HT22 (ht22-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT22 (ht22-il) Reynolds number: 200,000 Max Cl/Cd: 45.97 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht22-il-200000.txt Download as CSV file: xf-ht22-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6537 0.10333 0.09990 0.0363 1.0001 0.0334
-8.000 -0.6507 0.09937 0.09597 0.0334 1.0001 0.0345
-7.750 -0.6481 0.09524 0.09188 0.0282 1.0001 0.0356
-7.500 -0.6372 0.08997 0.08661 0.0169 1.0001 0.0364
-7.250 -0.6215 0.08435 0.08090 0.0077 1.0001 0.0368
-7.000 -0.6134 0.07700 0.07348 0.0021 1.0001 0.0373
-6.750 -0.6116 0.07422 0.07083 0.0077 1.0001 0.0390
-6.500 -0.5988 0.07082 0.06742 0.0066 1.0001 0.0408
-6.250 -0.5821 0.06624 0.06278 0.0028 1.0001 0.0427
-6.000 -0.5610 0.06106 0.05745 -0.0023 1.0001 0.0455
-5.750 -0.5254 0.05683 0.05252 -0.0097 1.0001 0.0486
-5.500 -0.5150 0.04924 0.04506 -0.0111 1.0001 0.0503
-5.250 -0.4964 0.04623 0.04205 -0.0114 1.0001 0.0522
-5.000 -0.4737 0.04300 0.03866 -0.0125 1.0001 0.0556
-4.750 -0.4445 0.03850 0.03349 -0.0147 1.0001 0.0630
-4.500 -0.4232 0.03538 0.03045 -0.0149 1.0001 0.0656
-4.250 -0.3948 0.03299 0.02746 -0.0156 1.0001 0.0765
-4.000 -0.3724 0.03009 0.02474 -0.0158 1.0001 0.0816
-3.750 -0.3362 0.02330 0.01675 -0.0150 1.0001 0.0512
-3.500 -0.3065 0.01965 0.01260 -0.0142 1.0001 0.0417
-3.250 -0.2777 0.01727 0.00976 -0.0136 1.0001 0.0407
-3.000 -0.2499 0.01601 0.00836 -0.0132 1.0001 0.0436
-2.750 -0.2219 0.01495 0.00712 -0.0126 1.0001 0.0471
-2.500 -0.1944 0.01353 0.00560 -0.0121 1.0001 0.0498
-2.250 -0.1675 0.01257 0.00472 -0.0118 1.0001 0.0574
-2.000 -0.1404 0.01161 0.00377 -0.0114 1.0001 0.0658
-1.750 -0.1132 0.01090 0.00315 -0.0111 1.0001 0.0822
-1.500 -0.0859 0.01004 0.00253 -0.0109 1.0001 0.1292
-1.250 -0.0714 0.00722 0.00230 -0.0086 1.0001 0.7557
-1.000 -0.0316 0.00676 0.00209 -0.0099 1.0001 0.9999
-0.750 -0.0048 0.00675 0.00195 -0.0095 1.0001 0.9999
-0.500 0.0221 0.00675 0.00185 -0.0092 1.0001 0.9999
-0.250 0.0489 0.00675 0.00178 -0.0089 1.0001 0.9999
0.000 0.0757 0.00676 0.00175 -0.0086 1.0001 0.9999
0.250 0.1024 0.00678 0.00175 -0.0083 1.0001 0.9999
0.500 0.1290 0.00680 0.00177 -0.0080 1.0001 0.9999
0.750 0.1556 0.00684 0.00183 -0.0077 1.0001 0.9999
1.000 0.1939 0.00690 0.00192 -0.0099 0.9725 0.9999
1.250 0.2383 0.00707 0.00193 -0.0124 0.8471 0.9999
1.500 0.2582 0.00753 0.00192 -0.0096 0.7247 0.9999
1.750 0.2812 0.00803 0.00197 -0.0080 0.6299 0.9999
2.000 0.3063 0.00848 0.00207 -0.0073 0.5607 0.9999
2.250 0.3324 0.00887 0.00219 -0.0067 0.5075 0.9999
2.500 0.3589 0.00922 0.00233 -0.0064 0.4627 0.9999
2.750 0.3856 0.00955 0.00250 -0.0061 0.4224 0.9999
3.000 0.4125 0.00985 0.00267 -0.0058 0.3841 0.9999
3.250 0.4394 0.01017 0.00285 -0.0056 0.3460 0.9999
3.500 0.4663 0.01050 0.00304 -0.0054 0.3062 0.9999
3.750 0.4932 0.01087 0.00329 -0.0052 0.2635 0.9999
4.000 0.5199 0.01131 0.00356 -0.0051 0.2165 0.9999
4.250 0.5464 0.01189 0.00394 -0.0050 0.1702 0.9999
4.500 0.5728 0.01260 0.00445 -0.0048 0.1317 0.9999
4.750 0.5990 0.01341 0.00514 -0.0046 0.1067 0.9999
5.000 0.6254 0.01419 0.00588 -0.0044 0.0904 0.9999
5.250 0.6514 0.01503 0.00671 -0.0041 0.0790 0.9999
5.500 0.6769 0.01610 0.00771 -0.0038 0.0711 0.9999
5.750 0.7031 0.01709 0.00885 -0.0033 0.0661 0.9999
6.000 0.7291 0.01796 0.00975 -0.0030 0.0609 0.9999
6.250 0.7539 0.01966 0.01153 -0.0026 0.0570 0.9999
6.500 0.7800 0.02091 0.01302 -0.0021 0.0544 0.9999
6.750 0.8055 0.02243 0.01478 -0.0016 0.0520 0.9999
7.000 0.8304 0.02375 0.01624 -0.0013 0.0492 0.9999
7.250 0.8521 0.02694 0.01964 -0.0011 0.0465 0.9999
7.500 0.8747 0.02950 0.02268 -0.0007 0.0455 0.9999
7.750 0.8956 0.03253 0.02625 -0.0002 0.0448 0.9999
8.000 0.9137 0.03621 0.03053 0.0000 0.0438 0.9999
8.250 0.9279 0.04072 0.03563 -0.0001 0.0425 0.9999
8.500 0.9333 0.04759 0.04311 -0.0010 0.0431 0.9999
8.750 0.9320 0.05512 0.05108 -0.0030 0.0444 0.9999
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Polar data table (+)
Polar graphs
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