HT23 (ht23-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT23 (ht23-il) Reynolds number: 200,000 Max Cl/Cd: 50.9 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht23-il-200000.txt Download as CSV file: xf-ht23-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HT23
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 -0.5378 0.08668 0.08350 0.0178 1.0000 0.0448
-8.000 -0.5375 0.08265 0.07950 0.0169 1.0000 0.0459
-7.750 -0.6527 0.08378 0.08046 0.0070 1.0000 0.0423
-7.500 -0.6464 0.08106 0.07779 0.0106 1.0000 0.0433
-7.250 -0.6370 0.07768 0.07440 0.0101 1.0000 0.0444
-7.000 -0.6263 0.07347 0.07016 0.0072 1.0000 0.0458
-6.750 -0.6136 0.06853 0.06516 0.0029 1.0000 0.0477
-6.500 -0.5970 0.06248 0.05894 -0.0032 1.0000 0.0509
-6.250 -0.5810 0.05412 0.04999 -0.0107 1.0000 0.0543
-6.000 -0.5650 0.05064 0.04663 -0.0106 1.0000 0.0558
-5.750 -0.5464 0.04774 0.04368 -0.0109 1.0000 0.0582
-4.750 -0.4471 0.02747 0.02128 -0.0134 1.0000 0.0404
-4.500 -0.4210 0.02427 0.01766 -0.0131 1.0000 0.0398
-4.250 -0.3940 0.02112 0.01410 -0.0127 1.0000 0.0378
-4.000 -0.3661 0.01865 0.01120 -0.0120 1.0000 0.0364
-3.750 -0.3382 0.01691 0.00922 -0.0114 1.0000 0.0367
-3.500 -0.3107 0.01555 0.00773 -0.0109 1.0000 0.0383
-3.250 -0.2828 0.01484 0.00690 -0.0104 1.0000 0.0417
-3.000 -0.2567 0.01327 0.00540 -0.0100 1.0000 0.0472
-2.750 -0.2294 0.01238 0.00449 -0.0095 1.0000 0.0544
-2.500 -0.2023 0.01144 0.00367 -0.0093 1.0000 0.0751
-2.250 -0.1765 0.00984 0.00295 -0.0093 1.0000 0.2439
-2.000 -0.1530 0.00855 0.00274 -0.0089 1.0000 0.5015
-1.750 -0.1361 0.00744 0.00270 -0.0059 1.0000 0.7646
-1.500 -0.0875 0.00703 0.00258 -0.0086 1.0000 1.0000
-1.250 -0.0613 0.00699 0.00242 -0.0082 1.0000 1.0000
-1.000 -0.0349 0.00697 0.00228 -0.0079 1.0000 1.0000
-0.750 -0.0086 0.00695 0.00219 -0.0075 1.0000 1.0000
-0.500 0.0178 0.00695 0.00213 -0.0072 1.0000 1.0000
-0.250 0.0442 0.00696 0.00209 -0.0069 1.0000 1.0000
0.000 0.0706 0.00698 0.00209 -0.0066 1.0000 1.0000
0.250 0.1110 0.00703 0.00213 -0.0093 0.9633 1.0000
0.500 0.1520 0.00719 0.00208 -0.0111 0.8458 1.0000
0.750 0.1725 0.00757 0.00202 -0.0086 0.7420 1.0000
1.000 0.1960 0.00798 0.00203 -0.0071 0.6669 1.0000
1.250 0.2214 0.00833 0.00207 -0.0064 0.6123 1.0000
1.500 0.2476 0.00865 0.00215 -0.0059 0.5694 1.0000
1.750 0.2743 0.00894 0.00224 -0.0055 0.5335 1.0000
2.000 0.3013 0.00922 0.00234 -0.0052 0.5026 1.0000
2.250 0.3284 0.00948 0.00246 -0.0049 0.4744 1.0000
2.500 0.3556 0.00973 0.00262 -0.0047 0.4485 1.0000
2.750 0.3829 0.01000 0.00277 -0.0045 0.4247 1.0000
3.000 0.4101 0.01025 0.00293 -0.0043 0.4013 1.0000
3.250 0.4375 0.01051 0.00311 -0.0041 0.3788 1.0000
3.500 0.4647 0.01077 0.00332 -0.0039 0.3568 1.0000
3.750 0.4921 0.01103 0.00353 -0.0037 0.3341 1.0000
4.000 0.5192 0.01131 0.00374 -0.0035 0.3119 1.0000
4.250 0.5465 0.01156 0.00397 -0.0034 0.2880 1.0000
4.500 0.5736 0.01185 0.00423 -0.0033 0.2638 1.0000
4.750 0.6006 0.01217 0.00447 -0.0031 0.2387 1.0000
5.000 0.6276 0.01249 0.00477 -0.0030 0.2130 1.0000
5.250 0.6545 0.01289 0.00514 -0.0029 0.1865 1.0000
5.500 0.6811 0.01338 0.00555 -0.0028 0.1577 1.0000
5.750 0.7072 0.01407 0.00611 -0.0027 0.1278 1.0000
6.000 0.7328 0.01496 0.00688 -0.0025 0.1014 1.0000
6.250 0.7587 0.01581 0.00775 -0.0022 0.0840 1.0000
6.500 0.7836 0.01689 0.00881 -0.0019 0.0737 1.0000
6.750 0.8091 0.01775 0.00973 -0.0016 0.0662 1.0000
7.000 0.8336 0.01900 0.01103 -0.0011 0.0604 1.0000
7.250 0.8587 0.02006 0.01220 -0.0007 0.0561 1.0000
7.500 0.8819 0.02185 0.01399 -0.0003 0.0523 1.0000
7.750 0.9064 0.02321 0.01561 0.0002 0.0494 1.0000
8.000 0.9306 0.02460 0.01721 0.0007 0.0466 1.0000
8.250 0.9539 0.02623 0.01905 0.0012 0.0444 1.0000
8.500 0.9758 0.02829 0.02124 0.0016 0.0425 1.0000
8.750 0.9927 0.03219 0.02553 0.0020 0.0407 1.0000
9.000 1.0124 0.03416 0.02797 0.0026 0.0393 1.0000
9.250 1.0271 0.03764 0.03195 0.0031 0.0384 1.0000
9.500 1.0363 0.04200 0.03686 0.0034 0.0379 1.0000
9.750 1.0382 0.04732 0.04271 0.0032 0.0378 1.0000
10.000 1.0311 0.05335 0.04922 0.0022 0.0379 1.0000
10.250 1.0143 0.05995 0.05619 -0.0003 0.0384 1.0000
10.500 0.9891 0.06696 0.06342 -0.0057 0.0390 1.0000
10.750 0.9608 0.07774 0.07432 -0.0169 0.0399 1.0000
11.000 0.9372 0.08790 0.08447 -0.0238 0.0408 1.0000
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Polar data table (+)
Polar graphs
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