0.00157 -0.0072 0.0821 0.9999
3.750 0.4946 0.00756 0.00173 -0.0071 0.0685 0.9999
4.250 0.5499 0.00798 0.00207 -0.0069 0.0510 0.9999
4.500 0.5776 0.00820 0.00227 -0.0068 0.0446 0.9999
4.750 0.6051 0.00843 0.00247 -0.0067 0.0388 0.9999
5.000 0.6327 0.00866 0.00268 -0.0066 0.0344 0.9999
5.250 0.6602 0.00888 0.00291 -0.0065 0.0313 0.9999
5.500 0.6876 0.00916 0.00318 -0.0064 0.0277 0.9999
5.750 0.7150 0.00940 0.00344 -0.0063 0.0262 0.9999
6.000 0.7424 0.00965 0.00371 -0.0062 0.0247 0.9999
6.250 0.7696 0.00992 0.00399 -0.0061 0.0228 0.9999
6.500 0.7966 0.01026 0.00434 -0.0060 0.0210 0.9999
6.750 0.8236 0.01063 0.00476 -0.0058 0.0197 0.9999
7.000 0.8506 0.01092 0.00509 -0.0057 0.0192 0.9999
7.250 0.8775 0.01122 0.00543 -0.0055 0.0184 0.9999
7.500 0.9043 0.01154 0.00580 -0.0054 0.0174 0.9999
7.750 0.9309 0.01190 0.00620 -0.0052 0.0165 0.9999
8.000 0.9572 0.01234 0.00666 -0.0051 0.0155 0.9999
8.250 0.9831 0.01293 0.00733 -0.0049 0.0145 0.9999
8.500 1.0095 0.01327 0.00773 -0.0047 0.0141 0.9999
8.750 1.0357 0.01366 0.00819 -0.0045 0.0136 0.9999
9.000 1.0616 0.01410 0.00869 -0.0043 0.0130 0.9999
9.250 1.0874 0.01455 0.00920 -0.0041 0.0124 0.9999
9.500 1.1129 0.01503 0.00974 -0.0040 0.0117 0.9999
9.750 1.1380 0.01561 0.01038 -0.0037 0.0110 0.9999
10.000 1.1625 0.01635 0.01121 -0.0035 0.0104 0.9999
10.250 1.1876 0.01685 0.01180 -0.0033 0.0100 0.9999
10.500 1.2122 0.01745 0.01249 -0.0030 0.0096 0.9999
10.750 1.2365 0.01808 0.01322 -0.0027 0.0092 0.9999
11.000 1.2605 0.01874 0.01396 -0.0025 0.0087 0.9999
11.250 1.2842 0.01943 0.01474 -0.0022 0.0083 0.9999
11.500 1.3072 0.02024 0.01563 -0.0019 0.0078 0.9999
11.750 1.3287 0.02133 0.01684 -0.0016 0.0073 0.9999
12.000 1.3511 0.02215 0.01778 -0.0012 0.0071 0.9999
12.250 1.3726 0.02309 0.01885 -0.0009 0.0068 0.9999
12.500 1.3933 0.02412 0.02002 -0.0005 0.0066 0.9999
12.750 1.4133 0.02522 0.02125 -0.0001 0.0063 0.9999
13.000 1.4323 0.02641 0.02257 0.0003 0.0060 0.9999
13.250 1.4502 0.02772 0.02401 0.0007 0.0058 0.9999
13.500 1.4663 0.02921 0.02564 0.0012 0.0055 0.9999
13.750 1.4795 0.03104 0.02763 0.0016 0.0053 0.9999
14.000 1.4878 0.03343 0.03021 0.0020 0.0051 0.9999
14.250 1.4926 0.03605 0.03302 0.0023 0.0049 0.9999
14.500 1.4930 0.03885 0.03601 0.0024 0.0049 0.9999
14.750 1.4763 0.04377 0.04114 0.0000 0.0049 0.9999
15.000 1.4137 0.06512 0.06289 -0.0211 0.0051 0.9999
15.250 1.3416 0.08333 0.08130 -0.0322 0.0055 0.9999
15.500 1.2381 0.10727 0.10543 -0.0456 0.0060 0.9999
15.750 1.1537 0.12925 0.12755 -0.0576 0.0065 0.9999
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Polar data table (+)
Polar graphs
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