HT22 (ht22-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT22 (ht22-il) Reynolds number: 100,000 Max Cl/Cd: 36.24 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht22-il-100000-n5.txt Download as CSV file: xf-ht22-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6520 0.10873 0.10384 0.0359 1.0001 0.0449
-8.250 -0.6497 0.10485 0.10001 0.0330 1.0001 0.0461
-8.000 -0.6494 0.10099 0.09620 0.0274 1.0001 0.0475
-7.750 -0.6449 0.09639 0.09163 0.0191 1.0001 0.0481
-7.500 -0.6348 0.09119 0.08640 0.0117 1.0001 0.0483
-7.250 -0.6233 0.08591 0.08104 0.0060 1.0001 0.0484
-7.000 -0.6107 0.08069 0.07570 0.0016 1.0001 0.0485
-6.500 -0.5851 0.06482 0.05967 -0.0026 1.0001 0.0271
-6.250 -0.5721 0.06057 0.05537 -0.0040 1.0001 0.0264
-6.000 -0.5548 0.05565 0.05030 -0.0066 1.0001 0.0258
-5.750 -0.5344 0.05035 0.04474 -0.0093 1.0001 0.0256
-5.500 -0.5108 0.04463 0.03858 -0.0118 1.0001 0.0264
-5.250 -0.4859 0.03976 0.03315 -0.0132 1.0001 0.0271
-5.000 -0.4620 0.03558 0.02852 -0.0140 1.0001 0.0271
-4.750 -0.4368 0.03181 0.02424 -0.0144 1.0001 0.0271
-4.250 -0.3847 0.02550 0.01697 -0.0145 1.0001 0.0281
-4.000 -0.3586 0.02379 0.01507 -0.0145 1.0001 0.0301
-3.750 -0.3314 0.02228 0.01328 -0.0143 1.0001 0.0333
-3.500 -0.3036 0.02044 0.01108 -0.0138 1.0001 0.0350
-3.250 -0.2759 0.01895 0.00930 -0.0133 1.0001 0.0367
-3.000 -0.2495 0.01763 0.00801 -0.0130 1.0001 0.0413
-2.750 -0.2226 0.01662 0.00691 -0.0126 1.0001 0.0461
-2.500 -0.1961 0.01556 0.00584 -0.0121 1.0001 0.0513
-2.250 -0.1694 0.01486 0.00511 -0.0117 1.0001 0.0607
-2.000 -0.1427 0.01411 0.00436 -0.0113 1.0001 0.0735
-1.750 -0.1159 0.01338 0.00376 -0.0110 1.0001 0.0975
-1.500 -0.0896 0.01243 0.00330 -0.0109 1.0001 0.1909
-1.250 -0.0687 0.01057 0.00309 -0.0099 1.0001 0.5984
-1.000 -0.0318 0.00955 0.00286 -0.0100 1.0001 0.9999
-0.750 -0.0052 0.00953 0.00268 -0.0096 1.0001 0.9999
-0.500 0.0214 0.00953 0.00254 -0.0093 1.0001 0.9999
-0.250 0.0479 0.00953 0.00245 -0.0089 1.0001 0.9999
0.000 0.0744 0.00954 0.00240 -0.0086 1.0001 0.9999
0.250 0.1007 0.00956 0.00239 -0.0083 1.0001 0.9999
0.500 0.1270 0.00959 0.00242 -0.0080 1.0001 0.9999
0.750 0.1645 0.00968 0.00250 -0.0100 0.9553 0.9999
1.000 0.2079 0.00988 0.00254 -0.0125 0.8440 0.9999
1.250 0.2337 0.01024 0.00255 -0.0109 0.7373 0.9999
1.500 0.2570 0.01066 0.00260 -0.0093 0.6520 0.9999
1.750 0.2818 0.01107 0.00269 -0.0082 0.5847 0.9999
2.000 0.3073 0.01145 0.00282 -0.0075 0.5303 0.9999
2.250 0.3333 0.01182 0.00297 -0.0069 0.4843 0.9999
2.500 0.3597 0.01217 0.00316 -0.0064 0.4433 0.9999
2.750 0.3860 0.01254 0.00339 -0.0060 0.4053 0.9999
3.000 0.4125 0.01289 0.00362 -0.0057 0.3679 0.9999
3.250 0.4390 0.01325 0.00386 -0.0054 0.3307 0.9999
3.500 0.4655 0.01365 0.00413 -0.0051 0.2922 0.9999
3.750 0.4920 0.01407 0.00446 -0.0048 0.2525 0.9999
4.000 0.5184 0.01455 0.00482 -0.0046 0.2125 0.9999
4.250 0.5446 0.01512 0.00524 -0.0045 0.1749 0.9999
4.500 0.5708 0.01576 0.00577 -0.0043 0.1432 0.9999
4.750 0.5969 0.01647 0.00642 -0.0041 0.1173 0.9999
5.000 0.6228 0.01725 0.00716 -0.0039 0.0996 0.9999
5.250 0.6485 0.01805 0.00794 -0.0037 0.0854 0.9999
5.500 0.6742 0.01892 0.00888 -0.0034 0.0756 0.9999
5.750 0.6992 0.01996 0.00996 -0.0030 0.0690 0.9999
6.000 0.7247 0.02087 0.01100 -0.0027 0.0621 0.9999
6.250 0.7491 0.02206 0.01220 -0.0024 0.0572 0.9999
6.500 0.7742 0.02335 0.01373 -0.0019 0.0538 0.9999
6.750 0.7988 0.02473 0.01534 -0.0015 0.0507 0.9999
7.000 0.8226 0.02605 0.01671 -0.0012 0.0473 0.9999
7.250 0.8462 0.02785 0.01879 -0.0008 0.0445 0.9999
7.500 0.8694 0.03001 0.02135 -0.0004 0.0426 0.9999
7.750 0.8912 0.03248 0.02425 0.0000 0.0408 0.9999
8.000 0.9120 0.03482 0.02699 0.0002 0.0389 0.9999
8.250 0.9320 0.03664 0.02898 0.0003 0.0368 0.9999
8.500 0.9479 0.04004 0.03275 0.0002 0.0353 0.9999
8.750 0.9589 0.04469 0.03812 -0.0001 0.0345 0.9999
9.000 0.9627 0.05051 0.04460 -0.0013 0.0339 0.9999
9.250 0.9574 0.05746 0.05209 -0.0040 0.0337 0.9999
9.500 0.9422 0.06563 0.06065 -0.0093 0.0338 0.9999
9.750 0.9180 0.07678 0.07195 -0.0210 0.0343 0.9999
10.000 0.8961 0.08902 0.08417 -0.0309 0.0347 0.9999
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Polar data table (+)
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